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Journal articles on the topic 'Aerodynamics (except hypersonic aerodynamics)'

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Published: 10 December 2022
Last updated: 28 January 2023

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1

Yang, R. J. "Hypersonic fin aerodynamics." Journal of Spacecraft and Rockets 31, no. 2 (March 1994): 339–41. http://dx.doi.org/10.2514/3.26443.

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2

Cummings, Russell M., and Hsun-Tiao Yang. "Lester Lees and Hypersonic Aerodynamics." Journal of Spacecraft and Rockets 40, no. 4 (July 2003): 467–74. http://dx.doi.org/10.2514/2.3988.

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3

Agnone, Anthony M., and B. Prakasam. "Hypersonic aerodynamics of nonaxisymmetric boattailed bodies." Journal of Spacecraft and Rockets 24, no. 2 (March 1987): 181–82. http://dx.doi.org/10.2514/3.25894.

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4

Harloff, Gary J. "High angle-of-attack hypersonic aerodynamics." Journal of Spacecraft and Rockets 25, no. 5 (September 1988): 343–44. http://dx.doi.org/10.2514/3.26010.

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5

YE, YouDa. "Advances and prospects in hypersonic aerodynamics." Chinese Science Bulletin 60, no. 12 (April 1, 2015): 1095–103. http://dx.doi.org/10.1360/n972014-01180.

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6

Gerasimov, S. I., V. I. Erofeev, A. G. Sirotkina, A. V. Zubankov, and R. V. Gerasimova. "Contactless Measuring Section in Hypersonic Aerodynamics." Journal of Applied Mechanics and Technical Physics 60, no. 4 (July 2019): 639–43. http://dx.doi.org/10.1134/s0021894419040060.

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7

Candler, Graham V. "Book Review: Computational Methods in Hypersonic Aerodynamics." AIAA Journal 31, no. 2 (February 1993): 410. http://dx.doi.org/10.2514/3.59985.

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8

Cunningham, Mark J. "Hypersonic aerodynamics for an entry research vehicle." Journal of Spacecraft and Rockets 24, no. 2 (March 1987): 97–98. http://dx.doi.org/10.2514/3.25879.

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9

Thuruthimattam, B. J., P. P. Friedmann, K. G. Powell, and R. E. Bartels. "Computational aeroelastic studies of a generic hypersonic vehicle." Aeronautical Journal 113, no. 1150 (December 2009): 763–74. http://dx.doi.org/10.1017/s0001924000003420.

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Abstract The hypersonic aeroelastic problem of a generic hypersonic vehicle having a lifting-body type fuselage and canted fins is studied using third order piston theory and Euler aerodynamics. Computational aeroelastic response results are used to obtain frequency and damping characteristics, and compared with those from piston theory solutions for a variety of flight conditions. Aeroelastic behavior is studied for the range of 2·5 < M < 28, at altitudes ranging from 10,000ft to 80,000ft. Because of the significant computational resources required, a study on optimal mesh selection was first carried out for use with Euler aerodynamics. The three dimensional flow effects captured using Euler aerodynamics was found to lead to significantly higher flutter boundaries when compared to those based on nonlinear piston theory. The results presented here illustrate some of the more important three dimensional effects that can be encountered in hypersonic aeroelasticity of complex configurations.
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10

McNamara, Jack J., Andrew R. Crowell, Peretz P. Friedmann, Bryan Glaz, and Abhijit Gogulapati. "Approximate Modeling of Unsteady Aerodynamics for Hypersonic Aeroelasticity." Journal of Aircraft 47, no. 6 (November 2010): 1932–45. http://dx.doi.org/10.2514/1.c000190.

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11

Ivanovich Khlopkov, Yuri, Vladimir Alekseevich Zharov, Anton Yurievich Khlopkov, and Zay Yar Myo Myint. "Development of Monte Carlo Methods in Hypersonic Aerodynamics." Universal Journal of Physics and Application 8, no. 4 (April 2014): 213–20. http://dx.doi.org/10.13189/ujpa.2014.020403.

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12

Upadhyay, Shivansh, Pramod Kumar, and Ajay Kumar Maurya. "AERODYNAMICS, STRUCTURAL CONFIGURATION AND MATERIALS OF HYPERSONIC AIRCRAFTS." International Journal of Engineering Applied Sciences and Technology 04, no. 07 (December 25, 2019): 158–64. http://dx.doi.org/10.33564/ijeast.2019.v04i07.025.

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13

Candler, G. V. "Errata: Review of Computational Methods in Hypersonic Aerodynamics." AIAA Journal 31, no. 4 (April 1993): 794. http://dx.doi.org/10.2514/3.49026.

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14

안미치코. "Aerodynamics Calculation of Reentry Body in Hypersonic Flowfield." Journal of the Korean Society of Mechanical Technology 15, no. 6 (December 2013): 819–25. http://dx.doi.org/10.17958/ksmt.15.6.201312.819.

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15

Iannelli, G. S., and A. J. Baker. "Accuracy and Efficiency Assessments for a Weak Statement CFD Algorithm for High-Speed Aerodynamics." Journal of Engineering for Gas Turbines and Power 116, no. 3 (July 1, 1994): 468–73. http://dx.doi.org/10.1115/1.2906844.

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A bilinear finite element, implicit Runge-Kutta space-time discretization has been established for an aerodynamics weak statement CFD algorithm. The algorithm admits real-gas effect simulation, for reliable hypersonic flow characterization, via an equilibrium reacting air model. The terminal algebraic system is solved using an efficient block-tridiagonal quasi-Newton linear algebra procedure that employs tensor matrix product factorizations within a lexicographic mesh-sweeping protocol. A block solution-adaptive remeshing, for totally arbitrary convex elements, is also utilized to facilitate accurate shock and/or boundary layer flow resolution. Numerical validations are presented for representative benchmark supersonic-hypersonic aerodynamics problem statements.
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16

Xiao, Han-shan, Chao Ou, Hong-liang Ji, Zheng-chun He, Ning-yuan Liu, and Xian-xu Yuan. "Low-Cost and Aerodynamics-Aim Hypersonic Flight Experiment MF-1." MATEC Web of Conferences 316 (2020): 04006. http://dx.doi.org/10.1051/matecconf/202031604006.

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For increasing understanding of fundamental hypersonic phenomena, the flight test program, named MF-1, is to gather fundamental scientific and engineering data on the physics and technologies critical to future operational hypersonic flight with low-cost flight test platform, which is built on the retrofitted rockets. The MF-1 program is a hypersonic flight test program executed by China Aerodynamic Research and Development Center (CARDC). The MF-1 flight flew in December 2015. The flight focuses primarily on integration of instrumentation on the test vehicle, with application to boundary layer transition and shock interaction experiments. The MF-1 payload consists of a blunted 7°half angle cone, a cylinder and 33° flare configuration. The payload was boosted to Mach 5.32 utilizing a solid-rocket booster without control for the whole flight. The flight was fully successful, and measured transition under supersonic and hypersonic conditions. The heat flux data were given by the three-dimensional thermal identification method to discriminate transition zone. The preliminary analysis shows that the real-time flight data obtained by MF-1 are reliable and can be used to validate the transition predicting model and software. The results show that the existing model is able to predict the transition location of cone at a small angle-of-attack for supersonic or hypersonic flow. This paper describes the MF-1 mission and some general conclusions derived from the experiment.
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17

Lobbia, Marcus A. "Rapid Supersonic/Hypersonic Aerodynamics Analysis Model for Arbitrary Geometries." Journal of Spacecraft and Rockets 54, no. 1 (January 2017): 315–22. http://dx.doi.org/10.2514/1.a33514.

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18

Mihai Leonida, NICULESCU, FADGYAS Maria Cristina, COJOCARU Marius Gabriel, PRICOP Mihai Victor, STOICAN Mihaita Gilbert, and PEPELEA Dumitru. "Computational Hypersonic Aerodynamics with Emphasis on Earth Reentry Capsules." INCAS BULLETIN 8, no. 3 (September 8, 2016): 55–64. http://dx.doi.org/10.13111/2066-8201.2016.8.3.5.

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19

Shen, Jian, Shao-bo Fan, Ya-xin Ji, Qing-yu Zhu, and Ji Duan. "Aerodynamics analysis of a hypersonic electromagnetic gun launched projectile." Defence Technology 16, no. 4 (August 2020): 753–61. http://dx.doi.org/10.1016/j.dt.2020.01.008.

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20

Yang, Xiaofeng, Wei Tang, Yewei Gui, Yanxia Du, Guangming Xiao, and Lei Liu. "Hypersonic static aerodynamics for Mars science laboratory entry capsule." Acta Astronautica 103 (October 2014): 168–75. http://dx.doi.org/10.1016/j.actaastro.2014.06.036.

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21

Stalker, R. J. "Modern developments in hypersonic wind tunnels." Aeronautical Journal 110, no. 1103 (January 2006): 21–39. http://dx.doi.org/10.1017/s0001924000004346.

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AbstractThe development of new methods of producing hypersonic wind-tunnel flows at increasing velocities during the last few decades is reviewed with attention to airbreathing propulsion, hypervelocity aerodynamics and superorbital aerodynamics. The role of chemical reactions in these flows leads to use of a binary scaling simulation parameter, which can be related to the Reynolds number, and which demands that smaller wind tunnels require higher reservoir pressure levels for simulation of flight phenomena. The use of combustion heated vitiated wind tunnels for propulsive research is discussed, as well as the use of reflected shock tunnels for the same purpose. A flight experiment validating shock-tunnel results is described, and relevant developments in shock tunnel instrumentation are outlined. The use of shock tunnels for hypervelocity testing is reviewed, noting the role of driver gas contamination in determining test time, and presenting examples of air dissociation effects on model flows. Extending the hypervelocity testing range into the superorbital regime with useful test times is seen to be possible by use of expansion tube/tunnels with a free piston driver.
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22

Tuttle, S. L. "An Experiment for Teaching Hypersonic Aerodynamics to Undergraduate Mechanical Engineering Students." International Journal of Mechanical Engineering Education 28, no. 2 (April 2000): 151–62. http://dx.doi.org/10.7227/ijmee.28.2.4.

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An experiment designed to enhance the teaching of hypersonics to undergraduate mechanical engineering students is described. A small shock tunnel is used to demonstrate principles learned in the classroom. The pressures measured on two models at hypersonic Mach numbers are compared with suitable theoretical estimates. Typical results are shown and the success and relevance of the experiment is reported. Consideration is given to the teaching of such a highly specialized subject as hypersonic aerodynamics at the undergraduate level.
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23

Nair, Manoj T., Naresh Kumar, and S. K. Saxena. "Computational Analysis of Inlet Aerodynamics for a Hypersonic Research Vehicle." Journal of Propulsion and Power 21, no. 2 (March 2005): 286–91. http://dx.doi.org/10.2514/1.2839.

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24

Khorrami, A. Farid, and Frank T. Smith. "Hypersonic aerodynamics on thin bodies with interaction and upstream influence." Journal of Fluid Mechanics 277 (October 25, 1994): 85–108. http://dx.doi.org/10.1017/s0022112094002697.

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In the fundamental configuration studied here, a steady hypersonic free stream flows over a thin sharp aligned airfoil or flat plate with a leading-edge shock wave, and the flow field in the shock layer (containing a viscous and an inviscid layer) is steady laminar and two-dimensional, for a perfect gas without real and high-temperature gas effects. The viscous and inviscid layers are analysed and computed simultaneously in the region from the leading edge to the trailing edge, including the upstream-influence effect present, to determine the interactive flow throughout the shock layer and the positions of the shock wave and the boundary-layer edge, where matching is required. Further theoretical analysis of the shock layer helps to explain the computational results, including the nonlinear breakdown possible when forward marching against enhanced upstream influence, for example as the wall enthalpy increases towards its insulated value. Then the viscous layer is computed by sweeping methods, for higher values of wall enthalpies, to prevent this nonlinear breakdown for airfoils including the flat plate. Thin airfoils in hypersonic viscous flow are treated, for higher values of the wall enthalpies and with the upstream-influence effect, as are hypersonic inviscid flows, by modifying the computational methods used for the flat plate. Also, the behaviour of the upstream influence for bodies of relatively large thickness, and under wall velocity slip and enthalpy jump for flat plates, is discussed briefly from a theoretical point of view.Subsequent to the present work, computations based on the Navier–Stokes and on the parabolized Navier–Stokes equations have yielded excellent and good agreement respectively with the present predictions for large Mach and Reynolds numbers.
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25

Chen, Zhiqiang, Yonghui Zhao, and Rui Huang. "Parametric reduced-order modeling of unsteady aerodynamics for hypersonic vehicles." Aerospace Science and Technology 87 (April 2019): 1–14. http://dx.doi.org/10.1016/j.ast.2019.01.035.

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26

Rychkov, V. N., M. E. Topchiyan, A. A. Meshcheryakov, and V. I. Pinakov. "Use of high pressures for solving problems of hypersonic aerodynamics." Journal of Applied Mechanics and Technical Physics 41, no. 5 (September 2000): 855–64. http://dx.doi.org/10.1007/bf02468731.

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27

Babinsky, Holger. "Editorial." Aeronautical Journal 122, no. 1253 (June 27, 2018): 1021. http://dx.doi.org/10.1017/aer.2018.75.

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It is an enormous honour for me to take over from Peter Bearman as Editor-in-Chief of the world's oldest aeronautics journal. Most of you will not know me and thus I'd like to give you a bit of background: I grew up in Bavaria and studied Aerospace Engineering at Stuttgart University. Under the German system it was common to work on the final research project (Diploma thesis) outside the University and I was lucky enough to find a suitable place in Cranfield. There, my supervisor was John Stollery, who led this journal as Editor-in-Chief for many years. After a PhD in hypersonic aerodynamics (also at Cranfield) I became a post-doctoral researcher at Tohoku University in Japan. 18 months later I returned to the UK to take up a lectureship in aerodynamics at the Engineering Department of Cambridge University where I am now the Professor of Aerodynamics, Head of the Fluids Group and Deputy Head of Department with responsibility for graduate education.
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28

Liu, Hai Yong, and Hong Fu Qiang. "Numerical Simulation of the Aerodynamics and Aerothermal Heating for a Hypersonic Vehicle." Advanced Materials Research 429 (January 2012): 147–53. http://dx.doi.org/10.4028/www.scientific.net/amr.429.147.

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A hypersonic forebody based on waverider and liftbody concept was presented. The configuration of a new hypersonic vehicle was designed by taking the configuration of X43A. Numerical simulation was conducted on the two-dimensional and three-dimensional models of the vehicle using CFD software of Gambit and Fluent. The effects of Mach number and attack angle on the aerodynamics and heat transfer were considered. The results of simulation investigation showed that: High compressed air was constrained beneath the pre-compressed surface of the forebody. The computational data on central cross section of the three-dimensional model for the vehicle was similar to that of the two-dimensional model. But great pressure gradient existed between the pre-compressed surface and side surface of the forebody which would lead to severe air leakage and pressure loss. The increasing of attack angle and Mach number enforced the stagnation of shock wave on the side walls of the engine. The thermal environment of the vehicle was deteriorated rapidly with increasing Mach number. But the viscous heating was overrated which lead to unbelievable high temperature. The software Fluent was more suitable to predict the aerodynamics than the heat transfer for hypersonic flow.
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29

Bhutta, Bilal A., and Clark H. Lewis. "Comparison of hypersonic experiments and PNS predictions. I - Aerothermodynamics. II - Aerodynamics." Journal of Spacecraft and Rockets 28, no. 4 (July 1991): 387–93. http://dx.doi.org/10.2514/3.26257.

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30

Neuwerth, G., U. Peiter, F. Decker, and D. Jacob. "Reynolds Number Effects on Low-Speed Aerodynamics of a Hypersonic Configuration." Journal of Spacecraft and Rockets 36, no. 2 (March 1999): 265–72. http://dx.doi.org/10.2514/2.3441.

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31

Wang, L., G. Y. He, Q. Wang, and L. S. Chen. "An Engineering Method for Computing the Aerodynamics Performance of Hypersonic Vehicle." IOP Conference Series: Materials Science and Engineering 816 (June 3, 2020): 012006. http://dx.doi.org/10.1088/1757-899x/816/1/012006.

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32

Xie, Dan, Min Xu, Honghua Dai, and Tao Chen. "New Look at Nonlinear Aerodynamics in Analysis of Hypersonic Panel Flutter." Mathematical Problems in Engineering 2017 (2017): 1–13. http://dx.doi.org/10.1155/2017/6707092.

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A simply supported plate fluttering in hypersonic flow is investigated considering both the airflow and structural nonlinearities. Third-order piston theory is used for nonlinear aerodynamic loading, and von Karman plate theory is used for modeling the nonlinear strain-displacement relation. The Galerkin method is applied to project the partial differential governing equations (PDEs) into a set of ordinary differential equations (ODEs) in time, which is then solved by numerical integration method. In observation of limit cycle oscillations (LCO) and evolution of dynamic behaviors, nonlinear aerodynamic loading produces a smaller positive deflection peak and more complex bifurcation diagrams compared with linear aerodynamics. Moreover, a LCO obtained with the linear aerodynamics is mostly a nonsimple harmonic motion but when the aerodynamic nonlinearity is considered more complex motions are obtained, which is important in the evaluation of fatigue life. The parameters of Mach number, dynamic pressure, and in-plane thermal stresses all affect the aerodynamic nonlinearity. For a specific Mach number, there is a critical dynamic pressure beyond which the aerodynamic nonlinearity has to be considered. For a higher temperature, a lower critical dynamic pressure is required. Each nonlinear aerodynamic term in the full third-order piston theory is evaluated, based on which the nonlinear aerodynamic formulation has been simplified.
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33

Khorrami, Ahmad Farid. "Upstream influence in hypersonic aerodynamics over sharp thin and thick bodies." International Journal of Engineering Science 41, no. 1 (January 2003): 45–59. http://dx.doi.org/10.1016/s0020-7225(02)00139-8.

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34

Pilyugin, N. N., R. F. Talipov, and S. V. Utyuzhnikov. "On the applicability of some approximate similitude laws in hypersonic aerodynamics." Fluid Dynamics 29, no. 2 (April 1994): 251–57. http://dx.doi.org/10.1007/bf02324316.

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35

Iannelli, G. S., and A. J. Baker. "A non-linearly stable implicit finite element algorithm for hypersonic aerodynamics." International Journal for Numerical Methods in Engineering 34, no. 2 (March 30, 1992): 419–41. http://dx.doi.org/10.1002/nme.1620340203.

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36

Bugel, Mathilde, Philippe Reynier, and Arthur Smith. "Survey of European and Major ISC Facilities for Supporting Mars and Sample Return Mission Aerothermodynamics and Tests Required for Thermal Protection System and Dynamic Stability." International Journal of Aerospace Engineering 2011 (2011): 1–18. http://dx.doi.org/10.1155/2011/937629.

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In the frame of future sample return missions to Mars, asteroids, and comets, investigated by the European Space Agency, a review of the actual aerodynamics and aerothermodynamics capabilities in Europe for Mars entry of large vehicles and high-speed Earth reentry of sample return capsule has been undertaken. Additionally, capabilities in Canada and Australia for the assessment of dynamic stability, as well as major facilities for hypersonic flows available in ISC, have been included. This paper provides an overview of European current capabilities for aerothermodynamics and testing of thermal protection systems. This assessment has allowed the identification of the needs in new facilities or upgrade of existing ground tests for covering experimentally Mars entries and Earth high-speed reentries as far as aerodynamics, aerothermodynamics, and thermal protection system testing are concerned.
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37

Jadhav, Vaibhav Balkrishna, and Arundhati Warke. "Investigation of ELAC 1 Aerodynamics Using CFD in Supersonic Flow." Applied Mechanics and Materials 592-594 (July 2014): 1955–61. http://dx.doi.org/10.4028/www.scientific.net/amm.592-594.1955.

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The ELAC 1 (ELliptical Aerodynamic Configuration 1) is basically Hypersonic space vehicle and first stage of TSTO (Two Stage To Orbit) destined to fly up to altitude of 35 Km with M∞=7 (Free stream Mach No.). In this paper, the comparison between the experimental data available at RWTH, Aachen and Polyhedral Unstructured Navier-Stokes solver simulations are made. The different AOA (Angles of attack) 0̊, 6̊ and 10̊ are considered with Re = 3.6×106 for the supersonic flow simulations. The various coefficients such as Aerodynamic coefficients, Pressure coefficients are compared with the wind tunnel data and the physics of the flow field is investigated.
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38

Ismagilov, D. R., and R. V. Sidelnikov. "Features of numerical simulation of hypersonic flow around simple bodies." Journal of «Almaz – Antey» Air and Space Defence Corporation, no. 2 (June 30, 2015): 49–54. http://dx.doi.org/10.38013/2542-0542-2015-2-49-54.

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The analysis of the possibility of using the numerical approximation schemes streams Roe FDS and AUSM + to meet the challenges of hypersonic aerodynamics and research trends in the perturbed region ahead streamlined blunt body to determine the laws of thermal and gas-dynamic processes and the establishment of the characteristics associated with the development of the necessary thermal protection of aircraft. Based on a comparison of the data with the experimental results revealed that the method of splitting the flow AUSM + is able to solve the problem of hypersonic flow around bodies with acceptable accuracy.
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39

Yang, Rui Guang, Jian Qiao Yu, and Yuan Chuan Shen. "Flight Dynamic Characteristic Analysis of a Generic Airbreathing Hypersonic Vehicle." Applied Mechanics and Materials 716-717 (December 2014): 724–29. http://dx.doi.org/10.4028/www.scientific.net/amm.716-717.724.

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Because of the high speed, strong coupling between aerodynamics and propulsion system, complex environmental conditions and new propulsion system, the airbreathing hypersonic vehicles have a complex dynamics characteristic. This paper use the generic hypersonic vehicle model (CSULA-GHV) to research this issue. The nonlinear longitudinal equations of motion are linearized based on the assumption of little perturbation. Analyze the dynamic characteristic on a feature point selected. The results show that, the stability of this model is poor. It has to design an efficient controller to adjust the poor stability.
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40

Chen, Z., Y. Zhao, and R. Huang. "Reduced-Order Modeling of Unsteady Hypersonic Aerodynamics in Multi-Dimensional Parametric Space." Journal of Applied Fluid Mechanics 11, no. 4 (July 1, 2018): 1033–45. http://dx.doi.org/10.29252/jafm.11.04.27943.

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41

Wang, Hongyu, Fu Min, Zhendong Xie, Jie Li, Jinwen Dai, and Yanguang Yang. "Quantitative study of the control of hypersonic aerodynamics using millisecond pulsed discharges." Physics of Fluids 34, no. 2 (February 2022): 021701. http://dx.doi.org/10.1063/5.0081599.

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42

Riabov, Vladimir V. "Aerodynamics of Two Side-by-Side Plates in Hypersonic Rarefied-Gas Flows." Journal of Spacecraft and Rockets 39, no. 6 (November 2002): 910–16. http://dx.doi.org/10.2514/2.3898.

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43

Oberkampf, William L., and Daniel P. Aeschliman. "Joint computational/experimental aerodynamics research on a hypersonic vehicle. I - Experimental results." AIAA Journal 30, no. 8 (August 1992): 2000–2009. http://dx.doi.org/10.2514/3.11172.

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44

Arguchintseva, Margarita A. "Shape Optimization in Problems of 3-Dimensional Hypersonic Aerodynamics and Heat Transfer." IFAC Proceedings Volumes 32, no. 2 (July 1999): 8118–23. http://dx.doi.org/10.1016/s1474-6670(17)57385-1.

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45

Guo, Jinghui, Guiping Lin, Jun Zhang, Xueqin Bu, and Hao Li. "Hypersonic aerodynamics of a deformed aeroshell in continuum and near-continuum regimes." Aerospace Science and Technology 93 (October 2019): 105296. http://dx.doi.org/10.1016/j.ast.2019.07.029.

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46

Luo, Da Lei, Jun Liu, Yuan Wang, and Deng Feng Fan. "The Method for Numerical Simulation of the Impact on the Infrared Radiation Seeker from the Warhead Shock Layer." Applied Mechanics and Materials 390 (August 2013): 464–67. http://dx.doi.org/10.4028/www.scientific.net/amm.390.464.

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It counts the impact on the infrared radiation seeker which in the head of the hypersonic missile. Firstly, it built the calculated model based on the shape of a missile, and compartmentalized the aerodynamics flow field grid , the infrared radiation seeker main mirror grid , the radiation field grid, and had the relation of the grids unambiguous, and got the communication of the aerodynamics flow field. Then it educed irradiance formula about the shock layer aerodynamic flow fled radiation affect to the infrared radiation seeker main mirror. The result is the infrared radiation wave band 3~5 to the main mirror, from the shock layer aerodynamic flow fled is about 120 W/m2. The distributing law of the impact is annular circumfused the center of the main mirror, the infrared radiation is the highest in the center of the main mirror, decreased by the radius of the main mirror.
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47

ZHU, JIAN, YING-YU HOU, CHEN JI, and ZI-QIANG LIU. "AERODYNAMIC MODELING OF OSCILLATING WING IN HYPERSONIC FLOW: A NUMERICAL STUDY." International Journal of Modern Physics: Conference Series 42 (January 2016): 1660177. http://dx.doi.org/10.1142/s2010194516601770.

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Various approximations to unsteady aerodynamics are examined for the unsteady aerodynamic force of a pitching thin double wedge airfoil in hypersonic flow. Results of piston theory, Van Dyke’s second-order theory, Newtonian impact theory, and CFD method are compared in the same motion and Mach number effects. The results indicate that, for this thin double wedge airfoil, Newtonian impact theory is not suitable for these Mach number, while piston theory and Van Dyke’s second-order theory are in good agreement with CFD method for Ma<7.
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48

Zhao, Lian Jin, Jia Lin, Jian Hua Wang, Jin Long Peng, De Jun Qu, and Lian Zhong Chen. "An Experimental Investigation on Transpiration Cooling for Supersonic Vehicle Nose Cone Using Porous Material." Applied Mechanics and Materials 541-542 (March 2014): 690–94. http://dx.doi.org/10.4028/www.scientific.net/amm.541-542.690.

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During hypersonic flight or cruise in the near space, the aerodynamic heating causes a very high temperature on the leading edge of hypersonic vehicles. Transpiration cooling has been recognized the most effective cooling technology. This paper presents an experimental investigation on transpiration cooling using liquid water as coolant for a nose cone model of hypersonic vehicles. The nose cone model consists of sintered porous material. The experiments were carried out in the Supersonic Jet Arc-heated Facility (SJAF) of China Academy of Aerospace Aerodynamics (CAAA) in Beijing. The cooling effect in the different regions of the model was analyzed, and the shock wave was exhibited. The pressure variations of the coolant injection system were continuously recorded. The aim of this work is to provide a relatively useful reference for the designers of coolant driving system in practical hypersonic vehicles.
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49

Liu, Hongkang, Chao Yan, Yatian Zhao, and Yupei Qin. "Uncertainty and sensitivity analysis of flow parameters on aerodynamics of a hypersonic inlet." Acta Astronautica 151 (October 2018): 703–16. http://dx.doi.org/10.1016/j.actaastro.2018.07.011.

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50

Wang, Xiaoguang, Miaojiao Peng, Zhenghong Hu, Yueshi Chen, and Qi Lin. "Feasibility investigation of large-scale model suspended by cable-driven parallel robot in hypersonic wind tunnel test." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 13 (August 8, 2016): 2375–83. http://dx.doi.org/10.1177/0954410016662067.

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Cable-driven parallel robot is a special kind of robot, which is actuated by cables. It is already applied in the low speed wind tunnel to get aerodynamic measurement of aircraft model, and the aircraft pose could be adjusted by changing the cable length. Whether it can be used in hypersonic wind tunnel still needs further discussion. This paper presents the dynamics and aerodynamics analysis of a large-scale model supported by 6-DOF cable-driven parallel robot to investigate the feasibility of this special kind of suspension system in hypersonic wind tunnel. The description of this setup with a X-51A-like model is given, and then based on the system dynamic equations, aerodynamic force and stiffness matrix are derived. In the simulation, properties of dynamics and aerodynamics are mainly concerned. A typical shock tunnel with flow duration of about 100 milliseconds is taken as an example, and results show that the system is stable enough to meet the fundamental static wind tunnel test. From the cable tension variation under impact load and the sensitivity analysis, it is likely accessible to derive the aerodynamic forces. Compared with the sting suspension method, cable-driven parallel robot has the priority of higher inherent frequency and more flexible degrees. The interference to the flow field induced by cables is also preliminarily proved to be small by the CFD simulation, which can be acceptable and corrected. Researches conducted show the feasibility of cable-driven parallel robot’s application in hypersonic wind tunnel.
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