Hostname: page-component-cd9895bd7-p9bg8 Total loading time: 0 Render date: 2024-12-22T10:18:32.942Z Has data issue: false hasContentIssue false
  • English
  • Français

Heat alleviation studies on hypersonic re-entry vehicles

Published online by Cambridge University Press:  15 November 2018

M. Khalid  and
K. A. Juhany Open the ORCID record for K. A. Juhany [Opens in a new window]
M. Khalid*
Affiliation:
Department of Aeronautical EngineeringKing Abdul Aziz UniversityJeddahSaudi Arabia
K. A. Juhany
Affiliation:
Department of Aeronautical EngineeringKing Abdul Aziz UniversityJeddahSaudi Arabia
*
*[email protected]
Get access Rights & Permissions [Opens in a new window]

Abstract

A numerical simulation has been carried out to investigate the effects of leading edge blowing upon heat alleviation on the surface of hypersonic vehicles. The initial phase of this work deals with the ability of the present CFD-based techniques to solve hypersonic flow field past blunt-nosed vehicles at hypersonic speeds. Towards this end, the authors selected three re-entry vehicles with published flow field data against which the present computed results could be measured. With increasing confidence on the numerical simulation techniques to accurately resolve the hypersonic flow, the boundary condition at the solid blunt surface was then equipped with the ability to blow the flow out of the solid boundary at a rate of at least 0.01–0.1 times the free stream (ρ∞u∞) mass flow rate. The numerical iterative procedure was then progressed until the flow at the surface matched this new ‘inviscid like’ boundary condition. The actual matching of the flow field at the ejection control surface was achieved by iterating the flow on the adjacent cells until the flow conformed to the conditions prescribed at the control surface. The conditions at the surface could be submitted as a ρ∞u∞ at the surface or could be equipped as a simple static pressure condition providing the desired flow rate. The comparison between the present engineering approach and the experimental data presented in this study demonstrate its ability to solve complex problems in hypersonic.

Keywords

Hypersonic flowheat transfer studiescomputational fluid dynamicsre-entry vehiclesfluid injectionstrong shock effects
Type
Research Article
Information
The Aeronautical Journal , Volume 122 , Issue 1257 , November 2018 , pp. 1673 - 1696
Copyright
© Royal Aeronautical Society 2018 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Hankey, W.L. Re-Entry Aerodynamics, 1988, AIAA Education Series, American Institute of Aeronautics and Astronautics, Washington, DC, USA.Google Scholar
2. Stumpf, D. K. Titan II – A History of Cold War Program, University of Arkansas Press, Fayetteville, USA, 2000.Google Scholar
3. Kattari, G. E. Effects of Mass Addition on Blunt-Body Boundary-Layer Transition and Heat Transfer, NASA Technical Paper 1139, Ames Research Center, Moffett Field, California, 1978.Google Scholar
4. Zhang, M., Xiang, S. and Tong, J. Film Cooling Effectiveness for Hypersonic Vehicles, The 22nd International Conference on Sound and Vibration, 12-16 July 2015, Florence, Italy.Google Scholar
5. Juhany, A. K., Hunt, M. L. and Sivo, J. M. Influence of Injectant Mach Number and Temperature on Supersonic Film Cooling, J of Thermophysics and Heat Transfer, Jan-March, 1994, 8, (1), 59–67.Google Scholar
6. Pappas, C. C. and Okuno, A. F. The Relation between Skin Friction and Heat Transfer for the Compressible Turbulent Boundary Layer with Gas Injection, NASA TN D 2857.Google Scholar
7. Glass, D. E., Dilley, A. D. and Kelly, H. N. Numerical Analysis of Convection/Transpiration Cooling, NASA/TM-1999-209828, NASA, Hampton, Virginia, December 1999.Google Scholar
8. Brune, A., Hosder, S., Gulli, S. and Maddalena, L. Variable transpiration cooling effectiveness in laminar and turbulent flows for hypersonic vehicles, AIAA J, January 2015, 53, (1), 176–189 Google Scholar
9. Henline, W. D. Transpiration Cooling of Hypersonic Blunt Bodies with Finite Rate Surface Reactions, NASA Contractor Report 177516, February 1989, NASA. Ames research Center, Moffat Field, California, USA.Google Scholar
10. Chen, Y.-K. and Henline, W. D. Hypersonic non-equilibrium Navier–Stokes solutions over an ablating graphite nose tip, J of Spacecraft and Rockets, 1994, 31, (5), 728–734.Google Scholar
11. Mitcheltree, R. A., Moss, J. N., Cheatwood, F. M., Greene, F. A. and Braunq, R. D. Aerodynamics of the Mars Microprobe Entry Vehicles, AIAA Paper 97-3658, 1997.Google Scholar
12. Moss, J. N., Glass, C. E. and Greene, F. A. DSMC Simulations of Apollo Capsule Aerodynamics for Hypersonic Rarefied Conditions, 9th AIAA/ASM Thermophysics and Heat Transfer Conference, 5–8 June, San Francisco, USA.Google Scholar
13. Grundmann, R. Aerothermodynamik, Springer Verlag, Berlin, Germany, 1st ed, Technische Universität Dresden, 2000.Google Scholar
14. Gordon, S. and McBride, B. J. Computer program for calculation of complex chemical equilibrium compositions and applications. Technical report, National Aeronautics and Space Administration, Office of Management, Sciatic and Technical Information Program, 1994.Google Scholar
15. Vinokur, M. Conservation equations of gas dynamics in curvilinear coordinate system, J of Computational Physics, 1974, 14, (2), pp 105–125.Google Scholar
16. Beam, R. and Warming, R. F. An implicit finite difference algorithm for hyperbolic systems in conservation law form, J of Computational Physics, September 1976, 22, (1), pp 87–110.Google Scholar
17. Pulliam, T. and Chaussee, D. S. A diagonal form of an implicit approximate-factorization algorithm, J of Computational Physics, March 1981, 39, (2), pp 347–363.Google Scholar
18. Fay, J. A. and Riddell, F. R. Theory of Stagnation Point Heat Transfer in Dissociated Air, J of the Aeronautical Sciences, Feb. 1958, 25, (2), pp 73–85, 121.Google Scholar
19. Kaatari, G. E. Effects of Mass Addition on Blunt-Body Boundary-Layer Transition and Heat Transfer, NASA Technical Paper 1139, 1978Google Scholar
20. Nowak, R. J. Gas-jet and Tangent Jet-slot Film Cooling Tests of a 12.5o cone at Mach Number 6.7, NASA Technical Paper 2786, May 1988.Google Scholar
21. Belotserkovskii., O. M. and Chushkin, M. I. [1961] Hypersonic flow past Blunt Cones. Fluid Dynamics Symposium, Jablona, September 1961.Google Scholar
22. Bertin, J. The effect of Protuberances, Cavities, and Angle of Attack on the Wind Tunnel Pressure and Heat Transfer Distribution for the Apollo Command Module, NASA TM X 1243, Manned Space Craft Center, Houston, Texas, 1966.Google Scholar
23. https://en.wikipedia.org/wiki/NASA_X-38 Google Scholar
24. Ludeke, H. and Krogmann, P. Numerical and Experimental Investigation of Laminar and Turbulent Boundary Layer Transition, European Congress on Computational Methods in Applied Sciences and Engineering, 11–14 September 2000, ECCOMAS 2000.Google Scholar