Log in

Relevant bibliographies by topics / Hypersonic Aerodynamics

Contents

Journal articles
Dissertations / Theses
Books
Book chapters
Conference papers
Reports

Academic literature on the topic 'Hypersonic Aerodynamics'

Author: Grafiati

Published: 4 June 2021

Last updated: 29 July 2024

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

Select a source type:

Consult the lists of relevant articles, books, theses, conference reports, and other scholarly sources on the topic 'Hypersonic Aerodynamics.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Journal articles on the topic "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.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

3

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.

Full text

APA, Harvard, Vancouver, ISO, and other styles

4

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

5

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

6

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

7

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

More sources

Dissertations / Theses on the topic "Hypersonic Aerodynamics"

1

Khorrami, Ahmad Farid. "Hypersonic aerodynamics on flat plates and thin aerofoils." Thesis, University of Oxford, 1991. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.292584.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

Hunt, Dillon C. "Measurement of ablation in transient hypersonic flows /." St. Lucia, Qld, 2001. http://www.library.uq.edu.au/pdfserve.php?image=thesisabs/absthe16475.pdf.

Full text

APA, Harvard, Vancouver, ISO, and other styles

3

Singh, Amarjit. "Experimental study of slender vehicles at hypersonic speeds." Thesis, Cranfield University, 1996. http://hdl.handle.net/1826/4257.

Full text

Abstract:

An experimental investigation of the hypersonic flow over (i) a wing-body configuration, (ii) a hemi-spherically blunted cone-cylinder body and (iii) a one-half- power-law body has been conducted for M,, = 8.2 and Re,, = 9.35x104 per cm. The tests were performed at model incidences, a=0,5 and 10° for flap deflection angles, (3 = 0,5,15, and 25° for the wing-body. The incidence ranged from -3 to 10° for the cone- cylinder and -5 to 15° for the power-law body. (i) The schlieren pictures showing top and side views of the model indicate that the body nose shock does not intersect the wing throughout the range of a under investigation. Detailed pressure measurements on the lower surface of the wing and flap along with the liquid crystal pictures suggest that the body nose shock does not strike the flap surfaces either. The wing leading edge shock is found to be attached at a=0 and 5° but detached at a= 10°. The liquid crystal pictures and surface pressure measurements indicated attached flow on the lower surface of the wing and flap for 13 =0 and 5° at all values of a under test. However at a= 0°, as the flap angle is increased to 15° the flow separates ahead of the hinge line. As incidence is increased the boundary layer becomes transitional giving rise to complex separation patterns around the flap hinge line. The spherically blunted body nose causes strong entropy layer effects over the wing and the trailing edge flap. A Navier-Stokes solution indicated a thick entropy layer of approximately constant thickness all around the cylindrical section of the body at zero incidence. However, at an incidence of 10° the layer tapers and becomes thinner under the body. The surface pressure over the wing and the plateau pressure for separated flow was found to increase from the root to the tip. This is partly because of the decrease in local Reynolds number across the span, however in the present case, entropy layer effects also affected separation. The entropy layer effects were found to reduce the peak pressures obtainable on the flap. The peak pressures, over the portion of the flap unaffected by entropy layer effects, could be estimated assuming quasi two dimensional flow. (ii) Force measurements were made for the blunted cone-cylinder alone as well as with the delta wing, with trailing-edge flap, attached to it. The lift, drag, and pitching moment characteristics for the cone-cylinder agree reasonably well with the modified Newtonian theory and the N-S results. The addition of a wing to the cone-cylinder body increases the lift as weil as the drag coefficient but there is an overall increase in the lift/drag ratio. The deflection of a flap from 0° to 25° increases the lift and drag coefficients at all the incidences tested. However, the lift/drag ratio is reduced showing the affects of separation over the wing. The experimental results on the wing-body are compared with the theoretical estimates based upon two-dimensional shock-expansion theory. (iii) The lift, and drag characteristics of a one-half-power-law body are compared with other existing results. The addition of strakes to the power-law body are found to improve its aerodynamic efficiency without any significant change in its pitching moment characteristics.

APA, Harvard, Vancouver, ISO, and other styles

4

Robinson, Matthew J. "Simultaneous lift, moment and thrust measurement on a scramjet in hypervelocity flow /." [St. Lucia, Qld.], 2003. http://www.library.uq.edu.au/pdfserve.php?image=thesisabs/absthe17611.pdf.

Full text

APA, Harvard, Vancouver, ISO, and other styles

5

Babinsky, Holger. "A study of roughness in turbulent hypersonic boundary-layers." Thesis, Cranfield University, 1993. http://dspace.lib.cranfield.ac.uk/handle/1826/7586.

Full text

Abstract:

The influence of large scale regular roughness on a Mach 5 turbulent boundary layer and a compression corner was investigated on axisymmetric wind tunnel models. Three types of roughness were examined; a series of square cavities at two different sizes and a 45 degree sawtooth. Typical sizes ranged from 50% to 100% of an undisturbed boundary layer thickness. The roughness was limited to a short region followed by a smooth surface. Compression corners were formed by 15° and 20° flares located downstream of the roughness. The flow in the wind tunnel was investigated in detail to obtain knowledge on operating conditions and flow quality. Liquid crystal thermography was developed for routine use in hypersonic blow-down wind tunnels with superior spatial resolution and experimental uncertainties in the range of traditional techniques. The effect on flow parameters downstream of the last roughness element were 7, found to differ significantly for the different quantities. Velocity profiles were found i, to be less full and skin friction was found to be reduced for all streamwise "~ distances. Surface heat transfer was increased in a short region limited to 1.5 boundary layer thicknesses behind the roughness whereas surface pressure was not affected. Sawtooth shaped roughness was found to cause a stronger j disturbance than square cavities of twice the size. Little influence of the roughness was noted on the flow over the compression corner. The flow over the 20° compression corner showed an increase in upstream influence for the sawtooth shaped roughness as well as the larger cavities. Surface pressure measurements did not indicate a separation in any case. Heat transfer measurements revealed a peak located approximately 0.25 boundary layer thicknesses behind the corner. No such feature was found in the surface pressure distributions. It is suggested that a small scale separation is located very close to the corner causing the peak in heat transfer at reattachment without any effect on surface pressures. The existence of such a separation has been confirmed by surface flow visualisations for both flares.

APA, Harvard, Vancouver, ISO, and other styles

6

Asproulis, Panagiotis. "High resolution numerical predictions of hypersonic flows on unstructured meshes." Thesis, Imperial College London, 1994. http://hdl.handle.net/10044/1/8357.

Full text

APA, Harvard, Vancouver, ISO, and other styles

7

Surah, Davinder. "Investigation of attachment line boundary layer characteristics in hypersonic flows." Thesis, Cranfield University, 2000. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.323921.

Full text

APA, Harvard, Vancouver, ISO, and other styles

8

Atcliffe, Phillip Arthur. "Effects of boundary layer separation and transition at hypersonic speeds." Thesis, Cranfield University, 1995. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.336458.

Full text

APA, Harvard, Vancouver, ISO, and other styles

9

Wilson, Althea Grace. "Numerical study of energy utilization in nozzle/plume flow-fields of high-speed air-breathing vehicles." Diss., Rolla, Mo. : Missouri University of Science and Technology, 2008. http://scholarsmine.mst.edu/thesis/pdf/Wilson_09007dcc804d881b.pdf.

Full text

Abstract:

Thesis (M.S.)--Missouri University of Science and Technology, 2008.
Vita. The entire thesis text is included in file. Title from title screen of thesis/dissertation PDF file (viewed April 25, 2008) Includes bibliographical references (p. 57).

APA, Harvard, Vancouver, ISO, and other styles

10

Modlin, James Michael. "Hypersonic aerospace vehicle leading edge cooling using heat pipe, transpiration and film cooling techniques." Diss., Georgia Institute of Technology, 1991. http://hdl.handle.net/1853/16347.

Full text

APA, Harvard, Vancouver, ISO, and other styles

More sources

Books on the topic "Hypersonic Aerodynamics"

1

K, Notestine Kristopher, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. Aerodynamic pressure and heating-rate distributions in tile gaps around chine regions with pressure gradients at a Mach number of 6.6. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

2

HEPPENHEIMER, T. A. Hypersonic technologies. Arlington, Va: Pasha Publications, 1993.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

3

Park, Chul. Nonequilibrium hypersonic aerothermodynamics. New York: Wiley, 1990.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

4

S, Murthy T. K., ed. Computational methods in hypersonic aerodynamics. Southampton: Computational Mechanics Publications, 1991.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

5

Utyuzhnikov, Sergey V. Hypersonic aerodynamics and heat transfer. New York: Begell, 2014.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

6

North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Aerodynamics of Hypersonic Lifting Vehicles. S.l: s.n, 1987.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

7

N, Pessin David, and Ames Research Center, eds. Aerodynamic analysis of hypersonic waverider aircraft. San Luis Obispo, CA: Cal Poly State University, 1993.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

8

Radespiel, R. Progress with multigrid schemes for hypersonic flow problems. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1991.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

9

Anderson, John David. Hypersonic and high temperature gas dynamics. New York: McGraw-Hill, 1989.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

10

Flandro, G. A. Dynamic interactions between hypersonic vehicle aerodynamics and propulsion system performance: Final report to Aircraft Guidance and Controls Branch, Guidance and Control Division ... [Washington, DC: National Aeronautics and Space Administration, 1992.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

More sources

Book chapters on the topic "Hypersonic Aerodynamics"

1

Kaushik, Mrinal. "Hypersonic Flows." In Theoretical and Experimental Aerodynamics, 237–50. Singapore: Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-13-1678-4_10.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

Gülçat, Ülgen. "Hypersonic Flow." In Fundamentals of Modern Unsteady Aerodynamics, 205–58. Singapore: Springer Singapore, 2015. http://dx.doi.org/10.1007/978-981-10-0018-8_7.

Full text

APA, Harvard, Vancouver, ISO, and other styles

3

GÜlçat, Ülgen. "Hypersonic Flow." In Fundamentals of Modern Unsteady Aerodynamics, 209–64. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-60777-7_7.

Full text

APA, Harvard, Vancouver, ISO, and other styles

4

Gülçat, Ülgen. "Hypersonic Flow." In Fundamentals of Modern Unsteady Aerodynamics, 193–244. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-14761-6_7.

Full text

APA, Harvard, Vancouver, ISO, and other styles

5

Viviand, H. "Similitude in Hypersonic Aerodynamics." In Hypersonic Flows for Reentry Problems, 72–97. Berlin, Heidelberg: Springer Berlin Heidelberg, 1991. http://dx.doi.org/10.1007/978-3-642-84580-2_7.

Full text

APA, Harvard, Vancouver, ISO, and other styles

6

Chattot, J. J., and M. M. Hafez. "Introduction to Hypersonic Flows." In Theoretical and Applied Aerodynamics, 399–456. Dordrecht: Springer Netherlands, 2015. http://dx.doi.org/10.1007/978-94-017-9825-9_12.

Full text

APA, Harvard, Vancouver, ISO, and other styles

7

Viviani, Antonio, and Giuseppe Pezzella. "Basics of Hypersonic Aerodynamics and Aerothermodynamics." In Aerodynamic and Aerothermodynamic Analysis of Space Mission Vehicles, 1–125. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-13927-2_1.

Full text

APA, Harvard, Vancouver, ISO, and other styles

8

Hirschel, Ernst Heinrich, and Hans Ulrich Meier. "Aerodynamics — from Near-Sonic to Hypersonic Flight." In Aeronautical Research in Germany, 387–407. Berlin, Heidelberg: Springer Berlin Heidelberg, 2004. http://dx.doi.org/10.1007/978-3-642-18484-0_16.

Full text

APA, Harvard, Vancouver, ISO, and other styles

9

Carlomagno, G. M., L. Luca, and G. Cardone. "Hypersonic Aerodynamics Research with an Infrared Imaging System." In New Trends in Instrumentation for Hypersonic Research, 493–502. Dordrecht: Springer Netherlands, 1993. http://dx.doi.org/10.1007/978-94-011-1828-6_44.

Full text

APA, Harvard, Vancouver, ISO, and other styles

10

Dimitrienko, Yury, Mikhail Koryakov, and Andrey Zakharov. "Application of Finite Difference TVD Methods in Hypersonic Aerodynamics." In Finite Difference Methods,Theory and Applications, 161–68. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-20239-6_15.

Full text

APA, Harvard, Vancouver, ISO, and other styles

Conference papers on the topic "Hypersonic Aerodynamics"

1

COCKRELL, JR., CHARLES, and LAWRENCE HUEBNER. "Generic hypersonic inlet module analysis." In 9th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-3209.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

SOBIECZKY, H. "Generic supersonic and hypersonic configurations." In 9th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-3301.

Full text

APA, Harvard, Vancouver, ISO, and other styles

3

FINLEY, DENNIS. "Hypersonic aerodynamics considerations and challenges." In 2nd International Aerospace Planes Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-5222.

Full text

APA, Harvard, Vancouver, ISO, and other styles

4

Riabov, Vladimir V. "Rarefaction Effects in Hypersonic Aerodynamics." In 27TH INTERNATIONAL SYMPOSIUM ON RAREFIED GAS DYNAMICS. AIP, 2011. http://dx.doi.org/10.1063/1.3562828.

Full text

APA, Harvard, Vancouver, ISO, and other styles

5

Landon, Mark, Darryl Hall, Jerry Udy, and Ernest Perry. "Automatic supersonic/hypersonic aerodynamic shape optimization." In 12th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-1898.

Full text

APA, Harvard, Vancouver, ISO, and other styles

6

Heller, M., F. Holzapfel, and G. Sachs. "Robust lateral control of hypersonic vehicles." In 18th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-4248.

Full text

APA, Harvard, Vancouver, ISO, and other styles

7

Lindblad, I., T. Groenland, J. L. Cambier, S. Wallin, T. Berens, P. Sacher, M. Netterfield, et al. "A study of hypersonic afterbody flowfields." In 15th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-2289.

Full text

APA, Harvard, Vancouver, ISO, and other styles

8

HARLOFF, GARY. "High angle of attack hypersonic aerodynamics." In 5th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2548.

Full text

APA, Harvard, Vancouver, ISO, and other styles

9

HOFFMANN, KLAUS, DENNIS WILSON, and CHARLES HAMBURGER. "Aerothermodynamic analysis of projectiles at hypersonic speeds." In 7th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2185.

Full text

APA, Harvard, Vancouver, ISO, and other styles

10

Li, Suxun, Yongkang Chen, Yulin Li, Suxun Li, Yongkang Chen, and Yulin Li. "Hypersonic flow over double-ellipsoid - Experimental investigation." In 15th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-2287.

Full text

APA, Harvard, Vancouver, ISO, and other styles

Reports on the topic "Hypersonic Aerodynamics"

1

Anderson, Jr, and John D. Hypersonic Aerodynamics Fellowships. Fort Belvoir, VA: Defense Technical Information Center, February 1991. http://dx.doi.org/10.21236/ada233584.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

Anderson, John D., and Jr. Fellowships in Hypersonic Aerodynamics. Fort Belvoir, VA: Defense Technical Information Center, February 1988. http://dx.doi.org/10.21236/ada194265.

Full text

APA, Harvard, Vancouver, ISO, and other styles

3

Munipalli, Ramakanth, Kamesh Subbarao, Shashi Aithal, Donald R. Wilson, and Jennifer D. Goss. Automated Design Optimization for Hypersonic Plasma-Aerodynamics. Fort Belvoir, VA: Defense Technical Information Center, June 2005. http://dx.doi.org/10.21236/ada435356.

Full text

APA, Harvard, Vancouver, ISO, and other styles

4

AIR FORCE TEST PILOT SCHOOL EDWARDS AFB CA. Volume 1. Aircraft Performance. Chapter 10. Hypersonic Aerodynamics. Fort Belvoir, VA: Defense Technical Information Center, April 1987. http://dx.doi.org/10.21236/ada320212.

Full text

APA, Harvard, Vancouver, ISO, and other styles

5

Kirsch, Jared, Blake Lance, Aaron Krueger, and Brian Freno. Expanded verification and validation studies of hypersonic aerodynamics with multiple physics-fidelity models. Office of Scientific and Technical Information (OSTI), June 2023. http://dx.doi.org/10.2172/2248032.

Full text

APA, Harvard, Vancouver, ISO, and other styles

6

Witzeman, F. Magneto-Aerodynamic Hypersonics. Fort Belvoir, VA: Defense Technical Information Center, December 2003. http://dx.doi.org/10.21236/ada419720.

Full text

APA, Harvard, Vancouver, ISO, and other styles

7

Bowersox, Rodney D., and Huaiguo Fan. Investigation of Combined Low-Angled Jets and Variable Wall Geometry for Hypersonic Aerodynamic Control. Fort Belvoir, VA: Defense Technical Information Center, November 2000. http://dx.doi.org/10.21236/ada384726.

Full text

APA, Harvard, Vancouver, ISO, and other styles

We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!