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Journal articles on the topic 'Aerodynamic package'

Author: Grafiati
Published: 4 June 2021
Last updated: 17 February 2022

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1

KIEDROWSKI, Jakub, Grzegorz JENDRO, Arkadiusz KAMIŃSKI, and Paweł FABIŚ. "Aerodynamics package for formula student car WT-02." Scientific Journal of Silesian University of Technology. Series Transport 109 (December 1, 2020): 55–60. http://dx.doi.org/10.20858/sjsutst.2020.109.5.

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This paper is a summary of the design and workmanship of the aero package vehicle Formula Student. Simulation research projects of the aerodynamic system were conducted. The article proposes different variants of the aero wings and conducted simulation studies of construction. The aerodynamics system impact on strength and reliability of selected models was determined.
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2

Guerrero, Alex, and Robert Castilla. "Aerodynamic Study of the Wake Effects on a Formula 1 Car." Energies 13, no. 19 (October 5, 2020): 5183. http://dx.doi.org/10.3390/en13195183.

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The high complexity of current Formula One aerodynamics has raised the question of whether an urgent modification in the existing aerodynamic package is required. The present study is based on the evaluation and quantification of the aerodynamic performance on a 2017 spec. adapted Formula 1 car (the latest major aerodynamic update) by means of Computational Fluid Dynamics (CFD) analysis in order to argue whether the 2022 changes in the regulations are justified in terms of aerodynamic necessities. Both free stream and flow disturbance (wake effects) conditions are evaluated in order to study and quantify the effects that the wake may cause on the latter case. The problem is solved by performing different CFD simulations using the OpenFoam solver. The significance and originality of the research may dictate the guidelines towards an overall improvement of the category and it may set a precedent on how to model racing car aerodynamics. The studied behaviour suggests that modern F1 cars are designed and well optimised to run under free stream flows, but they experience drastic aerodynamic losses (ranging from −23% to 62% in downforce coefficients) when running under wake flows. Although the overall aerodynamic loads are reduced, there is a fuel efficiency improvement as the power that is required to overcome the drag is smaller. The modern performance of Ground Effect by means of vortices management represent a very unique and complex way of modelling modern aerodynamics, but at the same time notably compromises the performance of the cars when an overtaking maneuver is intended.
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3

Yoshida, Yuki, Edyta Dziemińska, and Tomasz Goetzendorf-Grabowski. "Amphibious airplane for underwater observation: Conceptual design." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 14 (September 7, 2018): 2627–37. http://dx.doi.org/10.1177/0954410018799140.

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This paper aims at presenting the conceptual design of an amphibious airplane for underwater observation in the territory of Japan. Taking into account the specificity of this type of vehicles, particular attention should be paid to the analysis of aerodynamic and dynamic characteristics of aircraft. In order to cope up with this topic, commercial tools have been exploited (such as ANSYS Fluent for wing aerodynamics analysis) as well as the home-built software PANUKL package for aerodynamic analysis of the entire airplane and simulation and dynamic stability analysis for dynamic analysis. Special attention was given to the priorities resulting from understanding the characteristics of the Japanese client.
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4

Koterov, V. N., V. M. Krivtsov, and V. I. Zubov. "Software package to calculate the aerodynamic characteristics of aircrafts." Proceedings of the Institute for System Programming of the RAS 29, no. 6 (2017): 271–88. http://dx.doi.org/10.15514/ispras-2017-29(6)-17.

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5

Cole, Reena, Mark Davies, and Jeff Punch. "A Board Level Study of an Array of Ball Grid Components—Aerodynamic and Thermal Measurements." Journal of Electronic Packaging 125, no. 4 (December 1, 2003): 480–89. http://dx.doi.org/10.1115/1.1604811.

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Electronic package manufacturers publish thermal characteristics of components, which are measured using standard tests, measuring a thermal resistance value for a single component on a standard test printed circuit board (PCB). This limits the applicability of the characterization, as it does not show what aerodynamic or thermal interaction each package will have in a real system. This paper presents a new board-level electronics system test vehicle consisting of an array of ball grid components on three different effective thermal conductivity multi-layer PCB’s. Aerodynamic and thermal measurements are presented. It appears that PCB’s populated with low profile electronic packages behave like flat plates, leading to the proposition that component temperatures can be calculated using flat plate predictions. It is shown how both the airflow and the board conductivity can have a critical effect on the junction temperature, and a simple design rule is suggested, in terms of influence factors, to take account of these effects. These will lead to better estimates of electronic system reliability in the early part of the design cycle.
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Didenko, Anton, Vladislav Borisenko, and Jose Leoro. "Load distribution method in helicopter blade multibody dynamics system." E3S Web of Conferences 258 (2021): 09076. http://dx.doi.org/10.1051/e3sconf/202125809076.

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The paper focuses on the loads applied to the helicopter blade cross-sections in the multibody dynamics system. The main objective is to simplify the blade aerodynamics calculation and avoid time-consuming CFD methods. For this reason, the way of computing blade aerodynamics is proposed by using multibody dynamics methods with a linear-elastic blade model. As the primary tool for further research, the MCS Adams software package is selected. Splitting the main rotor blade into a finite number of sections, each having its own average value of installation and coning angles, simplifies the calculation. Afterward, expressions for the total flow velocity around the blade section and its angle of attack are obtained through vector operations. This provides a measure of aerodynamic forces acting on each section in its cross-sectional coordinate system. In conclusion, the article provides the formalized method of aerodynamic force distribution between blade sections in the multibody model as well as the correlation between the flow coordinate system and the blade chord coordinate system.
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7

Kudrov, M. A., A. S. Shcheglov, and V. S. Bugaev. "Study of vortex element method parameters and their effect on rigid rotation bodies aerodynamic computations." Journal of «Almaz – Antey» Air and Space Defence Corporation, no. 1 (March 30, 2019): 51–58. http://dx.doi.org/10.38013/2542-0542-2019-1-51-58.

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The purpose of this study was to implement a software package that allows non-stationary aerodynamic computations of fixed rotation bodies using the vortex element method. In the course of the work, we developed an algorithm for rigid rotation bodies aerodynamic computations by means of this method. Furthermore, we studied the influence of calculation parameters on the results obtained.
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8

Ivanov, A. V., G. E. Dumnov, A. V. Muslaev, and M. V. Popov. "Numerical modeling software package for computing aerodynamic characteristics of air cyclones." Chemical and Petroleum Engineering 49, no. 3-4 (July 2013): 188–96. http://dx.doi.org/10.1007/s10556-013-9724-6.

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9

Kalugin, V. T., A. Y. Lutsenko, and D. M. Slobodyanyuk. "The Influence of the Interference Effects on the Aerodynamic Characteristics of the Reentry Vehicle and Its Parachute System Structural Elements During Their Separation." Proceedings of Higher Educational Institutions. Маchine Building, no. 10 (727) (November 2020): 54–64. http://dx.doi.org/10.18698/0536-1044-2020-10-54-64.

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This work considers the aerodynamic characteristics of the reentry vehicle (RV) of a segmental-conical shape, and the parachute container hatch cover (PCHC) during its separation. Due to the aerodynamic interference, the hatch may collide with the RV. The authors propose a method of studying the aerodynamic characteristics of the PCHC and RV based on modelling using the dynamic mesh technology in the FlowVision software package. Stationary flow around the RV until the hatch cover separation, flow around the hatch cover and free flow are calculated. As the result of the calculations, the PCHC trajectories (excluding gravitational forces) under various initial separation conditions, as well as the aerodynamic characteristics of the RV are obtained. The cases when the hatch cover collides with the RV are identified.
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10

Wei, Jian Zheng, Rui Qiang Ma, Hui Feng Tan, and Wen Ting Zhang. "Aerodynamic Analysis of Inflatable Membrane Aeroshell." Applied Mechanics and Materials 423-426 (September 2013): 1705–10. http://dx.doi.org/10.4028/www.scientific.net/amm.423-426.1705.

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With continuous developments of the manned space flight and planetary exploration missions, a new inflatable re-entry aeroshell becomes one of the hot topics of international research. It has the obvious advantages of the easy package, light weight, large resistance area, the low coefficient of ballistic, and the small heat generated by hypersonic air. This vehicle can provide a new way for the emergency return of astronauts, deep space instrumentation and payload recovery. This paper focuses on an inflatable membrane aeroshell with a single loop. Three kinds of cone angle of 75 degrees, 90 degrees and 105 degrees are respectively studied aerodynamic drag. These results show that aerodynamic drag is relationship not only with cone angle but also aerodynamic configuration.
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11

Qiao, Yan Chao, Zi Qi Guo, Bao Gang Zhang, and Yao Lin Shi. "Optimization for the Air-Pod Shape." Advanced Materials Research 308-310 (August 2011): 136–41. http://dx.doi.org/10.4028/www.scientific.net/amr.308-310.136.

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in order to optimize the air-pod shape, this paper details work conducted using the commercial CFD software package ANSYS: Fluent to simulate the aerodynamic of air-pod. In our research, the results as followed: 1) In the benchmark, our comparative analysis of the flow over the NASA 0012 airfoil from the Experimental Data Base for Computer Program Assessment (AGARD-AR-138, 1979) implies that the ANSYS: Fluent software package numerical method simulates the airfoil viscous flow with the same accuracy as the wind-tunnel experiment. We can use it to finish our research. 2) We build the 3-D model to compute the aerodynamic of the air-pod. We choose the cylinder at first step. From the results we can see the pressure and wall shear concentrate at the side face of the cylinder. The pressure at the side faces is about twice than the direct side. Next step we will compute different models, such as spherical and drop-shaped, et al. then we can compare the pressure and wall shear field value for different models at different conditions. This work gives us best way to optimize the aerodynamic shape of air-pod.
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Baltrenas, Pranas, Rasa Vaiškūnaite, and Valdas Špakauskas. "EXPERIMENTAL STUDY AND MATHEMATICAL MODELLING OF BIOFILTER AERODYNAMIC RESISTANCE." JOURNAL OF ENVIRONMENTAL ENGINEERING AND LANDSCAPE MANAGEMENT 12, no. 3 (September 30, 2004): 79–84. http://dx.doi.org/10.3846/16486897.2004.9636823.

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Development of industry is not always accompanied with the implementation of clean technologies, thus the problem of air and water purification remains. For the moment, pollution with different paint components is widely spread and hard to be solved. A biofilter was developed at the Department Environmental Protection of Vilnius Gediminas Technical University (VGTU), and its chemical and physical purification principles and properties are analysed in works [1–3]. Besides the efficiency of pollutant cleaning, the characteristics of filter aerodynamic resistance are also essential, therefore, the aerodynamic properties of the biofilter are analysed in this work. For anticipation and theoretical evaluation of aerodynamic processes going on in a biological air‐purification device, the processes occurring in the object being investigated ‐ a biofilter ‐ were modelled with the help of Phoenics, Versions 3.2 and 3.5. Aerodynamic processes ‐ in‐coming flow velocity and aerodynamic charge resistance ‐ were analysed with the help of the software package Phoenics, Versions 3.2 and 3.5. Modelling was based on mathematical equations that describe physical laws.
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13

Martirosyan, A. A., V. I. Mileshin, Ya M. Druzhinin, and P. G. Kozhemyako. "Сomputational and Experimental Investigation of Aerodynamic Characteristics of a Counter-Rotating fan Using Various Software Packages." Herald of the Bauman Moscow State Technical University. Series Mechanical Engineering, no. 2 (125) (April 2019): 115–30. http://dx.doi.org/10.18698/0236-3941-2019-2-115-130.

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The paper presents the results of computing aerodynamic properties of the CRTF2A counter-rotating cowled fan developed as part of the European VITAL program. To achieve these results, we used the following software packages: NUMECA FINE TURBO, ANSYS CFX and CIAMs own 3D--IMP--MULTI hydrocode. We use the RANS approach to model turbulent flows. We performed a three-dimensional computation, completing Reynolds-averaged Navier --- Stokes equations by various turbulence models for the following relative angular frequency modes: n = 1 and 0.9. We used the following turbulence models available in the software packages: k--ε (ANSYS CFX, 3D--IMP--MULTI), k--ε (ANSYS CFX, NUMECA FINE TURBO, 3D--IMP--MULTI), SST (NUMECA FINE TURBO, ANSYS CFX, 3D--IMP--MULTI). We plotted head characteristics for each software package and determined the main differences. We plotted adiabatic efficiency and total pressure ratios as functions of height for the first and second rotors at the maximum efficiency points for both modes in the ANSYS CFX, NUMECA FINE TURBO and 3D--IMP--MULTI software packages
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14

Craig, Christopher, and Martin A. Passmore. "Methodology for the Design of an Aerodynamic Package for a Formula SAE Vehicle." SAE International Journal of Passenger Cars - Mechanical Systems 7, no. 2 (April 1, 2014): 575–85. http://dx.doi.org/10.4271/2014-01-0596.

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15

Hu, Hong. "A rotor section aerodynamic design package using the direct iterative surface curvature method." Computer Methods in Applied Mechanics and Engineering 190, no. 32-33 (May 2001): 4279–87. http://dx.doi.org/10.1016/s0045-7825(00)00318-2.

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16

Garkusha, V. V., S. R. Shakirov, S. I. Shpak, and V. V. Yakovlev. "Software Complex for Modeling the Gas Inlet Process in an Arbitrary Set of Reception." Vestnik NSU. Series: Information Technologies 17, no. 4 (2019): 23–32. http://dx.doi.org/10.25205/1818-7900-2019-17-4-5-23-32.

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The paper presents a software package for modeling the dynamic processes of the working gas passing through an arbitrary set of tanks connected by an arbitrary set of pipelines Calculations were carried out for various combinations of tank joints, including modeling complex aerodynamic installations of ITAM SB RAS.
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17

Lee, C. "Taranis and beyond: inspiring aerodynamic capability." Aeronautical Journal 118, no. 1206 (August 2014): 845–59. http://dx.doi.org/10.1017/s0001924000009593.

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Abstract In his 1916 book, Aircraft in Warfare, the Dawn of the Fourth Arm, F.W. Lanchester wrote: “The supremacy of British aircraft can only be maintained by the adoption of a thoroughly progressive constructional policy, guided constantly by the most recent scientific discovery and research, and by utilising to the full information and experience gained in the Services.” The recent successful flight trials of the Taranis low-observable unmanned demonstrator aircraft provide the latest evidence of the UK’s continued capacity for the entire design, development, manufacture, and flight testing of world-leading combat aircraft, particularly with regard to Aerodynamics. Taranis is both the culmination of many years’ research and development in the UK and a starting-point for the next generation of UK combat air systems. In this lecture, Taranis is reviewed, in such detail as current sensitivities will allow, in the wider context of UK combat aircraft aerodynamic capability, exemplified by the leading roles taken by the UK in the Tornado and Typhoon programmes and the important contribution made to the development of the F-35 Lightning II Joint Strike Fighter. The immediate technical challenges associated with the aerodynamic design and qualification of a low-observable air vehicle are considerable. In this instance they have been compounded by the balanced view taken within the project of trade-offs against many parameters. However, the UK aerodynamics community faces equally stringent challenges in terms of the identification and delivery of the most appropriate future systems; increasingly complex and demanding operational and functional requirements; and, perhaps most of all, maintaining an affordable and cost-effective capability in the face of strict budgetary pressures and austere economic conditions. Nevertheless, those challenges are accompanied by a wide range of opportunities, namely for national and international partnership; radically innovative engineering solutions and approaches; new thinking; and the engagement of the best minds and ideas in the UK academic community. Taranis represented a big integration task, requiring a particular set of skills to pull together the total package, resting on a bedrock of mastery of the technical issues. It has been an inspirational experience for those of us who have worked on it. It has demonstrated that the UK is capable of achieving the most demanding current and anticipated military aerodynamic requirements and has signposted the way to an exciting and nationally important future.
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18

Cheng, Xiao Han, Shan Ming Luo, Xue Feng Chang, and Dan Xie. "Numerical Analysis of an External Flow-Field around a Formula SAE Car Body Based on FLUENT." Advanced Materials Research 1039 (October 2014): 17–24. http://dx.doi.org/10.4028/www.scientific.net/amr.1039.17.

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This paper proposed a method to analysis an external flow-field around a Formula SAE car. Firstly, the body of Formula SAE car was designed conforming to the FSAE rules using CATIA. Then, the model of the external flow-field around the vehicle was established using computational fluid dynamic technology. A comparative analysis of the aerodynamic characteristics was made for the body between the conditions of being without the wing package and being with the wing package under different attack angle to get the static pressure graph, the lift force and the drag force then worked out the drag coefficient and confirmed which is the most suitable angle for the wings. The results showed that: the static pressure of the front body, the front part of the tires and the driver’s chest and head is the highest; the body has good streamline since its drag coefficient is 0.385; the rear wings can supply 65% downforce, when the attack angle of the rear wing is set to 8°. Finally, the real mold was fabricated according to the above 3D model and the analysis results. The method presented in this paper can provide theoretical basis and technical parameter for the aerodynamic formation designing and amelioration of the Formula SAE cars. Also it has guiding significance for the design and aerodynamic analysis of the Ordinary Passenger car.
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19

Shcheglov, Georgy A., and Sergey A. Dergachev. "Vortex Loops Based Method for Subsonic Aerodynamic Loads Calculation." MATEC Web of Conferences 221 (2018): 05004. http://dx.doi.org/10.1051/matecconf/201822105004.

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The new modification of vortex method is considered. It is based on closed vortex loops that can be considered as the separate vortex “superelement”. It is shown that such approach has number of advantages for vortex wakes evolution simulation. The loops generation algorithm permits to simulate the separation zone due to the self-organization of the loops. In this case, there is no need to determine the location of the vortex sheet separation zones. The developed software package can be used in the calculation of aerodynamic loads on unmanned aerial vehicles, as well as in solving the aeroelasticity problems of structural elements of these aircraft.
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20

Abid, Muhammad, Hafiz Abdul Wajid, Muhammad Zohair Iqbal, Shayan Najam, Ali Arshad, and Ammad Ahmad. "DESIGN AND ANALYSIS OF AN AERODYNAMIC DOWNFORCE PACKAGE FOR A FORMULA STUDENT RACE CAR." IIUM Engineering Journal 18, no. 2 (December 1, 2017): 212–24. http://dx.doi.org/10.31436/iiumej.v18i2.679.

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This paper presents design of aerodynamic downforce generating devices (front wing, rear wing and diffuser) to enhance the performance of the Formula Student Race Car using numerical and experimental studies. Numerical results using computational fluid dynamics (CFD) studies were primarily validated with the experimental results performed in the wind tunnel. It was concluded that the use of a downforce package can enhance the performance of the vehicle in the competition.
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21

Kosykh, Pavel V. "DEVELOPMENT OF AERODYNAMIC DIAGRAMS OF HIGH-LOADED REVERSE AXIAL FANS." Interexpo GEO-Siberia 2 (July 8, 2020): 72–81. http://dx.doi.org/10.33764/2618-981x-2020-2-72-81.

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Present-day achievements in the field of strength calculation and structural optimization allow creating main mine fans with higher tip speed than in currently used machines. The paper considers the features of calculating the aerodynamic diagrams of mine reverse axial fans with a tip speed over 200 m/s. It is shown that at such speed it is possible to obtain high-flow fans with significantly smaller dimensions than their existing counterparts. Aerodynamic diagrams with high reverse characteristics (flow rate of more than 0.7 from the direct mode for the network of the same aerodynamic characteristics as in direct mode) are developed. The aerodynamic characteristics of the developed diagrams are calculated in the ANSYS software package. It is shown that an increase in the tip speed contributes to an increase in reverse properties of fans compared to less high-speed machines designed for the same total pressure. The limiting values of axial velocity coefficient and pressure coefficient are determined, at which it is possible to obtain a fan without an inlet guide vane, with a monotonic dependence of total pressure on flow rate.
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22

Sheard, A. G., and K. Daneshkhah. "The Conceptual Design of High Pressure Reversible Axial Tunnel Ventilation Fans." Advances in Acoustics and Vibration 2012 (December 11, 2012): 1–11. http://dx.doi.org/10.1155/2012/562309.

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Tunnel ventilation fans, classically, must have the ability to both supply and extract air from a tunnel system, with the operator's choice dependent on the tunnel ventilation system's operating mode most appropriate at any given point in time. Consequently, tunnel ventilation fans must incorporate a reversible aerodynamic design which limits the maximum fan pressure rise. This paper presents three high pressure reversible fan concepts. These comprise a two-stage counter rotating fan, a single-stage high speed fan, and a two-stage fan with a single motor and impeller on each end of the motor shaft. The authors consider the relative merits of each concept. The third concept offers the most compact fan, transform, silencer, and damper package size. The authors discuss the mechanical design challenges that occur with a two-stage fan with a single motor and impeller on each end of the motor shaft. They present and consider a selected motor bearing arrangement and casing design for maintainability. Finally, the authors present both prototype fan and full-scale package aerodynamic and acoustic performance, before discussing the challenges presented by high temperature certification in accordance with the requirements of EN 12101-3: 2012.
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23

Erturk, Burak, and Yavuz Yaman. "Assessment of the performance of a cruise missile wing depending on design parameters at various flight conditions." MATEC Web of Conferences 304 (2019): 02009. http://dx.doi.org/10.1051/matecconf/201930402009.

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The design of a cruise missile wing is a multidisciplinary work, since the wing has to provide enough aerodynamic forces while being structurally safe. In order to meet the design requirements and achieve a successful design, several parameters of the wing need to be investigated at various flight conditions. In this paper, lift forces and flutter speeds are obtained for different wing geometries, at various altitudes and speeds. The design of experiments is constructed by changing the several variables of the wing to have better understanding of the effect of design parameters. The aerodynamic analyses for predicting the lift force are performed by using FLUENT and the aeroelastic analyses for the determination of the flutter speed are conducted by using ZAERO package programs.
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24

Boiko, Andrey V., Kirill V. Demyanko, Yuri M. Nechepurenko, and Grigory V. Zasko. "On the Use of Probability-Based Methods for Estimating the Aerodynamic Boundary-Layer Thickness." Fluids 6, no. 8 (July 28, 2021): 267. http://dx.doi.org/10.3390/fluids6080267.

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In this paper, known probabilistic methods for estimating the thickness of the boundary layer of a two-dimensional laminar flow of viscous incompressible fluid are extended to three-dimensional laminar flows of a viscous compressible medium. Their applicability to the problems of boundary-layer stability is studied with the LOTRAN3 software package, which allows us to compute the position of laminar-turbulent transition in three-dimensional aerodynamic configurations.
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25

Pravidlo, M. N., N. A. Lyubimova, and L. V. Bykov. "Numerical investigation of gas dynamics in the pyro actuator found in the mechanism for unfolding aerodynamic surfaces." Journal of «Almaz – Antey» Air and Space Defence Corporation, no. 2 (June 30, 2017): 37–42. http://dx.doi.org/10.38013/2542-0542-2017-2-37-42.

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The article presents a mathematical model of a pyro actuator found in the mechanism for unfolding aerodynamic surfaces of aircraft, which includes a collector system. The mathematical model proposed takes into account linked gas dynamic processes in the internal pyro actuator chambers and the dynamics of its mechanical traveller. We supply results of numerically investigating the main parameters of working body flow, obtained by using the ANSYS software package.
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26

Petronevich, V. V. "Organization principles and functional capabilities of the POTOK software package used for aerodynamic experiment automation." Automation and Remote Control 71, no. 11 (November 2010): 2475–82. http://dx.doi.org/10.1134/s0005117910110202.

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27

Golomazov, M. M., V. S. Finchenko, A. A. Ivankov, and S. I. Shmatov. "Program package for the computer-aided aerodynamic design system for descent vehicles in planetary atmospheres." Solar System Research 46, no. 7 (December 2012): 542–47. http://dx.doi.org/10.1134/s003809461207012x.

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28

Tihonchik, S. S., and N. I. Puchko. "Low-pressure nozzle with aerodynamic fuel atomization." Proceedings of the National Academy of Sciences of Belarus, Physical-Technical Series 65, no. 3 (October 21, 2020): 357–64. http://dx.doi.org/10.29235/1561-8358-2020-65-3-357-364.

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A research was carried out with the construction of a model of a low-pressure nozzle with aerodynamic fuel atomization, which shows the advantages of nozzles of this type. In order to reduce the time at the stage of development and calculations, modern computer design systems were used. The research was carried out in the Flow Simulation module of the SolidWorks software package, which allows you to calculate and build a model of the internal flow around the nozzle using already known parameters. These parameters were set through the program conditions panel: fuel consumption per second; air flow rate at the inlet to the nozzle; static pressure in the combustion chamber. The calculations performed by the module made it possible to evaluate the manufacturability of the design, as well as the internal processes of mixing fuel with air. To determine the quality of fine dispersion of the fuel atomization, a model of the velocity field was calculated over the entire section of the nozzle, from which it can be seen that the maximum flow rate of the fuel is achieved in the outlet channels of the fuel atomizer of the nozzle. The results obtained indicate the operation of the low-pressure principle while maintaining high-quality fuel atomization. The use of low-pressure nozzle with aerodynamic fuel atomization is possible in modern gas turbine engines of civil aircraft, as well as in gas turbine.
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29

KWON, Y. D., S. B. KWON, J. H. DOH, and HYUN-KOOK KIM. "FLUID-STRUCTURE-INTERACTION ANALYSIS OF GOLF CLUBS COMPRISING AIR GUIDES." International Journal of Modern Physics B 25, no. 31 (December 20, 2011): 4289–93. http://dx.doi.org/10.1142/s0217979211066799.

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An FSI analysis of wood is performed to predict the downward aerodynamic force caused by the face loft angle. Several experiments are carried out to retrieve the shaft stiffness as well as the stiffness of the entire system, which consists of a human body and the arm gripping the wood. A sudden load is applied to the head of the wood, and the dynamic response is captured using a digital camcorder. The motion of a white dot marked at the head of wood is tracked by a TEMA package to form a trajectory map as a function of time. The applied load is divided by the measured dynamic deflection to yield the dynamic stiffness of the club head gripped by the golfer. With these quantities (i.e., the downward force and stiffness of the wood head), one can predict the sole deflection caused by the aerodynamic downward force. To eliminate the inconsistent downward deflection that often results in missed shots, we create an air guide on the head of the wood to lead the direction of air flow downward. The air guide mounted on the head induces an upward aerodynamic force that compensate for the downward force. An FSI analysis is again performed on the wood head comprising the air guide to examine the nullified net aerodynamic force. Result show, that the deflection induced by the aerodynamic force is minimized, thus allowing a golfer to expect a more consistent and stable shot.
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30

El-Sayed, A. F. Abdel Azim, C. Hirsch, and R. Derdelinckx. "Dynamics of Vertical Axis Wind Turbines (Darrieus Type)." International Journal of Rotating Machinery 2, no. 1 (1995): 33–41. http://dx.doi.org/10.1155/s1023621x95000182.

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A computing package that combines finite element methods for evaluating the resonance frequencies and modes of turbine subcomponents (blade, tower and shaft) together with the aerodynamic calculations for forces and moments taking into consideration the dynamic stall as well as the dynamic response is developed. This method was applied to a realistic VAWT; namely; the PIONEER I built in the Netherlands by Fokker company. A reasonable agreement between the calculated and field results was predicted.
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Kim, Jang-Kweon, and Seok-Hyung Oh. "Experimental Study on the Aerodynamic Performance of Double Inlet Sirocco Fan for a Package Air Conditioner." Journal of the Korea Society For Power System Engineering 17, no. 1 (February 28, 2013): 58–63. http://dx.doi.org/10.9726/kspse.2013.17.1.058.

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32

Prasad, CS, Q.-Z. Chen, O. Bruls, F. D’Ambrosio, and G. Dimitriadis. "Aeroservoelastic simulations for horizontal axis wind turbines." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 231, no. 2 (November 19, 2016): 103–17. http://dx.doi.org/10.1177/0957650916678725.

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This paper describes the development of a complete methodology for the aeroservoelastic modelling of horizontal axis wind turbines at the conceptual design stage. The methodology is based on the implementation of unsteady aerodynamic modelling, advanced description of the control system and nonlinear finite element calculations in the Samcef Wind Turbines design package. The aerodynamic modelling is carried out by means of fast techniques, such as the blade element method and the unsteady vortex lattice method, including a free wake model. The complete model also includes a description of a doubly fed induction generator and its control system for variable speed operation. The Samcef Wind Turbines software features a nonlinear finite element solver with multi-body dynamics capability. The full methodology is used to perform complete aeroservoelastic simulations of a realistic 2 MW wind turbine model. The interaction between the three components of the approach is carefully analysed and presented here.
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Navó, Àlex, and Josep M. Bergada. "Aerodynamic Study of the NASA’s X-43A Hypersonic Aircraft." Applied Sciences 10, no. 22 (November 19, 2020): 8211. http://dx.doi.org/10.3390/app10228211.

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A 2D aerodynamic study of the NASA’s X-43A hypersonic aircraft is developed using two different approaches. The first one is analytical and based on the resolution of the oblique shock wave and Prandtl–Meyer expansion wave theories supported by an in-house program and considering a simplified aircraft’s design. The second approach involves the use of a Computational Fluid Dynamics (CFD) package, OpenFOAM and the real shape of the aircraft. The aerodynamic characteristics defined as the lift and drag coefficients, the aerodynamic efficiency and the pitching moment coefficient are calculated for different angles of attack. Evaluations are made for an incident Mach number of 7 and an altitude of 30 km. For both methodologies, the required angles of attack to achieve a Vertical Force Balance (VFB) and a completely zero pitching moment conditions are considered. In addition, an analysis to optimise the nose configuration of the aircraft is performed. The mass flow rate throughout the scramjet as a function of the angle of attack is also presented in the CFD model in addition to the pressure, density, temperature and Mach fields. Before presenting the corresponding results, a comparison between the aerodynamic coefficients in terms of the angle of attack of both models is carried out in order to properly validate the CFD model. The paper clarifies the requirements needed to make sure that both oblique shock waves originating from the leading edge meet just at the scramjet inlet clarifying the advantages of fulfilling such condition.
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Sung, Lai Gwo, Wan Zaidi Wan Omar, Ahmad Zafri Zainudin, S. Mansor, and Tholudin Mat Lazim. "Aerodynamic Analysis of the Preliminary Design of SURIAKAR 4 Using CFD." Applied Mechanics and Materials 629 (October 2014): 507–12. http://dx.doi.org/10.4028/www.scientific.net/amm.629.507.

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A four-wheel solar car, the SURIAKAR 4, was designed based on the revised regulations of the Challenger Class World Solar Challenge (2013). It is a four-wheel car with the front and back wheels enclosed in a wind cheating cover. The cockpit is located in such a way that it sits between the front and rear wheel, within the wheel cover on the right side of the car. This paper investigates the aerodynamic characteristics of the car, especially the drag and lift forces, and other forces and moments that determine the stability of the car using CFD package ANSYS Fluent. The model analysis was done with 2.23 million elements after a thorough grid independence study was conducted. The drag coefficient of SURIAKAR 4 is 0.1817. With a frontal area of 0.8934 m2 and at the design speed, the car requires 2132 W of power to overcome this aerodynamic drag. The results also showed that the airflow quality around the car is relatively well-behaved, with only a few turbulent flow points identified. This flow incurs drag penalty and thus have to be modified.
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35

Bashkirov, Igor G., Sergey L. Chernyshev, Vladlen S. Gorbovskoy, Andrey V. Kazhan, Vyacheslav G. Kazhan, and Victor V. Kovalenko. "To the issue of evaluating sonic boom overpressure and loudness." MATEC Web of Conferences 304 (2019): 02003. http://dx.doi.org/10.1051/matecconf/201930402003.

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At present, in the world there is a growing interest in the development of a new generation of supersonic passenger aircraft. One of the main problems of creating such aircraft is to ensure both an acceptable sonic boom level and high aerodynamic characteristics in the supersonic cruising mode. This requires the development of reliable methods for obtaining the near field under the plane with taking into account the influence of the boundary layer, calculation of overpressure signature on the ground and evaluation of sonic boom loudness. In this work four variants of the equivalent body of revolution of minimum sonic boom with different nose sharpening were investigated for an aircraft weighing 19 tons in supersonic cruising flight at Mach number of 1.7 and altitude of 15.5 km using the software package for solving the Reynolds–averaged Navier–Stokes equations (RANS) ANSYS CFX. A macro for calculating the overpressure signature on the ground for the distribution of disturbances in the near field under the aircraft and a program for evaluating the sonic boom loudness in various metrics were developed. Computational mesh verification of the results was carried out, the obtained overpressure signatures were compared with theoretical data and calculation results from the software package for the integration of complete system of Euler equations by finite–difference method X–CODE. The effect of the sharpening of the nose part on aerodynamic drag and sound boom characteristics was shown. The work was done in the interests of the international project RUMBLE (RegUlation and norM for low sonic Boom LEvels).
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Abdelfattah, S., and M. T. Schobeiri. "Experimental and numerical investigations of aerodynamic behavior of a three-stage high-pressure turbine at different operation conditions." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 226, no. 6 (October 26, 2011): 1535–49. http://dx.doi.org/10.1177/0954406211423725.

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Using the Reynolds-averaged Navier–Stokes-based numerical methods to simulate the flow field, efficiency and performance of high-pressure turbine components of multi-stage steam turbines result in substantial differences between the experimental and the numerical results pertaining to the individual flow quantities. These differences are integrally noticeable in terms of major discrepancies in aerodynamic losses, efficiency, and performance of the turbine. As a consequence, engine manufacturers are compelled to frequently calibrate their simulation package by performing a series of experiments before issuing efficiency and performance guaranty. The aim of this article is to investigate the cause of the aforementioned differences by utilizing a three-stage high-pressure research turbine with three-dimensional compound lean blades as the platform for experimental and numerical investigations. Experimental data were obtained using interstage aerodynamic measurements at three measurement stations, namely, downstream of the first rotor row, the second stator row, and the second rotor row. Detailed measurements were conducted using custom-designed five-hole probes traversed in both circumferential and radial directions. Aerodynamic measurements were carried out within a rotational speed range of 1800–2800 r/min. Numerical simulations were performed utilizing a commercially available computational fluid dynamics code. A detailed mesh of the three stages was created and used to simulate the corresponding operating conditions. The experimental and numerical results were compared following a critical discussion relative to differences mentioned above.
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Pracheta, Dutta, Acharya Anup, Alam Shahriar, and Rahman Bakaul Saifur. "Computational Study on Effect of Flap Deflection on NACA 2412 Airfoil in Subsonic Flow." Applied Mechanics and Materials 829 (March 2016): 9–14. http://dx.doi.org/10.4028/www.scientific.net/amm.829.9.

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This computational study is aimed at studying the effects of flap deflection angle on aerodynamic coefficients of NACA 2412 airfoil and thus predicting the suitability of using the airfoil with flap at various phases of flight. The change in airflow over the airfoil at different angles of attack (0, 4, 8 and 12 degrees) and at different flap deflections give a clear understanding for the use of right combination of these two parameters. A full package of pictorial description for visualizing the changes in flow with and without the flap is provided through pressure and velocity contours.
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38

Leutwyler, Zachary, and Charles Dalton. "A Computational Study of Torque and Forces Due to Compressible Flow on a Butterfly Valve Disk in Mid-stroke Position." Journal of Fluids Engineering 128, no. 5 (February 11, 2006): 1074–82. http://dx.doi.org/10.1115/1.2236129.

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The ability to accurately predict the aerodynamic torque and lift and drag forces on a 2-D model of a 0.18 aspect ratio biconvex circular-arc disk operating in a compressible flow using computational fluid dynamics (CFD) was investigated. Fluent 6.0 was the CFD package utilized to perform these calculations. Grid-convergence and time-convergence/stability were analyzed first, followed by a qualitative study of the Spalart-Allmaras, k-ε, and k-ω turbulence models with their enhancement features and model variants. Fluent was used to predict the pressure profile on the disk surface for disk positions 30, 45, and 60 deg (where 0 deg is the fully closed position) and over a range of pressure ratios. The pressure ratios were selected to determine the capability of CFD to accurately predict the flow field and resulting torque in flows ranging from nearly incompressible to highly compressible. Fluent predictions for the pressure profiles on the disk were compared to test data so that the lift and drag forces and aerodynamic torque could be determined responsibly. Acceptable comparisons were noted.
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39

Шийко, Олександр Миколайович, Анатолій Михайлович Павлюченко, Андрій Вікторович Скорик, Олексій Анатолійович Обухов, and Ігор Володимирович Коплик. "РОЗРАХУНОК АЕРОДИНАМІЧНИХ ХАРАКТЕРИСТИК НАДЗВУКОВИХ ОПЕРЕНИХ ОСЕСИМЕТРИЧНИХ ТІЛ ОБЕРТАННЯ." Aerospace technic and technology, no. 2 (April 22, 2019): 4–17. http://dx.doi.org/10.32620/aktt.2019.2.01.

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The subject of research in the article is the aerodynamic forces arising from the flight of supersonic feathered rotation bodies such as unguided rockets. The aim of the work is to develop a method for calculating the aerodynamic coefficients of the resultant forces and moments of supersonic feathered bodies of revolution such as unguided missiles when flown around at an angle of attack with pre-, trans- and supersonic speeds according to drawings of their external contours. Tasks: using modern software systems and flight experiments, develop a method for calculating the distribution of normal and tangential stresses over the surface of a supersonic feathered body of rotation, their equivalent and aerodynamic coefficients at up-, trans- and supersonic flow velocities at an angle of attack. The applied methods are the numerical solution of the Navier-Stokes equations, the use of two-parameter differential models of near-wall turbulent viscosity, verification of the methodology by comparing the results of calculations with the data of flight experiments and known data on the aerodynamic resistance of the object of research. The following results were obtained. Based on the numerical solution of the Navier-Stokes equations in the ANSYS CFX software package using the γ-ReΘt SST–model of Menter’s near-wall turbulence, a method is developed for calculating the aerodynamic characteristics of supersonic axially symmetric rotation bodies of uncontrollable missiles according to drawings of the external contours in the presence of a counter-flow angle. Using the developed technique it is possible to calculate the aerodynamic coefficients of friction resistance, pressure resistance and bottom resistance at sub-, trans- and supersonic speeds. Characteristics include the coefficients of the longitudinal aerodynamic force, transverse aerodynamic force, aerodynamic stabilizing moment and the coordinate of the center of pressure of the feathered body of rotation. For the calculations, were applied the external contours of the unguided missile M–21OФ. Calculations were performed for the counter-flow Mach numbers within0,1 £ M∞ £ 2,5. The aerodynamic coefficients were calculated as functions of the Mach number M∞. In order to determine the Reynolds number of the beginning of the laminar-turbulent transition in the boundary layer for this type of aircraft the characteristics of the friction resistance were calculated and compared with the flight data for two samples of research aerophysical complexes. Conclusions. The scientific novelty of the results is as follows: a pilot test was created and involved the results of flight experiments on Reynolds numbers of the start of a laminar-turbulent transition in the boundary layers of a method for calculating the aerodynamic drag coefficients of supersonic axially rotated bodies of rotation like uncontrollable missiles according to the drawings of their external contours during turning angle of attack based on the numerical solution of the Reynolds-averaged Navier-Stokes equations in the framework of the programme product ANSYS CFX using γ-ReΘt SST–Menter turbulence model. Verification of the calculation results was carried out on the basis of their comparison with the known values of the aerodynamic characteristics of the object of research with the axisymmetric flow.
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40

Onishi, Yasuyuki, Thomas Ramsay, Timothy Juan, and James McKillen. "The Thermal and Aerodynamic Development of a Cooling and Heat Resistance Package for a New Hybrid Sports Car." SAE International Journal of Passenger Cars - Mechanical Systems 8, no. 1 (April 14, 2015): 155–64. http://dx.doi.org/10.4271/2015-01-1526.

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41

Gad-el-Hak, Ibrahim. "Fluid–Structure Interaction for Biomimetic Design of an Innovative Lightweight Turboexpander." Biomimetics 4, no. 1 (March 22, 2019): 27. http://dx.doi.org/10.3390/biomimetics4010027.

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Inspired by bird feather structures that enable the resistance of powerful aerodynamic forces in addition to their lower weight to provide stable flight, a biomimetic composite turbine blade was proposed for a low-temperature organic Rankine cycle (ORC) turboexpander that is capable of producing lower weight expanders than that of stainless steel expanders, in addition to reduce its manufacturing cost, and hence it may contribute in spreading ORC across nonconventional power systems. For that purpose, the fluid–structure interaction (FSI) was numerically investigated for a composite turbine blade with bird-inspired fiber orientations. The aerodynamic forces were evaluated by computational fluid dynamics (CFD) using the commercial package ANSYS-CFX (version 16.0) and then these aerodynamic forces were transferred to the solid model of the proposed blade. The structural integrity of the bird-mimetic composite blade was investigated by performing finite element analysis (FEA) of composite materials with different fiber orientations using ANSYS Composite PrepPost (ACP). Furthermore, the obtained mechanical performance of the composite turbine blades was compared with that of the stainless steel turbine blades. The obtained results indicated that fiber orientation has a greater effect on the deformation of the rotor blades and the minimum value can be achieved by the same barb angle inspired from the flight feather. In addition to a significant effect in the weight reduction of 80% was obtained by using composite rotor blades instead of stainless steel rotor blades.
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42

Marchevsky, Ilia K., and Valeria V. Puzikova. "Numerical Simulation of Wind Turbine Rotors Autorotation by Using the Modified LS-STAG Immersed Boundary Method." International Journal of Rotating Machinery 2017 (2017): 1–7. http://dx.doi.org/10.1155/2017/6418108.

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A software package is developed for numerical simulation of wind turbine rotors autorotation by using the modified LS-STAG level-set/cut-cell immersed boundary method. The level-set function is used for immersed boundaries description. Algorithm of level-set function construction for complex-shaped airfoils, based on Bézier curves usage, is proposed. Also, algorithm for the level-set function recalculation at any time without reconstructing the Bézier curve for each new rotor position is described. The designed second-order Butterworth low-pass filter for aerodynamic torque filtration for simulations using coarse grids is presented. To verify the modified LS-STAG method, the flow past autorotating Savonius rotor with two blades was simulated at Re=1.96·105.
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43

Долгих, Вячеслав Сергеевич. "ОПТИМІЗАЦІЯ НОСОВОЇ ЧАСТИНИ ФЮЗЕЛЯЖУ З ТОЧКИ ЗОРУ АЕРОДИНАМІКИ ЛІТАКА." Open Information and Computer Integrated Technologies, no. 86 (February 14, 2020): 127–38. http://dx.doi.org/10.32620/oikit.2019.86.09.

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The paper represents the analysis intended to optimize the fuselage nose section with regard to aircraft aerodynamics in the process of development of an unmanned transport aircraft (UTA). The article deals with provisions of high aerodynamic efficiency that cannot be achieved without proper selection of the shape and optimal fuselage parameters that determine mutual interference of aircraft components and units. When analyzing the flow improvement around the fuselage nose in flight, three fuselage versions were considered listed further: 1) a prototype for testing automatic flight control systems with participation of pilots; 2) a nose symmetrical relative to the fuselage rocket type cylinder axis; 3) a supposedly optimal variant based on the results of previous calculations. The aerodynamic characteristics of 3D fuselage models for positive integer Reynolds numbers (full-scale model) were calculated using the ANSYS software package. Three computational grids were built for these models in ANSYS ICEM CFD. The given version of the fuselage nose section intended for testing automatic flight control systems with participation of pilots initially has the greatest resistance among the considered variants. That is, first variant of the fuselage nose gives substantial braking zone as well as significant flow acceleration zone exists in place where fuselage is transformed into cylindrical part. The variant with the nose section symmetrical relative to the rocket type cylinder axis has smaller braking zone and less dispersed flow in place where fuselage is transformed into cylindrical part and, therefore, it has lower resistance in comparison with the first version. The fuselage execution developed on the basis of the results of previous calculations, despite the extensive acceleration zone at the junction of the nose to the cylindrical part, has shown the least resistance, respectively, and is the best of the considered variants. This is also confirmed by a comparison of streamlines over the nose surface. The streamlines are given for calculations at angle of attack of 8°; at this angle of attack, the difference in the coefficient Cx is clearly visible.
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Ambaw, A., M. Mukama, and U. L. Opara. "Computational fluid dynamics (CFD) based analysis of the aerodynamic and thermodynamic performances of package designs during cooling of stacked pomegranates." Acta Horticulturae, no. 1201 (April 2018): 205–12. http://dx.doi.org/10.17660/actahortic.2018.1201.28.

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45

Ferrier, L., M. Vezza, and H. Zare-Behtash. "Improving the aerodynamic performance of a cycloidal rotor through active compliant morphing." Aeronautical Journal 121, no. 1241 (May 11, 2017): 901–15. http://dx.doi.org/10.1017/aer.2017.34.

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ABSTRACTCycloidal rotors are a novel form of propulsion system that can be adapted to various forms of transport such as air and marine vehicles, with a geometrical design differing significantly from the conventional screw propeller. Research on cycloidal rotor design began in the early 1930s and has developed throughout the years to the point where such devices now operate as propulsion systems for various aerospace applications such as micro air vehicles, unmanned air vehicles and compound helicopters. The majority of research conducted on the cycloidal rotor’s aerodynamic performance have not assessed mitigating the dynamic stall effect, which can have a negative impact on the rotor performance when the blades operate in the rotor retreating side. A solution has been proposed to mitigate the dynamic stall effect through employment of active, compliant leading-edge morphing. A review of the current state of the art in this area is presented. A two-dimensional, implicit unsteady numerical analysis was conducted using the commercial computational fluid dynamics software package STAR CCM+, on a two-bladed cycloidal rotor. An overset mesh technique, otherwise known as a chimera mesh, was used to apply complex transient motions to the simulations. Active, compliant leading-edge morphing is applied to an oscillating NACA 0015 aerofoil to attempt to mitigate the dynamic stall whilst maintaining the positive dynamic lift coefficient (Cl) contributions. It was verified that by applying a pulsed input leading-edge rotational morphing schedule, the leading-edge vortex does not fully form and the large flow separation is prevented. Further work in this investigation will focus on coupling the active, leading-edge motion to the cycloidal rotor model with the aim to maximise aerodynamic performance.
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46

Seyednia, Mahbod, Mehran Masdari, and Shidvash Vakilipour. "Numerical assessment of a deformable trailing-edge flap on aerodynamic load control of a pitching S809 airfoil using OpenFOAM." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 233, no. 7 (April 2019): 890–900. http://dx.doi.org/10.1177/0957650919838142.

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Due to the unsteady nature of the flow around horizontal-axis wind turbines, the blades are subjected to severe unsteady and fatigue loads. This necessitates an in-depth aerodynamic analysis of flow control techniques to enhance the performance of a wind turbine as well as the lifetime of its components. Using OpenFOAM package in this study, a series of two-dimensional incompressible simulations are performed to present a deeper insight into the aerodynamic characteristics of an oscillating deformable trailing-edge flap, as a promising flow control device, in a sinusoidal pitching motion of an S809 airfoil. Herein, it is of particular interest to investigate the effects of deformable trailing-edge flap size, oscillation frequency, and the phase shift with reference to airfoil motion on lift and drag hysteresis loops. For this purpose, a pure-pitching motion of an S809 airfoil without flap deflection is considered as the benchmark problem in which the airfoil oscillates in the near-stall region at [Formula: see text]. After validation and verification of our simulations through comparison against the corresponding experimental and numerical work, a comprehensive investigation is conducted to study the effects of the aforementioned parameters on the aerodynamic loads. Our results reveal the fact that an out-of-phase deflection of the deformable trailing-edge flap with a frequency equal to the airfoil frequency can significantly mitigate the fatigue load. Under these circumstances, an increase in the deformable trailing-edge flap size can also help the airfoil experience less-severe loads in a cycle of motion. Furthermore, higher values of deformable trailing-edge flap frequency or other values of phase shift except the out-of-phase oscillation cannot alleviate fatigue loads. An airfoil under these conditions can, however, enhance the resultant load required for a blade rotation in the case of low wind periods.
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47

RIMSHIN, V. I., P. S. TRUNTOV, E. S. KETSKO, and I. S. KUZINA. "METHOD OF DETERMINING WIND LOADS AND IMPACTS USING THE SOFTWARE." Building and reconstruction 92, no. 6 (2020): 43–50. http://dx.doi.org/10.33979/2073-7416-2020-92-6-43-50.

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The current study considers a multifunctional high security residential complex. The study was conducted as part of the scientific and technical support for the design of the construction project. The compliance of design and survey documentation with the established requirements is usually a result of scientific and technical support of design. The methodology of determining wind loans and impacts is implemented with the help of a software package named SOFiSTiK. This software is capable of performing computations of stationary and non-stationary wind loans. Aerodynamic coefficients of drag and lateral force, as well as average pressure values were found as a result of applying the methodology in question. Also, patterns of medium pressure propagation on the surface of facade systems and patterns of medium-velocity fields of the complex were determined.
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48

Sayyed, Shoeb R., B. B. Singh, and Nasreen Bano. "Radiative MHD Stagnation-Point Flow with Heat Transfer Past a Permeable Stretching/Shrinking Sheet in a Porous Medium." Diffusion Foundations 11 (August 2017): 110–28. http://dx.doi.org/10.4028/www.scientific.net/df.11.110.

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In the present study, an analytical analysis has been carried out to investigate the MHD stagnation-point flow and heat transfer past a permeable stretching/shrinking sheet in a porous medium in the presence of thermal radiation. Similarity transformations have been employed to simplify the momentum and energy equations into coupled nonlinear ordinary differential equations. The resulting nonlinear ordinary differential equations are then solved analytically through BVPh 2.0 Mathematica package based on homotopy analysis method (HAM). Effects of various parameters such as Prandtl number, permeability parameter, magnetic parameter, suction/blowing parameter, stretching/shrinking parameter, radiation parameter and wall temperature exponent on velocity and/or temperature profiles are explored and discussed graphically. Our results have been compared with the available literature and have been found in excellent agreement. This study may have applications in metallurgy industry and aerodynamic extrusion of plastic sheet.
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49

Davies, Mark R. D., Reena Cole, and John Lohan. "Factors Affecting the Operational Thermal Resistance of Electronic Components." Journal of Electronic Packaging 122, no. 3 (November 15, 1999): 185–91. http://dx.doi.org/10.1115/1.1286101.

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The thermal resistance of electronic components is known to often differ considerably between standard test conditions and those found in service. One way to correct for this is to use multi-parameter thermal resistances. Another, presented here, is to adjust the junction-to-ambient thermal resistance to account for operational conditions. For forced convection applications, two factors are proposed; the first accounts for any upstream aerodynamic disturbance and the second addresses purely thermal interaction. Thus if an upstream powered component interacts with a downstream component, the two factors are combined. It is shown that both factors may be quantified in terms of readily measured temperatures and then used as coefficients to adjust the standard thermal resistance data for operational conditions. To overcome the misconception that the currently published single-value thermal resistances are solely a property of the electronic package, thermal resistance is redefined to include both the resistance of the package and the part of the printed circuit board (PCB) covered by the component thermal footprint. This approach is applied to a symmetrical array of board mounted 160-lead devices and data showing how the factors vary with component position, nondimensional power distribution and Reynolds number is presented. Based on data a new method of generating operational component thermal resistances is proposed. [S1043-7398(00)00603-4]
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50

Dorogi, Dániel, Betti Bolló, and Szilárd Szabó. "Effects of external disturbances on the performance of an axial cooling fan." Analecta Technica Szegedinensia 13, no. 1 (June 25, 2019): 48–55. http://dx.doi.org/10.14232/analecta.2019.1.48-55.

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In this study flow around an axial flow fan is investigated by the means of CFD computations using the commercial software package, ANSYS Fluent. The rotation speed of the impeller was set to the constant value of n = 2500min-1. The results obtained from the computation are validated against those from measurements; good agreements can be seen. The effects of two different external disturbances are analysed. First, the fan was place into a uniform stream where the free stream velocity is varied between U = 0 and 100 km/h. After that, a computation is carried out for U = 0 km/h where the half of the suction side of the fan was covered by a flat plate. The results showed that the fluid pressure and the aerodynamic force increases with the free stream velocity. Asymmetric pressure and fluid force distribution was identified when suction side of the fan was partially covered.
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