Journal articles: 'Hypersonic Aerodynamics'

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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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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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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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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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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D’Oriano, Vera, Raffaele Savino, and Michele Visone. "Aerothermodynamic study of a small hypersonic plane." Aircraft Engineering and Aerospace Technology 90, no. 2 (March 5, 2018): 471–80. http://dx.doi.org/10.1108/aeat-06-2015-0151.

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Purpose This paper aims to present an aerothermodynamic analysis of a new concept of a small hypersonic airplane. Aerodynamics characteristics for different flow conditions encountered during the missions are analyzed. The effects of elevons deflection for pitch control and of the presence of engines on aerodynamic performances are also investigated for different flight conditions. The effects of boundary layer laminar–turbulent transition on aerodynamic heating are studied to preliminarily identify proper materials that can sustain the hypersonic phase. Design/methodology/approach Aerodynamic characteristics are predicted by means of the semi-empirical aerodynamic prediction code Missile DATCOM and computational fluid dynamics simulations. Computational fluid dynamics analysis is also performed to investigate aerodynamic heating phenomenon. Findings Major discrepancies between the results offered by the two methods have been registered in transonic regime, whereas in subsonic and super-hypersonic conditions, Missile DATCOM confirms to be a suitable tool for preliminary design steps. The results of the analysis show that for the identification of the materials that can sustain the hypersonic phase, the turbulent solution must be taken into account. Carbon fiber reinforced ceramics composite materials seem particularly well suited for the nose, wing and vertical tail leasing edges and control surfaces, while titanium alloys could be used for the rest of the vehicle surface. Originality/value This new concept of vehicle is designed both for point-to-point medium range hypersonic transportation and long duration suborbital space tourism missions, by integrating available technologies developed for aeronautical and space systems.

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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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8

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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9

Hutt, G. R., and R. A. East. "Static and dynamic pitch stability of a blunted cone with forward facing aerodynamic spike in hypersonic flow." Aeronautical Journal 89, no. 888 (October 1985): 307–14. http://dx.doi.org/10.1017/s0001924000015074.

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This paper presents experimental data highlighting the effects of a forward facing aerodynamic spike on the pitch stability of a blunted cone in hypersonic flow. Spike length and angle of attack variations on stability derivatives are described. Suitable application of the inviscid embedded Newtonian pitch stability prediction technique shows how the influence of spike aerodynamics may be successfully modelled. The paper extends the knowledge of aerodynamic spike flow effects, which have to date concentrated on aerodynamic drag reduction qualities at zero degrees angle of attack.

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10

Zhang, Xi-bin, and Qun Zong. "Modeling and Analysis of an Air-Breathing Flexible Hypersonic Vehicle." Mathematical Problems in Engineering 2014 (2014): 1–9. http://dx.doi.org/10.1155/2014/264247.

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By using light-weighted material in hypersonic vehicle, the vehicle body can be easily deformed. The mutual couplings in aerodynamics, flexible structure, and propulsion system will bring great challenges for vehicle modeling. In this work, engineering estimated method is used to calculate the aerodynamic forces, moments, and flexible modes to get the physics-based model of an air-breathing flexible hypersonic vehicle. The model, which contains flexible effects and viscous effects, can capture the physical characteristics of high-speed flight. To overcome the analytical intractability of the model, a simplified control-oriented model of the hypersonic vehicle is presented with curve fitting approximations. The control-oriented model can not only reduce the complexity of the model, but also retain aero-flexible structure-propulsion interactions of the physics-based model and can be applied for nonlinear control.

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11

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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12

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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13

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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14

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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15

Bibin, John, and Kulkarni Vinayak. "Investigation of Energy Deposition Technique for Drag Reduction at Hypersonic Speeds." Applied Mechanics and Materials 367 (August 2013): 222–27. http://dx.doi.org/10.4028/www.scientific.net/amm.367.222.

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Reduction in aerodynamic heating is the major design concern for hypersonic or hypervelocity vehicles which makes typical configurations blunt nosed for this flow regime. These blunt configurations make the space flight costlier due to higher wave drag. Therefore development and optimization of drag reduction techniques is the field of investigation and research in the area of hypersonic aerodynamics. The present work focuses on the investigation of concentrated energy addition technique for drag reduction. An in-house developed high precision compressible flow solver has been employed for the computational investigation of this technique. Parametric studies are carried out to investigate the effect of strength of energy source, location of energy addition and size of energy source.

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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

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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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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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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20

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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21

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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22

Munk, David J., Gareth A. Vio, and Dries Verstraete. "A Hypersonic Aircraft Optimization Tool with Strong Aerothermoelastic Coupling." Applied Mechanics and Materials 846 (July 2016): 494–99. http://dx.doi.org/10.4028/www.scientific.net/amm.846.494.

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The design and optimization of hypersonic aircraft is severely impacted by the high temperatures encountered during flight as they can lead to high thermal stresses and a significant reduction in material strength and stiffness. This reduction in rigidity of the structure requires innovative structural concepts and a stronger focus on aerothermoelastic deformations in the early design and optimization phase of the design cycle. This imposes the need for a closer coupling of the aerodynamic, thermal and structural design tools than is currently in practice. The paper presents a multi-disciplinary, closely coupled optimization suite that is suitable for preliminary design in the hypersonic regime. The time varying temperature distribution is applied through an equilibrium analysis, and is coupled to the aerodynamics through the Tranair® solver. An analysis of the effect that the aerothermodynamic coupling has on the sizing of the aircraft is given, along with the effect of skin buckling. It is shown that the coupling of the aerothermodynamics drives the sizing of the structure and therefore must be considered for hypersonic applications.

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23

Gao, Yidi. "A design review on hypersonic aerodynamics configurations and applicability to hypersonic transports." Theoretical and Natural Science 11, no. 1 (November 17, 2023): 127–34. http://dx.doi.org/10.54254/2753-8818/11/20230391.

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As the world of commercial aviation recovers from the global recession after the pandemic, demands for faster and more reliable air transportation are on the rise. Research in Hypersonic Transports, led by both government and private sectors, aims to revolutionize the industry with its high time efficiency and customizability for various needs. This paper reviews the design principle and challenges of HST from a technical standpoint, while overviewing high-speed gas dynamics, analyzing the waverider configurations, and addressing the technical intricacies of designing a hypersonic vehicle. It shows that the waverider configuration is a suitable HST candidate for its large fuel storage and high inlet compatibility for an airframe-propulsion integrated design. This paper aims to provide holistic context for the advantages and challenges associated with HST, while providing insights into the compatibility of a waverider configuration that can be optimized for civilian transport applications.

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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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25

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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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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27

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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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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29

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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Furudate, Michiko Ahn. "MC-New: A Program to Calculate Newtonian Aerodynamic Coefficients Based on Monte-Carlo Integration." Aerospace 9, no. 6 (June 20, 2022): 330. http://dx.doi.org/10.3390/aerospace9060330.

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A computer program, MC-New, to calculate Newtonian aerodynamics is presented. The aerodynamic coefficients of a geometry expressed by an analytic function are calculated in a Monte-Carlo integration manner, in which the local forces on the randomly chosen sample points are summed up. The verification study and the accuracy analysis show that the program can provide good approximations of exact solutions. The example results of the parametric study on the Apollo-like entry capsule geometry are presented, showing the potential capability of the MC-New program as an efficient open-source tool for designing hypersonic vehicles.

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Mateescu, Dan. "Explicit Exact and Third-Order-Accurate Pressure-Deflection Solutions for Oblique Shock and Expansion Waves." Open Aerospace Engineering Journal 3, no. 1 (February 18, 2010): 1–8. http://dx.doi.org/10.2174/1874146001003010001.

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This paper presents explicit analytical solutions of the pressure coefficient and the pressure ratio across the oblique shock and expansion waves in function of the flow deflection angle. These new explicit pressure-deflection solutions can be efficiently used in solving applied aerodynamic problems in supersonic flows, such as the aerodynamics of airfoils and wings in supersonic-hypersonic flows and the shock and expansion waves interactions, and can be also used to increase the computational efficiency of the numerical methods based on the Riemann problem solution requiring the pressure-deflection solution of the oblique shock and expansion waves, such as the Godunov method.

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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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Guo, Jinghui, Guiping Lin, Xueqin Bu, Shiming Fu, and Yanmeng Chao. "Effect of static shape deformation on aerodynamics and aerothermodynamics of hypersonic inflatable aerodynamic decelerator." Acta Astronautica 136 (July 2017): 421–33. http://dx.doi.org/10.1016/j.actaastro.2017.03.019.

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Feng, Yi, Wei Tang, and Yewei Gui. "Aerodynamic configuration optimization by the integration of aerodynamics, aerothermodynamics and trajectory for hypersonic vehicles." Chinese Science Bulletin 59, no. 33 (July 16, 2014): 4608–15. http://dx.doi.org/10.1007/s11434-014-0534-9.

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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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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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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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Boyi, Chen, Liu Yanbin, Shen Haidong, and Lu Yuping. "Surrogate modeling of a 3D scramjet-powered hypersonic vehicle based on screening method IFFD." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 2 (August 6, 2016): 265–78. http://dx.doi.org/10.1177/0954410016636161.

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The emphasis of this paper lies in the development of an efficient approach to reproduce the behaviors of the scramjet-powered hypersonic system with high fidelity. The modeling of the dual-mode scramjet powered hypersonic vehicle dynamics with shock interaction, Ram-to-Scram transition, and finite rate chemistry reaction is firstly introduced. The structure of surrogate model is identified with the implement of iterative fractional factorial design (IFFD). In order to declare the reliability of the surrogate models, ν-gap metric is applied to distinguish the difference among these surrogate models in terms of closed-loop performance. The results show that the influence of Mach number on the aerodynamics should not be overlooked, and the effect of propulsion system to the aerodynamic pitch moment is dramatic. Further, the partial Kriging model appears to have the closest plants throughout the flight envelope compared with the full Kriging model and polynomials model. Nevertheless, considering the briefness of analytical expression, the polynomials model may be an alternative approach for design-oriented modeling.

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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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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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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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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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Witcher, Kenneth, Ian McAndrew, and Elena Vishnevskaya. "Aerodynamic Analysis of Low Speed Wing Design using Taguchi L9 Orthogonal Array." MATEC Web of Conferences 151 (2018): 04005. http://dx.doi.org/10.1051/matecconf/201815104005.

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The study of aerodynamics has been preoccupied with understanding flight at increasing speeds and ultimately supersonic. Today, this pursuit has advanced the science for both Hypersonic and Transonic flight to near Mach 1 supporting economical commercial flight operations. This research presents the data from a Taguchi array on low speed with twin wing designs to establish the design parameters for their use in low speed and high altitude. Also presented is how aerodynamic advantages can be achieved through understanding the interactions of parameters and their use. This is compared to operational effectiveness when applied to remotely piloted aircraft that are not constrained by direct requirements. The research concludes with suggestions for improved designs and further work that may enable higher altitudes with low speeds.

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Wang, Liang, Weihua Zhang, Ke Peng, and Donghui Wang. "Adaptive Command Filtered Integrated Guidance and Control for Hypersonic Vehicle with Magnitude, Rate and Bandwidth Constraints." MATEC Web of Conferences 151 (2018): 05004. http://dx.doi.org/10.1051/matecconf/201815105004.

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This paper proposes a novel integrated guidance and control (IGC) method for hypersonic vehicle in terminal phase. Firstly, the system model is developed with a second order actuator dynamics. Then the back-stepping controller is designed hierarchically with command filters, where the first order command filters are implemented to construct the virtual control input with ideal states predicted by an adaptive estimator, and the nonlinear command filter is designed to produce magnitude, rate and bandwidth limited control surface deflection finally tracked by a terminal sliding mode controller with finite convergence time. Through a series of 6-DOF numerical simulations, it’s indicated that the proposed method successfully cancels out the large aerodynamics coefficient uncertainties and disturbances in hypersonic flight under limited control surface deflection. The contribution of this paper lies in the application and determination of nonlinear integrated design of guidance and control system for hypersonic vehicle.

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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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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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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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Chen, Jingfan, Xiaoqiang Fan, Bing Xiong, and Yi Wang. "Shape Optimization of the Cross-Section for Noncircular Hypersonic Missile Forebody." International Journal of Aerospace Engineering 2020 (October 23, 2020): 1–9. http://dx.doi.org/10.1155/2020/8885494.

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In the hypersonic regime, noncircular missiles have attracted significant attention from researchers. The paper first summarizes the development and present situation of the noncircular missiles at home and abroad. Previous research found that the cross-section shape of missiles has a direct influence on the aerodynamics performance. To find the best cross-section shape in terms of lift-drag-ratio, an efficient and robust shape optimization framework is developed. Class/shape function transformation (CST) method and power-law curve are introduced to complete the parametric modeling of the noncircular missile. The evolutionary algorithm has been utilized to improve the optimization efficiency. A combination of script and journal files is written to automate the CAD loft, mesh generation, and CFD simulations process. Finally, the forebody section of a missile body is chosen as an example to deliver the whole optimization steps. The optimization results show that the lift-to-drag ratio increases from 1.8 to 2.4 when the hypersonic missile forebody cruises at the design condition. The results also demonstrate that the optimized configuration has a better aerodynamic performance than the original one over a wide speed range from Mach 2 to 8 and a wide attack of angle range from 0 to 30.

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Blankson, I. M. "Air-Breathing Hypersonic Cruise: Prospects for Mach 4–7 Waverider Aircraft." Journal of Engineering for Gas Turbines and Power 116, no. 1 (January 1, 1994): 104–15. http://dx.doi.org/10.1115/1.2906779.

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There is currently a renewal of world-wide interest in hypersonic flight. Vehicle concepts being considered range from cruise missiles to SSTO and TSTO vehicles. The new characteristics of these vehicles are that they will be powered by air-breathing engines and have long residence times in the air-breathing corridor. In the Mach 4–7 regime, waverider aircraft are being considered as candidates for both long-range and short-range cruise missions, as hypersonic missiles, and as high-L/D highly maneuverable vehicles. This paper will discuss the potential for near-term and far-term application of air-breathing engines to the above-mentioned waverider vehicle concepts and missions. In particular, the cruise mission is discussed in detail and attempts are made to compare and contrast it with the accelerator mission. Past criticisms levied against waveriders alleging low volumetric efficiency, lack of engine/airframe integration studies, poor off-design performance, poor take-off and landing capability, have been shown by ongoing research to be unfounded. A discussion is presented of some of the technical challenges and ongoing research aimed at realizing such vehicles: from turboramjet and scramjet technology development, propulsion-airframe integration effects on vehicle performance, aeroservothermoelastic systems analysis, hypersonic stability and control with aeroservothermoelastic and propulsion effects, etc. A unique and very strong aspect of hypersonic vehicle design is the integration and interaction of the propulsion system, aerodynamics, aerodynamic heating, stability and control, and materials and structures. This first-order multidisciplinary situation demands the ability to integrate highly coupled and interacting elements in a fundamental and optimal fashion to achieve the desired performance. Some crucial technology needs are found in propulsion-airframe integration and its role in configuration definition, hypersonic boundary-layer transition and its impact on vehicle gross-weight and mission success, scramjet combustor mixing length and its impact on engine weight and, CFD (turbulence modeling, transition modeling, etc) as a principal tool for the design of hypersonic vehicles. Key technology implications in thermal management, structures, materials, and flight control systems will also be briefly discussed. It is concluded that most of the technology requirements in the Mach 4–7 regime are relatively conventional, making cited applications near-term, yet offering very significant advancements in aircraft technology.

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Jin, Yunjuan, Aifang Qu, and Hairong Yuan. "Radon measure solutions for steady compressible hypersonic-limit Euler flows passing cylindrically symmetric conical bodies." Communications on Pure & Applied Analysis 20, no. 7-8 (2021): 2665. http://dx.doi.org/10.3934/cpaa.2021048.

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<p style="text-indent:20px;">We study steady uniform hypersonic-limit Euler flows passing a finite cylindrically symmetric conical body in the Euclidean space <inline-formula><tex-math id="M1">\begin{document}$ \mathbb{R}^3 $\end{document}</tex-math></inline-formula>, and its interaction with downstream static gas lying behind the tail of the body. Motivated by Newton's theory of infinite-thin shock layers, we propose and construct Radon measure solutions with density containing Dirac measures supported on surfaces and prove the Newton-Busemann pressure law of hypersonic aerodynamics. It happens that if the pressure of the downstream static gas is quite large, the Radon measure solution terminates at a finite distance from the tail of the body. The main difficulty of the analysis is a correct definition of Radon measure solutions. The results are helpful to understand mathematically some physical phenomena and formulas about hypersonic inviscid flows.</p>

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Journal articles on the topic 'Hypersonic Aerodynamics'

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