Journal articles: 'Aerodynamic calculation'

1

Дмитрій Миколайович Зінченко, Г. Ортамевзи, and А. Рахмати. "THE CALCULATION AERODYNAMIC CHARACTERISTICS OF A HYBRID AEROSTATIC AIRCRAFT." MECHANICS OF GYROSCOPIC SYSTEMS, no. 27 (October 6, 2014): 102–11. http://dx.doi.org/10.20535/0203-377127201438208.

Full text

Abstract:

The article presents a justification layout a new type aircraft with two different sources lifting force – aerodynamic and aerostatic. Consider especially the exploitation aircraft easier to air, identified key issues research, unresolved tasks, formulated the task. Logged matching aerodynamic profile for bearing surface hybrid aircraft, made its adaptation. Using the method of computational aerodynamics the calculation of the flow around the bearing surface, presents an analysis of the results and conclusions and recommendations are given on an aerodynamic design.

APA, Harvard, Vancouver, ISO, and other styles

2

Wang, Jianfeng, Hao Li, Yiqun Liu, Tao Liu, and Haibo Gao. "Aerodynamic research of a racing car based on wind tunnel test and computational fluid dynamics." MATEC Web of Conferences 153 (2018): 04011. http://dx.doi.org/10.1051/matecconf/201815304011.

Full text

Abstract:

Wind tunnel test and computational fluid dynamics (CFD) simulation are two main methods for the study of automotive aerodynamics. CFD simulation software solves the results in calculation by using the basic theory of aerodynamic. Calculation will inevitably lead to bias, and the wind tunnel test can effectively simulate the real driving condition, which is the most effective aerodynamics research method. This paper researches the aerodynamic characteristics of the wing of a racing car. Aerodynamic model of a racing car is established. Wind tunnel test is carried out and compared with the simulation results of computational fluid dynamics. The deviation of the two methods is small, and the accuracy of computational fluid dynamics simulation is verified. By means of CFD software simulation, the coefficients of six aerodynamic forces are fitted and the aerodynamic equations are obtained. Finally, the aerodynamic forces and torques of the racing car travel in bend are calculated.

APA, Harvard, Vancouver, ISO, and other styles

3

Ovchinnicov, V. V., and Yu V. Petrov. "THE AERODYNAMIC CHRACTERISTICS CALCULATION METHODOLOGY OF TWO-SHELL PARAGLIDERS." Civil Aviation High TECHNOLOGIES 21, no. 3 (July 3, 2018): 91–100. http://dx.doi.org/10.26467/2079-0619-2018-21-3-91-100.

Full text

Abstract:

Currently, two-shell paragliders (TSP) find a sufficiently wide application, including the solution of transport problems. A two-shell paraglider is a soft wing, the form of which is supported by the high-speed pressure in the stream and it is a complex aeroelastic system. To determine the aerodynamic characteristics of such system the use of nonlinear aerodynamics and nonlinear theory of elasticity methods is required, it causes the significant computational difficulties. This paper studies the aerodynamic characteristics of various steady-state shapes of gliding parachutes, the calculation-experimental method of their calculation is proposed. It is shown that the replacement of the volumetric profile of TSP median surface allows to receive the results which correctly reflect the qualitative effects of stalled and attached flows. It leads to the assumption that such replacement was possible for obtaining data about the main patterns of parachute finite wings span flow. The aerodynamic characteristics data of TSP steady-state shapes allow to identify the regularities of their changes depending on parachute cutting shape, the deformations of its surface caused by the incoming flow or control actions. To solve the problem of gliding parachute stall, with a stream of air, the discrete vortex method with closed frameworks is used. This method allows to calculate the aerodynamic characteristics of parachutes. The middle surface airflow of TSP steady-state shape with the flow of an ideal incompressible fluid is examined. The parachute fabric permeability is not considered because the upper and lower TSP cloth is either made of low permeable or impermeable fabric. The stalled aerodynamic coefficients are determined by time averaging after calculations up to its larger values. The results of the calculations are given. The possibility of application the proposed methodology for calculation of TSP aerodynamic characteristics in the range of angles of attack to 10° and over 20° for the simplified calculation scheme with accuracy 10% is shown. At the same time, it is revealed that with the increase of soft wing elongation, it is important to consider its main surface curvature for more precise aerodynamic characteristics definition. The proposed methodology can be used for rapid assessments of aerodynamic forces at the design stage and in planning tube experiment. The obtained results can be useful in TSP design during the performance of the tube experiments.

APA, Harvard, Vancouver, ISO, and other styles

4

Bondarenko, Oleksandr, and Anton Smagliy. "Software complex for aircraft characteristics calculation." MECHANICS OF GYROSCOPIC SYSTEMS, no. 40 (December 26, 2021): 93–100. http://dx.doi.org/10.20535/0203-3771402020249156.

Full text

Abstract:

The article describes the method of calculating the aerodynamic loads of the aircraft, which can be programmed within the graphic user interface. The method uses statistical data of typical aerodynamic profiles flow in wind tunnels and mathematical expressions that describe the known laws of aerohydromechanics. The graphic user interface is tested by a model of the famous Ukrainian aircraft A32 that manufactured by Aeropract company. A surface model of the aircraft for modeling consists of the theoretical surface for the wing and the fuselage. A comparison of the formula’s calculation in the graphical interface and finite element calculations is given. The software interface is built in C #.

APA, Harvard, Vancouver, ISO, and other styles

5

Yu, Jing Mei, Yan Hong Yu, and Pan Pan Liu. "Horizontal Axis Wind Turbine Numerical Simulation of Two Dimensional Angle of Attack." Advanced Materials Research 619 (December 2012): 111–14. http://dx.doi.org/10.4028/www.scientific.net/amr.619.111.

Full text

Abstract:

wind power is the most effective form of wind energy utilization, modern large-scale wind turbine with horizontal axis wind mainly. Horizontal axis wind turbine aerodynamic performance calculation of the wind turbine aerodynamics research hot spot, is a wind turbine aerodynamic optimization design and calculation of critical load. Horizontal axis wind turbine airfoil aerodynamic performance of the wind turbine operation characteristics and life plays a decisive role". Using Fluent software on the horizontal axis wind turbine numerical simulation, analysis of the United States of America S809NREL airfoil aerodynamic characteristics of different angles of attack numerical simulation, analyzes the different angles of attack in the vicinity of the pressure, velocity distribution. By solving the two-dimensional unsteady, compressible N-S equations for the calculation of wind turbine airfoil S809used the characteristics of flow around. N-S equation in body-fitted coordinate system is given, with the Poisson equation method to generate the C grid.

APA, Harvard, Vancouver, ISO, and other styles

6

Shen, Kai, Hong Chen, Shi Fan Gu, and Ji Min Ni. "Research on Calculation Method of Engine Cooling Fan." Advanced Materials Research 732-733 (August 2013): 495–500. http://dx.doi.org/10.4028/www.scientific.net/amr.732-733.495.

Full text

Abstract:

It’s introduced the method of calculation, modeling techniques and solution techniques of the aerodynamic performance of engine cooling fan. Based on a fan-tunnel test, the relation between static pressure, power, efficiency with volume flow is calculated in Fluent. It is proposed a few improved models and compared the calculations of different models. It’s analyzed the problems and reasons in the calculations of models and proposed the improved methods in fan test and numerical calculation. Keywords:Cooling Fan, Aerodynamic Performance, Models

APA, Harvard, Vancouver, ISO, and other styles

7

Figat, Marcin, Tomasz Goetzendorf‐Grabowski, and Zdobysław Goraj. "Aerodynamic calculation of unmanned aircraft." Aircraft Engineering and Aerospace Technology 77, no. 6 (December 2005): 467–74. http://dx.doi.org/10.1108/00022660510628453.

Full text

APA, Harvard, Vancouver, ISO, and other styles

8

Luchkov, Andrey N., Evgeny V. Zhuravlev, and Egor Y. Cheban. "METHOD OF CALCULATING THE LIFT COEFFICIENT FOR A WIG’S COMPOUND WING FLYING CLOSE TO THE GROUND." Russian Journal of Water Transport, no. 62 (March 6, 2020): 51–61. http://dx.doi.org/10.37890/jwt.vi62.39.

Full text

Abstract:

In the design and characteristics justification of WIG crafts, determination of optimal aerodynamic and moment coefficients and their ratio is still one of the most important problems. Values and ratios of these coefficients provide not only technical tasks performance, but also safe operation of a WIG craft within the framework of AP standards and rules of water transport operation. The paper is devoted to the method of calculating the Cy lift coefficient for the complex compound wing with washers by using the superposition method and verification of calculated data with experimental values. The study was based on TsAGI-876 wing profile characteristics at various relative flight heights.Calculation of the aerodynamic Cy coefficient is performed in several stages:1. Calculation of the aerodynamic Cy coefficient for the center section;2. Calculation of aerodynamic Cy coefficient for the console section;3. Calculation of the total Cy coefficient by using the superposition method.The proposed method of calculation provides an accuracy of up to 93%, which can be considered a satisfactory result for preliminary design of types «B» and «C» WIG crafts.

APA, Harvard, Vancouver, ISO, and other styles

9

Guan, Xin, Hua Dong Wang, Zhi Li Sun, Xiao Guo Bi, and Xu Dong Liu. "Variation of Aerodynamic Load Engineering Analysis during Wind Turbine Run." Applied Mechanics and Materials 291-294 (February 2013): 501–6. http://dx.doi.org/10.4028/www.scientific.net/amm.291-294.501.

Full text

Abstract:

In order to improve design reliability of wind turbine, it is needed that calculating method of aerodynamic load during wind turbine run. In paper from the angle of the project, NACA special airfoil of wind turbine is analyzed. Combined with thin-theory, airfoil angle of attack variation is deduced, meanwhile wind turbine actual force is calculated in each blade location point when blade of wind turbine is running based on wind shear theory and tower shadow effect. According to actual condition calculation method is engineering amplified, aerodynamic load calculation method of wind turbine blade is obtained. By this method aerodynamic load which is calculated match with experiment result, it fits better.

APA, Harvard, Vancouver, ISO, and other styles

10

Abuzov, Aleksandr, Igor' Grigor'ev, and Yaroslav Abuzov. "TO THE QUESTION OF AERODYNAMICS HULLS TRANSPORT AND CARGO AIRSHIPS DESIGNED FOR THE FOREST COMPLEX." Forestry Engineering Journal 12, no. 1 (April 15, 2022): 68–81. http://dx.doi.org/10.34220/issn.2222-7962/2022.1/6.

Full text

Abstract:

The article touches upon topical issues related to the transport development of forest areas with the help of aircraft, namely aerostatic ones. An assessment of their capabilities and advantages over other modes of transport is given. Examples and technical characteristics of the developed and created experimental samples of hybrid transport-cargo airships, which were intended for operation in the forest complex, are given. The key issue that the authors consider in this article is the aerodynamics of the airship hull, which has a major impact on the movement and maneuverability of the airship in the process of carrying out transport and cargo operations. A simplified method for calculating the flow around the body of an aerostatic aircraft, which depends on the geometric parameters of the body, is presented. The main stages of calculations of aerodynamic parameters are determined, including the transverse and longitudinal flow around the hull, the movement of the aircraft with the angle of attack and the influence of aerodynamic pressure. Attention is paid to the inertial properties of the environment and, as a result, to the method of calculation when moving with acceleration, where the airship is represented by a body of revolution, which is influenced by the attached mass. The presented article is a series of scientific works of the authors aimed at studying the technical parameters of aerostatic aircraft, including aerodynamic performance

APA, Harvard, Vancouver, ISO, and other styles

11

Galyuzhin, Aleksandr Sergeyevich. "AERODYNAMIC CALCULATION OF CENTRIFUGAL MAGNETIC DEHUMIDIFIERS." Вестник Белорусско-Российского университета, no. 1 (2015): 5–14. http://dx.doi.org/10.53078/20778481_2015_1_5.

Full text

APA, Harvard, Vancouver, ISO, and other styles

12

Mitchell, Samuel, Iheanyichukwu Ogbonna, and Konstantin Volkov. "Aerodynamic Characteristics of a Single Airfoil for Vertical Axis Wind Turbine Blades and Performance Prediction of Wind Turbines." Fluids 6, no. 7 (July 13, 2021): 257. http://dx.doi.org/10.3390/fluids6070257.

Full text

Abstract:

The design of wind turbines requires a deep insight into their complex aerodynamics, such as dynamic stall of a single airfoil and flow vortices. The calculation of the aerodynamic forces on the wind turbine blade at different angles of attack (AOAs) is a fundamental task in the design of the blades. The accurate and efficient calculation of aerodynamic forces (lift and drag) and the prediction of stall of an airfoil are challenging tasks. Computational fluid dynamics (CFD) is able to provide a better understanding of complex flows induced by the rotation of wind turbine blades. A numerical simulation is carried out to determine the aerodynamic characteristics of a single airfoil in a wide range of conditions. Reynolds-averaged Navier–Stokes (RANS) equations and large-eddy simulation (LES) results of flow over a single NACA0012 airfoil are presented in a wide range of AOAs from low lift through stall. Due to the symmetrical nature of airfoils, and also to reduce computational cost, the RANS simulation is performed in the 2D domain. However, the 3D domain is used for the LES calculations with periodical boundary conditions in the spanwise direction. The results obtained are verified and validated against experimental and computational data from previous works. The comparisons of LES and RANS results demonstrate that the RANS model considerably overpredicts the lift and drag of the airfoil at post-stall AOAs because the RANS model is not able to reproduce vorticity diffusion and the formation of the vortex. LES calculations offer good agreement with the experimental measurements.

APA, Harvard, Vancouver, ISO, and other styles

13

Marques, Alexandre Noll, and João Luiz F. Azevedo. "Numerical Calculation of Impulsive and Indicial Aerodynamic Responses Using Computational Aerodynamics Techniques." Journal of Aircraft 45, no. 4 (July 2008): 1112–35. http://dx.doi.org/10.2514/1.32151.

Full text

APA, Harvard, Vancouver, ISO, and other styles

14

Pavlov, Stanislav. "ESTIMATION OF AMOUNT CHANGING OF LOCAL AERODYNAMIC RESISTANCE OF ELEMENTS OF VENTILATION SYSTEM OF MINE AT REVERSING BEHAVIOR OF VENTILATION SYSTEM." Interexpo GEO-Siberia 2, no. 4 (2019): 212–19. http://dx.doi.org/10.33764/2618-981x-2019-2-4-212-219.

Full text

Abstract:

In the work study results of influence of typical working junction angle on amount changing of local aerodynamic resistances when air flows in different directions is represented. Using finite-element software, aerodynamic parameters of elements of mine ventilation network is obtained and is compared with analytical calculations Interinfluence local aerodynamic resistances located at ventilation network consecutively in normal and reversing behavior is discovered. It allows to increase accuracy of calculation of mine ventilation network at emergency ventilation operation.

APA, Harvard, Vancouver, ISO, and other styles

15

Samsonov, Vladimir. "Calculation of aerodynamic characteristics of adjacent buildings." Construction and Architecture 8, no. 1 (February 4, 2020): 67–81. http://dx.doi.org/10.29039/2308-0191-2020-8-1-67-81.

Full text

Abstract:

The article describes the basic formulas for determination of the aerodynamic characteristics of the industrial buildings and their complexes: the size of the circulation zones, the aerodynamic coefficients and the velocity profiles of the wind.

APA, Harvard, Vancouver, ISO, and other styles

16

Konoplev, M., D. Onokhin, A. Zagoskin, and S. Karpov. "Aerodynamics and convective heat transfer processes in cyclone chambers with external recirculation of gases." Journal of Physics: Conference Series 2088, no. 1 (November 1, 2021): 012021. http://dx.doi.org/10.1088/1742-6596/2088/1/012021.

Full text

Abstract:

Abstract The paper presents the results of an experimental and theoretical calculation study of aerodynamics and convective heat transfer on the side surface of cyclone recirculation furnace devices. The possibility of controlling the main aerodynamic characteristics without changing the geometric parameters of the cyclone devices by organizing external gas recirculation is shown.

APA, Harvard, Vancouver, ISO, and other styles

17

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

18

Yue, Chun Guo, Xin Long Chang, You Hong Zhang, and Shu Jun Yang. "Numerical Calculation of a Missile's Aerodynamic Characteristic." Advanced Materials Research 186 (January 2011): 220–24. http://dx.doi.org/10.4028/www.scientific.net/amr.186.220.

Full text

Abstract:

In virtue of Fluent of CFD software, numerical computations of aerodynamics of an air-to-air missile in different mach numbers and different attack angles were carried though. The movement trends of lift coefficient, drag coefficient and pitching moment coefficient with variety of mach numbers and attack angles were gained, meanwhile, distributing trends of pressure, temperature and weather velocity were also obtained. The results indicated that the basis and references could be offered by numerical computation results for shape design of missile and definite preponderances were showed than traditionary numerical computation methods.

APA, Harvard, Vancouver, ISO, and other styles

19

Roggero, F., and R. Larguier. "Aerodynamic calculation of complex three-dimensional configurations." Journal of Aircraft 30, no. 5 (September 1993): 561–70. http://dx.doi.org/10.2514/3.46383.

Full text

APA, Harvard, Vancouver, ISO, and other styles

20

Brodsky, Sergey A., Alexander V. Nebylov, and Alexander I. Panferov. "The WIG-craft Aerodynamic Model Parameters Calculation." IFAC-PapersOnLine 52, no. 12 (2019): 256–61. http://dx.doi.org/10.1016/j.ifacol.2019.11.252.

Full text

APA, Harvard, Vancouver, ISO, and other styles

21

Liu, Q., D. Qi, and Y. Mao. "Numerical calculation of centrifugal fan noise." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 220, no. 8 (August 1, 2006): 1167–77. http://dx.doi.org/10.1243/09544062jmes211.

Full text

Abstract:

A numerical study on the aerodynamic noise generation of an industrial centrifugal fan with forward swept blades is carried out. Three-dimensional numerical simulations of the complete unsteady flowfield in the whole impeller — volute configuration are performed to obtain the aerodynamic sound sources. Then, aerodynamic sound is calculated using the Lowson equation and compared with the measurements. Moreover, the fan is modified for noise reduction by increasing the distance between the impeller tip and the volute tongue and sloping the volute tongue. The sound levels of the modified fan are lower than those of the original one over almost the entire range of frequencies analysed. The blade passing frequency level of the modified fan is decreased by about 15 dB at the design point. The method described and applied in this work provides a good qualitative prediction of the noise generation when designing a new fan, thus facilitating the choice of the lowest noise fan from several feasible alternatives.

APA, Harvard, Vancouver, ISO, and other styles

22

Erofeev, V. I., and I. A. Samokhvalov. "EVALUATION OF THE VITALITY OF A FLANGED CONNECTION WITH A STEEL TOWER STRUCTURE WITH ACCOUNT OF EXPERIMENTAL DETERMINATION OF AERODYNAMIC COEFFICIENTS." Problems of strenght and plasticity 82, no. 2 (2020): 215–24. http://dx.doi.org/10.32326/1814-9146-2020-82-2-215-224.

Full text

Abstract:

A numerical study of the survivability of the flange assembly is carried out upon reaching a critical load and in the presence of a defect in one of the design areas, taking into account the calculated values of the aerodynamic coefficients. An experiment is being carried out to determine the values of the wind load acting on the supporting legs of a metal tower. The calculation of the stressstrain state is performed using software system as SCAD Office and IDEA StatiCa 10.0. After calculating the forces in the core model of the structure, a threedimensional plate model of the assembly is formed and prepared for calculation. According to the results of the experiment, a graph was compiled with the values of aerodynamic coefficients, which were used in calculating the stressstrain state of the node. The analysis of the calculation results revealed that in the design (defectfree) state of the structure, the safety factor of the bearing units and elements is 35-40% (equivalent stresses were 165 MPa). If there is a defect in the metal structures of the belt in the region of the flange, the equivalent stresses increase to 247.6 MPa in the region of the cleavage (defective hole), thus, the margin in bearing capacity drops to 0.4%. As a result of the assessment of the survivability of the flange connection, it was revealed that the connection has a high potential survivability, in turn, the flange itself is able to work in the presence of some defects without reducing its bearing capacity to a critical level. The aerodynamic coefficients obtained in this work will determine the wind load on this type of profile and can be used in design calculations of tower structures for wind loads.

APA, Harvard, Vancouver, ISO, and other styles

23

Zhang, Yao Ping. "Explicit Formula for Estimating Aerodynamic Drag on Trains Running in Evacuated Tube Transportation." Applied Mechanics and Materials 307 (February 2013): 156–60. http://dx.doi.org/10.4028/www.scientific.net/amm.307.156.

Full text

Abstract:

Because of reducing aerodynamic drag, the maglev train could run at a high-speed in the partial vacuum tube. Scientists of some conutries such as U.S., Swiss and China, have started the research work on high-speed tube trains. In this situation, evacuated tube transportation aerodynamics becomes an important theory research aspect, in which the main study content is how to calculate aerodynamic drag. Based on the explicit formula for estimating aerodynamic drag on moving body in an infinite boundary surroundings put up by Isaac Newton, the evacuated tube surroundings is analyzed and the explicit formula with blockage ratio as an independent variable for estimating aerodynamic drag acted on trains running in the evacuated tube which is a finite space is deduced. With the calculation case, compared with the results came out from the explicit formula got in this paper and the results got by Fluent software, it was found that those results are closed. Thus, the explicit formula created in this paper for conveniently estimating aerodynamic drag based on trains running in evacuated tube transportation is credible.

APA, Harvard, Vancouver, ISO, and other styles

24

MINKINA, Svetlana A., and Maxim I. URYADOV. "RECONSTRUCTION OF GAS DUCTS OF WATER BOILERS WITH INSTALLATION OF FLUE GAS PUMPS." Urban construction and architecture 10, no. 4 (March 5, 2021): 42–49. http://dx.doi.org/10.17673/vestnik.2020.04.6.

Full text

Abstract:

The work is devoted to solving the problem of the lack of draft of the existing chimney when operating hot water boilers at full capacity. Thermal and aerodynamic calculations were performed. Thermal calculation was carried out with diff erent loading of hot water boilers and the number of operating burners. The options for the operation of boilers according to the regime map and test protocols are considered. In the aerodynamic calculation for the sections, the resistance of the gas ducts was determined, the chimney was calculated. A fl ue gas pump is installed to remove combustion products from hot water boilers. This will ensure the parallel operation of two hot water boilers over the entire load range.

APA, Harvard, Vancouver, ISO, and other styles

25

Sychugov, N. P. "Specific speed and overall dimensions in calculation and selection of transverse fans." Traktory i sel hozmashiny 83, no. 5 (May 15, 2016): 27–33. http://dx.doi.org/10.17816/0321-4443-66193.

Full text

Abstract:

When calculating, designing and selecting the fans, along with the similarity theory and dimensional analysis, the criteria of specific speed and overall dimensions are used, which allow to study a great number of aerodynamic configurations and characteristics of highly efficient fan prototypes and at the same time to choose the configuration which meets technical requirements most completely. The criteria of specific speed and overall dimensions are properly elaborated and used when designing and calculating radial and axial fans, but not suitable for the transverse fans, because in their flowing part the air flow is not three-dimensional but two-dimensional, and consequently there is an additional independent parameter in calculation, namely the usable width. Based on the main correlations of transverse fans’ parameters (the propeller diameter and its rotation frequency, the usable width of flowing part) and moving air density, dimensionless and dimensional criteria of specific speed and overall dimensions for these air flow generators are derived. On the basis of theoretical and experimental studies, the cause-and-effect laws allowing to determine the criteria of specific speed and overall dimensions for transverse fans are revealed. Graphical interpretation of rational values areas of these criteria is shown, and calculations are performed. According to the known values of criteria of specific speed and overall dimensions, the examples of calculations for transverse fans using the dimensionless aerodynamic configurations and characteristics of highly efficient fan prototypes are given. The calculations are supplied with graphical interpretation.

APA, Harvard, Vancouver, ISO, and other styles

26

Solovyov, Oleg, Sergey Yeryomenko, Vitaliy Kobrin, and Yuriy Vorobyov. "Dipole Approximation in the Calculation of the Perturbed Velocities." Transport and Telecommunication Journal 15, no. 4 (December 19, 2014): 308–14. http://dx.doi.org/10.2478/ttj-2014-0027.

Full text

Abstract:

Abstract In this article we consider one of the approaches aimed at reducing time of calculation of aerodynamic characteristics of the studied objects using discrete vortex method. Also, accuracy assessment of calculation of aerodynamic characteristics was performed. Analysis of the obtained dependences allows us to make a conclusion that the considered approach to the calculation of the functions of the mutual influence on the stages of formation of the system of linear algebraic equations, position of vortex sheet nodes as well as aerodynamic loads reduces hardware costs about three times, with a relative error of less than 4%.

APA, Harvard, Vancouver, ISO, and other styles

27

He, Pan, and Jian Xia. "Study on the Influence of Low-Level Jet on the Aerodynamic Characteristics of Horizontal Axis Wind Turbine Rotor Based on the Aerodynamics–Controller Interaction Method." Energies 15, no. 8 (April 7, 2022): 2709. http://dx.doi.org/10.3390/en15082709.

Full text

Abstract:

Accurate prediction of the aerodynamic characteristics of wind rotors subjected to various wind profiles is of considerable importance in the aerodynamics and structural design of wind turbines. As a very complex atmospheric phenomenon, the impact of a low-level jet (LLJ) on the aerodynamic characteristics of wind rotors is becoming more and more significant with the increase in wind turbine height. Additionally, during calculating the aerodynamic characteristics of the wind rotor, the known wind speed, rotor speed, and blade-pitch angle are generally required. However, when the wind profile is in the LLJ condition, it is difficult to determine the blade-pitch angle and rotor speed. Therefore, in this paper, the blade-element-momentum (BEM) method is exploited by considering the coupling with the generator-torque controller and blade-pitch controller. In order to solve the problem of the unknown rotor speed and blade-pitch angle under the LLJ condition, a C++ code is developed. Then, the influence of the LLJ on the aerodynamic characteristics of the wind rotor is exclusively examined. The research results show that the calculation method can precisely evaluate the rotor speed, blade-pitch angle, and aerodynamic characteristics of the wind rotor. The influence of the LLJ on the aerodynamic loads of the wind rotor is greater than that of the wind shear. When the LLJ is placed inside the rotor swept area, the aerodynamic loads of the blade exhibit two local maximums and local minimums with the variation of the azimuth angle in a rotation period. The closer the LLJ height is to the hub height, the greater the average aerodynamic loads of the wind rotor are, and the smaller the amplitude of aerodynamic loads of the blade is relative to the average value. When the LLJ height is positioned outside the rotor swept area, the change law of the aerodynamic loads of the blade would be similar to that of the wind subjected to a very strong wind shear inflow. This study provides a crucial reference for a more rational assessment of the aerodynamic characteristics of wind turbines under the action of complex wind profiles, as well as revealing the influence of the LLJ on the aerodynamic characteristics of wind turbines.

APA, Harvard, Vancouver, ISO, and other styles

28

Wang, Yu Shan, and Di Lin Pan. "Numerical Analysis of the Influence of Export Structure on Jet Fan Aerodynamics Performances." Applied Mechanics and Materials 713-715 (January 2015): 3–6. http://dx.doi.org/10.4028/www.scientific.net/amm.713-715.3.

Full text

Abstract:

The internal flow of jet fan has been simulated using FLUENT software.By changing the length of exit duct and the angle of the exit cowl,a series of numerical simulation research has been done.The calculation results show that the length of exit duct and structure of exit cowl has obvious influence on jet fan aerodynamics performances and reasonable export structure can effectively improve jet fan aerodynamic performances.

APA, Harvard, Vancouver, ISO, and other styles

29

Mikhailovskiy, K. V., and S. V. Baranovski. "Accounting for Icing in the Design Analysis of Polymer Composite Wings." Proceedings of Higher Educational Institutions. Маchine Building, no. 3 (708) (March 12, 2019): 61–70. http://dx.doi.org/10.18698/0536-1044-2019-3-61-70.

Full text

Abstract:

The aircraft aerodynamic characteristics are directly dependent on their geometry, in particular, on the wing airfoil. The airfoil can change significantly in-flight due to the growth of ice, which can impact effectiveness of the airfoil. Accounting for this phenomenon is a multidisciplinary task that requires an appropriate solution, making it relevant for design calculations. The process of obtaining an ice-covered surface of the aircraft using the performed calculation of the external aerodynamics problem is described in this paper. The shape and geometry, as well as the ice effect on the aerodynamic characteristics are examined. Various arrangements are considered, both for the aircraft as a whole and for the wing separately, with engine nacelle traditionally mounted on a pole under the wing. Several flight modes at different altitudes in clouds of non-uniform phase composition (water and mixed) with particles of different diameter are considered. This work is part of the compiled methods of designing a polymer composite wing using parametrical modeling at the design analysis stage.

APA, Harvard, Vancouver, ISO, and other styles

30

Zhang, Jing, Wenwen Kang, and Lingyu Yang. "Aerodynamic benefits of boundary layer ingestion for distributed propulsion configuration." Aircraft Engineering and Aerospace Technology 91, no. 10 (November 4, 2019): 1285–94. http://dx.doi.org/10.1108/aeat-06-2018-0174.

Full text

Abstract:

Purpose Boundary layer ingestion (BLI) is one of the probable noteworthy features of distributed propulsion configuration (DPC). Because of BLI, strong coupling effects are generated between the aerodynamics and propulsion system of aircraft, leading to the specific lift and drag aerodynamic characteristics. This paper aims to propose a model-based comprehensive analysis method to investigate this unique aerodynamic. Design/methodology/approach To investigate this unique aerodynamics, a model-based comprehensive analysis method is proposed. This method uses a detailed mathematical model of the distributed propulsion system to provide the essential boundary conditions and guarantee the accuracy of calculation results. Then a synthetic three-dimensional computational model is developed to analyze the effects of BLI on the lift and drag aerodynamic characteristics. Findings Subsequently, detailed computational analyses are conducted at different flight states, and the regularities under various flight altitudes and velocities are revealed. Computational results demonstrate that BLI can improve the lift to drag ratio evidently and enable a great performance potentiality. Practical implications The general analysis method and useful regularities have reference value to DPC aircraft and other similar aircrafts. Originality/value This paper proposed a DPS model-based comprehensive analysis method of BLI benefit on aerodynamics for DPC aircraft, and the unique aerodynamics of this new configuration under various flight altitudes and velocities was revealed.

APA, Harvard, Vancouver, ISO, and other styles

31

Zhang, Li Jun, Xiao Jiao Chen, Min Li, Yue Fan, and Qiang Fu. "Research on Numerical Calculation Method to Aerodynamic Noise in High Velocity Environment." Advanced Materials Research 655-657 (January 2013): 809–12. http://dx.doi.org/10.4028/www.scientific.net/amr.655-657.809.

Full text

Abstract:

At present, the flight velocity and flight performance of an aircraft are higher, so that aerodynamic noise caused by an engine jet in the take-off and flight processes can reach 160 dB. The high strength of the jet aerodynamic noise is very harmful to vehicle drivers, vehicle structures and airborne equipments. Two numerical calculation methods to aerodynamic noise, the FW-H acoustic analogy method and the FW-H acoustic analogy and boundary element combining method, were introduced. These two methods were used to predict the aerodynamic noise, and the numerical calculation results were compared with the physical experimental results. Results show that the FW-H acoustic analogy method can predict aerodynamic noise. However, it cannot predict the sound field distribution. The FW-H acoustic analogy and boundary element combining method is able to predict the sound field distribution with sound reflection.

APA, Harvard, Vancouver, ISO, and other styles

32

Wang, Linpeng, Yuting Dai, and Chao Yang. "Bifurcation Analysis with Aerodynamic-Structure Uncertainties by the Nonintrusive PCE Method." International Journal of Aerospace Engineering 2017 (2017): 1–17. http://dx.doi.org/10.1155/2017/2571253.

Full text

Abstract:

An aeroelastic model for airfoil with a third-order stiffness in both pitch and plunge degree of freedom (DOF) and the modified Leishman–Beddoes (LB) model were built and validated. The nonintrusive polynomial chaos expansion (PCE) based on tensor product is applied to quantify the uncertainty of aerodynamic and structure parameters on the aerodynamic force and aeroelastic behavior. The uncertain limit cycle oscillation (LCO) and bifurcation are simulated in the time domain with the stochastic PCE method. Bifurcation diagrams with uncertainties were quantified. The Monte Carlo simulation (MCS) is also applied for comparison. From the current work, it can be concluded that the nonintrusive polynomial chaos expansion can give an acceptable accuracy and have a much higher calculation efficiency than MCS. For aerodynamic model, uncertainties of aerodynamic parameters affect the aerodynamic force significantly at the stage from separation to stall at upstroke and at the stage from stall to reattach at return. For aeroelastic model, both uncertainties of aerodynamic parameters and structure parameters impact bifurcation position. Structure uncertainty of parameters is more sensitive for bifurcation. When the nonlinear stall flutter and bifurcation are concerned, more attention should be paid to the separation process of aerodynamics and parameters about pitch DOF in structure.

APA, Harvard, Vancouver, ISO, and other styles

33

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

34

Li, Xinkai, Ke Yang, Hao Hu, Xiaodong Wang, and Shun Kang. "Effect of Tailing-Edge Thickness on Aerodynamic Noise for Wind Turbine Airfoil." Energies 12, no. 2 (January 16, 2019): 270. http://dx.doi.org/10.3390/en12020270.

Full text

Abstract:

The influence of wind turbine airfoil trailing edge thickness on aerodynamics and aerodynamic noise characteristics was studied using the computational fluid dynamics (CFD)/ Ffowcs Williams–Hawkings (FW–H) method in the present work. First, the airfoil of a DU97-W-300-flatback airfoil was chosen as the research object, and numerical method validation was performed. Three kinds of turbulence calculation methods (unsteady Reynolds average Navier-Stokes (URANS), detached eddy simulation (DES), and large eddy simulation (LES)) were investigated in detail, and three sets of grid scales were used to study the impact of the airfoil on the aerodynamic noise. Secondly, the airfoil trailing edge thickness was changed, and the impact of trailing edge thickness on aerodynamics and aerodynamic noise was investigated. Results show that three kinds of turbulence calculation methods yield the same sound pressure frequency, and the magnitude of the sound pressure level (SPL) corresponding to the mean frequency is almost the same. The calculation of the SPL of the peak value and the experimental results can match well with each other, but the calculated core frequency is slightly lower than the experimental frequency. The results of URANS and DES are closer to each other with a changing trend of SPL, and the consequences of the DES calculation are closer to the experimental results. From the comparison of two airfoils, the blunt trailing edge (BTE) airfoil has higher lift and drag coefficients than the original airfoil. The basic frequency of lift coefficients of the BTE airfoil is less than that of the original airfoil. It is demonstrated that the trailing vortex shedding frequency of the original airfoil is higher than that of the BTE airfoil. At a small angle of attack (AOA), the distribution of SPL for the original airfoil exhibits low frequency characteristics, while, at high AOA, the wide frequency characteristic is presented. For the BTE airfoil, the distribution of SPL exhibits low frequency characteristics for the range of the AOA. The maximum AOA of SPL is 4° and the minimum AOA of SPL is 15°, while, for the original airfoil, the maximum AOA of SPL is 19°, and the minimum AOA is 8°. For most AOAs, the SPL of the BTE airfoil is larger than that of the original airfoil.

APA, Harvard, Vancouver, ISO, and other styles

35

Tarichko, V. I., and P. I. Shalupina. "Refinement of the characteristics of the aerodynamic resistance to the movement of special wheeled chassis and tractors based on the use of computational gas dynamics methods." Nauchno-tekhnicheskiy vestnik Bryanskogo gosudarstvennogo universiteta 7, no. 3 (September 25, 2021): 270–79. http://dx.doi.org/10.22281/2413-9920-2021-07-03-270-279.

Full text

Abstract:

An accurate assessment of the characteristics of the aerodynamic resistance to movement is important for the preliminary selection of the parameters of the engine, transmission and chassis of a special wheeled chassis or tractor. The strength of the movement resistance affects the dynamic characteristics of the car. The existing calculation methods allow for a wide variation of the aerodynamic drag coefficient, which complicates the task of preliminary selection of car parameters. The purpose of this article is to clarify and develop the engineering methodology for carrying out traction-dynamic calculations of special wheeled vehicles and tractors based on the results of computer modeling performed using computational fluid and gas dynamics (CFD modeling) methods. The modeling methodology and calculation results of a special wheeled chassis manufactured by JSC «BAZ» are considered.

APA, Harvard, Vancouver, ISO, and other styles

36

Liang, Di, and Sheng Jing Tang. "The Design and Development of the Aerodynamic Engineering Prediction Software for Aircrafts." Applied Mechanics and Materials 543-547 (March 2014): 3136–40. http://dx.doi.org/10.4028/www.scientific.net/amm.543-547.3136.

Full text

Abstract:

Aerodynamic analysis and calculation are very important parts in the aircraft design, and aerodynamic engineering prediction is widely used in the aircraft preliminary design stage. However, traditional aerodynamic engineering prediction causes heavy computation and is time-consuming. The developed software such as DATCOM has the disadvantages of complicated operation and black box structure. To overcome the disadvantages above, we develop the software for aerodynamic engineering prediction based on the aerodynamic characteristics and prediction for aircrafts. There are three parts in this software which are database, calculation module and user interface. The software is verified by a numerical example of one aircraft, and compares with the data of Computational Fluid Dynamics (CFD) and the wind tunnel test. The results show that the calculated results of the aerodynamic engineering prediction and CFD are basically consistent, and the software is able to meet the accuracy demand in the preliminary design phase of the aircraft.

APA, Harvard, Vancouver, ISO, and other styles

37

F., Mandour,, Mahmoud, K, and Abdalla, M. "Computational Techniques for Calculation of Missile Aerodynamic Coefficients." International Conference on Applied Mechanics and Mechanical Engineering 14, no. 14 (May 1, 2010): 1–19. http://dx.doi.org/10.21608/amme.2010.38119.

Full text

APA, Harvard, Vancouver, ISO, and other styles

38

Kalugin, Vladimir T., Alexander Y. Lutsenko, and Dinara K. Nazarova. "CALCULATION OF ROCKET NOSE FAIRING SHELLS AERODYNAMIC CHARACTERISTICS." Civil Aviation High TECHNOLOGIES 21, no. 1 (March 13, 2018): 22–29. http://dx.doi.org/10.26467/2079-0619-2018-21-1-22-29.

Full text

APA, Harvard, Vancouver, ISO, and other styles

39

F., Mandour,, Mahmoud, K, and Abdalla, M. "Computational Techniques for Calculation of Missile Aerodynamic Coefficients." International Conference on Electrical Engineering 7, no. 7 (May 1, 2010): 1–21. http://dx.doi.org/10.21608/iceeng.2010.33250.

Full text

APA, Harvard, Vancouver, ISO, and other styles

40

Zhang, Bin, Zhiwei Feng, Boting Xu, Tao Yang, and Wuyu Peng. "Rapid Aerodynamic Calculation Method for Hypersonic Gliding Vehicle." IOP Conference Series: Materials Science and Engineering 751 (February 7, 2020): 012011. http://dx.doi.org/10.1088/1757-899x/751/1/012011.

Full text

APA, Harvard, Vancouver, ISO, and other styles

41

Gonda, Igor, and A. F. Abd El Khalik. "On the Calculation of Aerodynamic Diameters of Fibers." Aerosol Science and Technology 4, no. 2 (January 1985): 233–38. http://dx.doi.org/10.1080/02786828508959051.

Full text

APA, Harvard, Vancouver, ISO, and other styles

42

Li, Yun Feng. "Loads Calculation of Pitch Bearing of Wind Turbine." Advanced Materials Research 148-149 (October 2010): 479–84. http://dx.doi.org/10.4028/www.scientific.net/amr.148-149.479.

Full text

Abstract:

Loads calculation process for pitch bearing of wind turbine was presented. The aerodynamic of the rotor was analyzed by using momentum theory and blade element theory firstly; then the aerodynamic loads, the gravitational loads and the centrifugal loads of the pitch bearing were calculated along each axis of the bearing coordinate system; thirdly, all the loads of each direction of the pitch bearing load were composed into three loads, they are radial, axial and tilting moment loads. A calculation example was given at last.

APA, Harvard, Vancouver, ISO, and other styles

43

Sokhatsky, A. V. "METHOD OF DISCRETE FEATURES AS PLANNING MEANS IS AERODYNAMIC OUTLINES OF TRANSPORT VEHICLES." Journal of Numerical and Applied Mathematics, no. 1 (135) (2021): 186–92. http://dx.doi.org/10.17721/2706-9699.2021.1.25.

Full text

Abstract:

The main stages of the development of the discrete singularities’ method are described. Modern results on the numerical solution of boundary hypersingular integral equations by the methods of collocations and piecewise constant approximations are given. The modern going near planning of aerodynamic design outline of transport vehicles conditionally can be divided into three stages: engineering approaches are close, design on the basis of methods of discrete singularities, approaches that arе based on integration of complete and the Reynolds-averaged of Navier-Stokes equations. On the first stage various engineering approaches are used for forming of aerodynamic outline, going out a requirement specification and requirements of customer. Close geometrical and aerodynamic descriptions are determined in the first. An aerodynamic outline is formed in the first close. On the second stage it follows to use more difficult models of aerodynamics on the basis of various approaches that is built on the model of ideal liquid. Bearing properties are determined, power and moment characteristics for the corresponding outline of aircraft. The third stage is most difficult and expensive cost. On this stage it follows to use methods and models that are based on equations for turbulent flow. The second stage is in-process considered – as means of the previous planning of aerodynamic arrangement with the use of methods of discrete features. A non-stationary chart in that tearing away is designed from all sharp edge of wing is in-process used. This chart has the most general case of forming of process of flowing around of the bearing system of aircraft. However, complication of physical interpretation of forming of such processes in the conditions of ideal liquid remains problematic. The necessities of practice require expansion and deepening of theoretical approaches for the study of non-stationary. Application of model of ideal liquid for the calculation of the bearing system of a perspective transport vehicle allows to set forth aerodynamic task as task of Neumann for Laplace operator. The calculations of the bearing systems of difficult geometrical plane form are conducted. Dependences of carrying capacity and longitudinal moment are got depending on the corner of attack and distance to the ground clearance. A computational experiment confirmed that a method of discrete vorteces was one of important methods of computational aerodynamics. He is effective means for untiing of a number of aerodynamic tasks.

APA, Harvard, Vancouver, ISO, and other styles

44

Ding, Jiao Jiao, Hao Wang, Li Ping Sun, and Bing Ma. "Optimal Design of Wind Turbine Blades with Wilson and BEM Method Integrated." Applied Mechanics and Materials 404 (September 2013): 286–91. http://dx.doi.org/10.4028/www.scientific.net/amm.404.286.

Full text

Abstract:

This paper presented a new dynamic optimal design method of wind turbine blade which combined the Wilson model with the BEM aerodynamic model. Considering the wind energy utilization coefficient as the target function, the Wilson theory was used to optimize a 1.5MW blades aerodynamic shape. The revised distribution of chord and twist angle was nearly of linear change in the main output power section of blade. The optimized wind energy utilization coefficient can reach 0.552, which is very closed to the Betz limitation. In the part of the calculation of aerodynamic performance, considering both the effect of solidity and eddy current loss on the aerodynamic performance calculation, and also considering the sensitivity of the initial value in a nonlinear equation, it utilized the blade element momentum theory (BEM) which was a classical method on the aerodynamic performance of blade to calculate the aerodynamic performance.The results shows the optimized power output can be up to 1.3426MW, and compared with the rated power, the efficiency reached 89%.

APA, Harvard, Vancouver, ISO, and other styles

45

Xu, Hao, Qin Huang, Jinglong Han, and Haiwei Yun. "Calculation of Hinge Moments for a Folding Wing Aircraft Based on High-Order Panel Method." Mathematical Problems in Engineering 2020 (November 5, 2020): 1–14. http://dx.doi.org/10.1155/2020/8881233.

Full text

Abstract:

Calculating hinge moments during the morphing process is a critical aspect in the folding wing design. The deficiencies of the traditional flat-plate aerodynamic model in the calculation are expounded in this work, and a flight simulation platform based on a high-order panel method is established. On the basis of the platform, a typical flight-folding process of the aircraft is simulated, and the results of different aerodynamic models are compared. Results show that airfoil thickness has a great influence on the aerodynamic loading distribution of wing surfaces and thus affects the hinge moments during the folding process. The flat-plate method, which ignores the influence of the airfoil thickness, shows a great simulation error in hinge moment, whereas the high-order panel method can effectively describe the thickness effect and obtain reliable simulation results.

APA, Harvard, Vancouver, ISO, and other styles

46

Bilous, Illya, Illya Kryvohatko, and Yurii Yakovlev. "Methodology for calculating the efficiency of the rudders of the tandem aircraft." MECHANICS OF GYROSCOPIC SYSTEMS, no. 40 (December 26, 2021): 11–21. http://dx.doi.org/10.20535/0203-3771402020248733.

Full text

Abstract:

As of recent rapid development in the field of UAVs, unusual aerodynamic practices can be used, for example, the tandem scheme. In early planning stages, it’s important to evaluate aerodynamic characteristics of the chosen scheme and to approximate its balancing losses, as it impacts the stability and controllability of the craft. The most effective way of aerodynamic characteristics analysis is done using wind tunnels. However, it requires considerable investments in both financial terms and time, when designing the model, conducting the experiment and processing the results. Because of that, it’s worthwhile to consider the simple CFD calculations (XFOIL). This paper calculates aerodynamic characteristics of a tandem-scheme based “A-8” aircraft using XFLR5 analysis tool with the results compared to a real wind tunnel experiment. The overall conclusion of the paper is a recommendation to consider XFLR5 for early planning stages for advanced balancing losses calculation approximation.

APA, Harvard, Vancouver, ISO, and other styles

47

Pakalnis, Egidijus, Eduardas Lasauskas, and Jonas Stankūnas. "ANALYSIS OF CALCULATION RESULTS OF LIFT AND DRAG FORCES FOR SEVERAL WINGS USING NONLINEAR SECTION DATA." Aviation 9, no. 1 (March 31, 2005): 26–31. http://dx.doi.org/10.3846/16487788.2005.9635893.

Full text

Abstract:

Calculation results for 11 different finite span wings are presented. Calculations were made by a combination of a numerical solution of lifting line theory with a technique developed to evaluate nonlinear section lift data. Aerodynamic coefficients for these wings are compared to the research results of other authors and to experimental data.

APA, Harvard, Vancouver, ISO, and other styles

48

Tian, De, Shuo Ming Dai, Si Liu, and Ning Bo Wang. "Analysis of Aerodynamic Performance for Wind Turbine Based on Amended Calculation of BEM Theory." Advanced Materials Research 608-609 (December 2012): 775–80. http://dx.doi.org/10.4028/www.scientific.net/amr.608-609.775.

Full text

Abstract:

Effects of tip losses, hub losses, amended attack angle, and amended thrust coefficient are taken into consideration to analyze aerodynamic performance of wind turbine blades based on the blade element momentum (BEM) theory. Based on amended calculation of BEM theory, a program code is developed by software named Matlab. Using a 1500kW wind turbine as an example, aerodynamic information, performance coefficients and blade load distributions are calculated. Compared with the well-known international wind power design software called Garrad Hassan (GH) Bladed, the results have good consistency, which further verifies amendments to the model algorithms and accuracy of the calculation. As a result, the amended calculation of BEM theory can reflect blade aerodynamic performance characteristics under actual operating condition, which has good reference and practicality for the wind turbine design and evaluation.

APA, Harvard, Vancouver, ISO, and other styles

49

Jin, Xin, Gang Sun, and Chun Juan Liu. "Neural Network and Data Mining Method in Aerodynamic Optimization." Applied Mechanics and Materials 52-54 (March 2011): 1421–26. http://dx.doi.org/10.4028/www.scientific.net/amm.52-54.1421.

Full text

Abstract:

This document focuses on the case that optimization direction is hard to determine in aerodynamic optimization processes, and proposes an intelligent approach based on ANN learning, followed by result visualization using data mining technology. It can not only help visualize the optimization process (qualitative analysis), but also determine the optimization direction (quantitative calculation), which can save time of frequent CFD calculation and obviously improve efficiency in aerodynamic optimization.

APA, Harvard, Vancouver, ISO, and other styles

50

Nie, Tao, and Wei Qiang Liu. "CFD Turbulent Model and Grid Dependency of Hypersonic Aerodynamic Heating Calculation Accuracy." Applied Mechanics and Materials 291-294 (February 2013): 1636–39. http://dx.doi.org/10.4028/www.scientific.net/amm.291-294.1636.

Full text

Abstract:

Four turbulent models are introduced. The hypersonic aerodynamic heating calculation results by Shear Stress Transport (SST) turbulent model of different grid scale shows that near wall y+ spacing approximate to one third of the upper limit prescribed by turbulent model. Then, the comparison of the hypersonic aerodynamic heating calculation results by different turbulent model and the test data shows that SST turbulent model can give an enough accurate result.

APA, Harvard, Vancouver, ISO, and other styles

Journal articles on the topic 'Aerodynamic calculation'

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles