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Relevant bibliographies by topics / Aerodynamic package

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Academic literature on the topic 'Aerodynamic package'

Author: Grafiati

Published: 4 June 2021

Last updated: 17 February 2022

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Journal articles on the topic "Aerodynamic package"

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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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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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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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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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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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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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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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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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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Dissertations / Theses on the topic "Aerodynamic package"

1

López, Pereira Ramón. "Validation of software for the calculation of aerodynamic coefficients : with a focus on the software package Tornado." Thesis, Linköping University, Fluid and Mechanical Engineering Systems, 2010. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-57972.

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Malík, Jiří. "Design kapotáže studentské formule." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2014. http://www.nusl.cz/ntk/nusl-231733.

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Diplomová práce pojednává o návrhu kapotáže vozidla Formula Student. Vozy této kategorie se každoročně učástní série mezinárodních závodů všech zůčastněných studentských týmů. Úroveň návrhu se posuzuje jak v dynamických tak ve statických disciplínách. Tato práce popisuje proces návrhu tří koncepčních variant společně s rozpracováním finální varianty pro fázi výroby. Navíc je zde prezentován koncept obsahující aerodynamický paket, který slouží jako výhledová studie možného vývoje vozidla.

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Rixey, Joseph W., and Joseph W. Rixey. "A multi-faceted engineering study of aerodynamic errors of the Service Aircraft Instrumentation Package (SAIP)." Thesis, Monterey, California. Naval Postgraduate School, 1992. http://hdl.handle.net/10945/24252.

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The general objectives of this research are to investigate, identify, and quantify the aerodynamic sources of altitude determination errors of the U. S. Navy's Service Aircraft Instrumentation Package (SAIP) and to make recommendations to remedy these errors. This multi-faceted study includes aero- panel methods, computational fluid dynamics (CFD), wind tunnel testing, and flight test evaluations. The Airflow Sensor Assembly (ASA), a device similar to a calibrated pitot static tube, was intended to meet the SAIP's required specifications for altitude determination. However, the ASA is housed in the five inch diameter body of the SAIP and mounted on a variety of host aircraft. The over-pressure generated by the SAIP body as well as the wing/pylon system engulf the static pressure ports creating altitude errors well out of performance limits. This over-pressure associated with these bodies was apparently not accounted for during design and acquisition and extensive modifications will be needed to offset or eliminate their effects

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Lopez, Pereira Ramon. "Validation of software for the calculation ofaerodynamic coefficients : with a focus on the software package Tornado." Thesis, Linköping University, Fluid and Mechanical Engineering Systems, 2010. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-58316.

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Several programs exist today for calculating aerodynamic coefficients that with some simplificationsprovide fast approximations of the values for a real aircraft.Four different programs were analyzed for this report: Tornado, AVL, PANAIR and a handbook-typepreliminary method. In addition, ANSYS CFX was used for airfoil validation. For calculation of the zerolift drag, an approximation was computed in order to calculate the remaining values that were notcalculated by the software: drag contribution for fuselages, nacelles and some horizontal stabilizersand fins.Different types of aircraft were selected for trial: two commercial aircraft (Boeing 747-100 and 777-300), a TF-8A research airplane (with area rule application: some additions were made to the fuselageto prevent large variations in the cross-section when the contribution of the wing is added), a LockheedConstellation C-69 used as a military cargo airplane, a Boeing Stratocruiser used by the USAF withtwo configurations (basic and bomber), and an Aero Commander 680 Super, similar to a Cessna 162.Two airfoils (NACA2412, 0012) were also analyzed, to investigate the limitations of software designedfor three-dimensional calculations.The accuracy of the results showed that the validity of the software depends on the planform of theaircraft, as well as the simulation parameters Mach number and Reynolds number. The shape of thewing caused some of the methods to have serious difficulties in converging to valid results, orincreased the simulation time beyond acceptable limits.

Numera finns det olika program för beräkning av de aerodynamiska koefficienterna från en modellmed vissa förenklingar som ger en snabb approximation av värdena för ett verkligt flygplan.Fyra olika program har analyserats för denna rapport: Tornado, AVL, PANAIR och en handbokbaserad preliminär metod. Dessutom användes ANSYS CFX för validering av vingprofiler . Vidberäkningen av noll-lyft motståndet, en approximation användes för de återstående delarna som inteberäknas av de andra metoderna: motståndsbidraget från flygkroppar, gondoler och vissa horisontellastabilisatorer och fenor.Olika flygplaner har testats: två trafikflygplan (Boeing 747-100 och 777-300), ett TF-8Aforskningsflygplan (med area regel användning: några tillägg gjordes på flygkroppen för att tvärsnitteninte har stora variationer när bidraget från vingen läggas), ett Lockheed Constellation C-69, ett BoeingStratocruiser som används av USAF i två konfigurationer (den vanliga och bombplan), och ett AeroCommander 680 Super, som liknar ett Cessna 162. Två vingprofiler (NACA 2412, 0012) analyseradesockså, för att kontrollera begränsningarna av programmen avsedd för tredimensionella beräkningar.Riktigheten av resultaten visade att giltigheten av programmen beror på formen av flygplanernasvingar, samt de simulationernas parametrar: Mach nummer och Reynolds nummer. Formen på vingenorsakade några av de metoderna att ha stora svårigheter med konvergensen till giltiga resultat, ellerökat simulering tid över acceptabla gränser.

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Bin, Ab Wahab Abas. "The development of computer package for determining and solving pedestrian wind environmental discomfort and its wind tunnel validity test." Thesis, University of Salford, 1991. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.305099.

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Books on the topic "Aerodynamic package"

1

Rixey, Joseph W. A multi-faceted engineering study of aerodynamic errors of the Service Aircraft Instrumentation Package (SAIP). Monterey, California: Naval Postgraduate School, 1992.

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2

Blanchard, Robert C. The high resolution accelerometer package (HiRAP) flight experiment summary for the first 10 flights. [Washington D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

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3

Blanchard, Robert C. The High Resolution Accelerometer Package (HiRAP) flight experiment summary for the first 10 flights. [Washington, DC]: National Aeronautics and Space Administration, 1992.

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Blanchard, Robert C. The high resolution accelerometer package (HiRAP) flight experiment summary for the first 10 flights. Washington, D.C: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

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5

United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., ed. UNAERO, a package of FORTRAN subroutines for approximating unsteady aerodynamics in the time domain. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1987.

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6

Center, Langley Research, ed. Description of an aeronautical geometry conversion package: Wave-drag to LaWGS to SIMP. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1987.

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Conference papers on the topic "Aerodynamic package"

1

Ibos, C., C. Lacroix, L. Chuzet, D. Granville, C. Ibos, C. Lacroix, L. Chuzet, and D. Granville. "SINPA, a full 3D fluid-structure software package for parachute simulation." In 14th Aerodynamic Decelerator Systems Technology Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-1508.

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2

Epple, Philipp, Tobias Essler, Gerhard Bloch, Viktor Below, and Stefan Gast. "Aerodynamic Devices for Formula Student Race Cars." In ASME 2014 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/imece2014-39041.

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Formula Student race cars are getting more competitive and hence enhancements of the car aerodynamics, although the top speeds are not exceeding 140 km/h, are getting more important in order to have a competitive race car. Therefore aerodynamic packages consisting of several aerodynamic devices are being developed. Especially the front and rear inverted airfoils or wings have a major influence on the dynamic behaviour of the car. These wings are designed in order to develop a maximum down force at still acceptable drag. The Reynolds number is about 5×105. However, most of the airfoils and corresponding available airfoil data were developed for Reynolds numbers of the order of 3×106<Re<8×106. The lift coefficient of an airfoil is basically determined by its camber, the distance of the maximum camber from the leading edge, thickness and the shape of the airfoil, as well as by the angle of attack. The NACA 4 digit series of airfoils allows controlling these parameters exactly. Therefore a study was performed analyzing over 500 different NACA 4 digit airfoils configurations systematically by variation of these parameters and studying its impact on the lift and drag coefficients at Reynolds numbers of 5×105. Based on these airfoils the aerodynamic design process is described. Full car CFD simulations with ANSYS CFX of the race car with and without aerodynamic package are shown and compared. Detailed quantitative analysis of the forces on the wings and the whole car are presented without and with the aerodynamic package.

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3

Rehnberg, Sven, Lucas Börjesson, Robert Svensson, and Jonathan Rice. "Race Car Aerodynamics - The Design Process of an Aerodynamic Package for the 2012 Chalmers Formula SAE Car." In SAE 2013 World Congress & Exhibition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2013. http://dx.doi.org/10.4271/2013-01-0797.

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Ning, Fangfei. "MAP: A CFD Package for Turbomachinery Flow Simulation and Aerodynamic Design Optimization." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-26515.

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This paper presents an in-house CFD package and its derivations for turbomachinery flow simulation as well as aerodynamic design optimization which have been employed in several primary Chinese aero-engine institutions. The package contains TurboMesh, a highly automated mesh generation code for turbomachinery, and MAP, a CFD solver for general purpose. Besides the programming strategies, the numerical schemes, and the parallelization methods adopted in the codes are outlined. Emphasis is placed on a novel mixing plane model used in MAP. The proposed model satisfies flux conservation property and very robust in actual usage. Additionally, further improved performance of the model can be achieved by applying a technique similar to the perfect matching layer for non-reflecting boundary conditions. On the basis of MAP, a set of derivations have also been developed. They include several versions of MAP which are based on specific flow models, respectively, an inverse code for the design optimization of 3D blade shape, an improved-delayed-detached-eddy-simulation based code, and a scale-adaptive-simulation based code. Some of these versions of MAP are briefly introduced and demonstrated through a few examples except for the inverse code in which a direct method proposed by the author is explained with a few more words. Illustrations show the applicability of the inverse code for the design of compressor blades in practical multi-blade row environment. By embedding MAP with an in-house numerical optimization package, the numerical optimization of the 2D/3D blade shape can be realized. Some examples for 3D aerodynamic optimizations of compressors are presented.

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THOMPSON, J., J. RUSSELL, and R. BLANCHARD. "Methods for extracting aerodynamic accelerations from Orbiter High Resolution Accelerometer Package flight data." In 14th Atmospheric Flight Mechanics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2365.

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Oskin, Sergey V., Alexei V. Miroshnikov, and Dmitry S. Tsokur. "Investigation of the Aerodynamic Characteristics of Electric Motors when Regulating Their Speed in the Comsol Package." In 2021 International Russian Automation Conference (RusAutoCon). IEEE, 2021. http://dx.doi.org/10.1109/rusautocon52004.2021.9537420.

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Maazouddin, Amarddin Z., and Dongmei Zhou. "Drag Reduction on SUVs and Trucks by Wake Control." In ASME 2008 International Mechanical Engineering Congress and Exposition. ASMEDC, 2008. http://dx.doi.org/10.1115/imece2008-68730.

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Road vehicles such as SUVs or pickup trucks are described as bluff bodies. When the air flow passes over the road vehicles the flow will separate at the rear of the vehicle, forming a large low pressure turbulent wake region behind the vehicle. The formed pressure drag posts resistance on the road vehicles and thus increases the work done by the engine to propel the vehicle. The purpose of this paper is to present the development and design of drag reducing devices for SUVs by studying the SUV’s aerodynamics. Numerical simulations using commercial software package — FLUENT were performed in order to study the aerodynamics behind the vehicles. A computer model of the Ahmed Vehicle Model was selected as a benchmark test. This Ahmed Model is a simple geometric body that retains major flow features where most part of the drag is concentrated. Seven different spoiler designs for the SUV have been studied. Their results for the SUV’s aerodynamics have been presented through velocity vectors, pressure contours, and aerodynamic lift and drag plots. One spoiler design was found to be able to reduce aerodynamic drag and others were found to be able to reduce the lift.

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Atiqullah, Mir, Rigoverto Sanchez, and Benjamin Hamler. "Undergraduate Research on Trailer-Truck Aerodynamic Drag." In ASME 2013 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/imece2013-65218.

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The transportation industry is heavily dependent on ‘big rigs’ or semitrailers. Since its introduction during 1920s semitrailers have revolutionized the industry. However their geometrical designs have not evolved much to make them aerodynamically more streamlined, thus more fuel efficient. While over 5.6 million such commercial trailer trucks are registered in the country and with increasing diesel fuel prices, it is more important than ever to study their aerodynamics, redesign for reducing aerodynamic drag and help make these ‘big rigs’ more fuel efficient. Aerodynamic drag is the force that acts on a solid object moving in air due to difference in dynamic pressure developed around that object. Skin friction also causes resistance force which is small compared to pressure induced drag. Higher drag resistance, just like road and tire resistance, causes loss of energy and thereby lowers fuel mileage. Drag resistance is caused by both surface friction as well as air pressure difference around a moving object/vehicle. An ideal remedy is of course to completely redesign the shape and size of these semitrailers to conform to those with known low drag. Another intermediate approach would be to retrofit the existing semitrailers with devices that change the overall shape towards more aerodynamic ones. During the recent past a wide range of such add on devices have been introduced. Current research was directed in two fronts: CAD and Drag simulation as well as experimental drag testing. First a base CAD model and then various modifications were developed using an industry standard CAD package. These models were then imported into Computational Fluid Dynamics (CFD) software. These followed by modeling add-on devices to reduce drag. The simulations were repeated with various combinations of these add-on drag reducers. The areas targeted for drag reduction study included gap between tractor and trailer, lower sides of the trailer between front and rear wheel sets, and rear of the trailer. The results showed varying effectiveness of these add-on devices, individually and in combination. Scale models of the trailer truck were built using wood as well as Rapid Prototyping (RP) directly from CAD using polymer. These models were then tested in the wind tunnel at speeds between 35 and 75 miles per hour. The data and the trends in Cd values compared well with the simulated values. The overall CFD and scale model studies provided a comprehensive knowledge and understanding of the drag in semi-trailers and factors that affect it. Future studies may expand the varieties and locations of these devices as well as complete redesigns of the trailer-trucks.

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Aziz, Imran, Wasim Tarar, Imran Akhtar, and M. Nadeem Azam. "Vibratory Stress Suppression in Turbine Blades Subjected to Aerodynamic Loading." In ASME 2013 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/imece2013-63724.

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Vibratory stresses are the main cause of failure in gas turbine engines and other rotating machinery components. These stresses must be attenuated to an acceptable level through an efficient process in order to prevent failures in turbine blades. Research [8] has shown that a thin magneto mechanical coating layer can make a significant contribution to the damping and reduction of these vibratory stresses. Previous studies on analyzing the damping characteristics of these coatings for various applications, such as beams and turbine blades, employed general solid mechanics loads. In this study, we numerically compute aerodynamic loads on one and a half stage axial turbine in order to bring more reality to the problem. We employ a three-dimensional finite-volume based solver to simulate the flow in the turbine using SST model to account for turbulence effects. Sliding mesh technique is used to allow the transfer of flow parameters across the sliding rotor/stator interfaces. In order to model a single passage configuration, profile transformation method is used. A free vibration analysis has been performed to obtain natural frequencies and corresponding mode shapes to analyze resonance conditions. The computed CFD loads are then applied to an uncoated and coated turbine blade through a finite-element analysis (FEA) package. A forced response analysis is performed at the critical frequencies to obtain vibratory stresses. Numerical results show suppression of vibratory stresses at various low and high frequency vibration modes. The results are benchmarked against published data and closely match the expected outcome. The research presents an effective procedure for suppression of vibratory stresses in gas turbine engine component subjected to real world aerodynamic loading. The new procedure is a significant improvement towards more realistic simulation based solutions for vibration suppression problems.

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10

Sikder, Tushita, Saurabh Kapoor, and Yuping He. "Optimizing Dynamic Performance of High-Speed Road Vehicles Using Aerodynamic Aids." In ASME 2016 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/imece2016-65414.

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This paper focuses on the effects of aerodynamic aids on the lateral and longitudinal dynamics of high-speed road vehicles. Aerodynamic aids, such as spoilers, can reduce drag to improve vehicle’s fuel economy and acceleration performance. On the other hand, aerodynamic aids can be utilized to enhance the lateral stability of the vehicle at high speeds by generating downforce or negative lift. However, the co-existence of drag and lift creates a paradox, that is, the downforce generated to improve car’s high-speed stability acts as a parasitic force on the car-body and slows down the vehicle forward speed. This paper will illustrate the juxtaposed effects of the aerodynamic forces on the lateral stability of the vehicle. Airfoils in the role of external aerodynamic aids will be examined based on their shapes, geometrical configurations, and at varying relative positions using the CFD technique. Moreover, the effects of attack angles, change in Reynold’s numbers (air stream velocities), and varying ground clearance on the lateral dynamics of the vehicle will be analyzed using numerical simulations with ANSYS FLUENT software package. The results and reliability of CFD simulations has a high dependency on the size of the grid, thus the aim of this paper will be to ensure that the results are independent of the grid size. Selection of the optimum design will be based on performance parameters like drag and lift coefficients. The challenge posed here is to ensure the lateral stability of the vehicle while achieving high average speed. Therefore, the main goal of the study is to enhance handling capabilities of the road vehicles at high speeds while minimizing the drag.

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