Design of three-dimensional hypersonic inlets with rectangular to elliptical shape transition

36th AIAA Aerospace Sciences Meeting and Exhibit

Volumn , Issue , 1998, Pages

  Smart, M K ^a,b  

^a NASA LANGLEY RESEARCH CENTER   (United States)

^b NATIONAL RESEARCH COUNCIL   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

AEROSPACE ENGINEERING; BOUNDARY LAYERS; DESIGN; HYPERSONIC FLOW; SHOCK WAVES;

BOUNDARY-LAYER SEPARATION; DESIGN PROCEDURE; ELLIPTICAL SHAPES; SHAPE TRANSITIONS; SHOCK WAVE INTERACTION; THREE-DIMENSIONAL DISPLACEMENTS; TOTAL PRESSURE RECOVERY; TWO-DIMENSIONAL INLETS;

HYPERSONIC INLETS;

EID: 84983157638     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: None     Document Type: Conference Paper

References (17)

1. Hartill, W. B., "Analytical and experimental investigation of a scramjet inlet of quadriform shape," Tech Rep. AFAPL-TR-65-74, U. S. Airforce, August 1965, Marquardt Corporation.
2. Heirsey, J. L. and Snow, M. L., "Modular inlet investigation," Quarterly Report AQR/66-1, Aeronautics Division, Research and Development, Applied Physics Laboratory, Johns Hopkins University, January-March, 1966.
3. Kutshenreuter, P. H., "Hypersonic inlet tests in helium and air," General Electric Company Advanced Engine and Technology Departments, Cincinnati, Ohio; presented at the AIAA Propulsion Joint Specialist Conference, The Unites States Air Force Academy, Colorado, June 14-18, 1965.
4. Kantrowitz, A. and Donaldson, C., "Preliminary investigation of supersonic diffusers," NACA ACR No. L5D20, 1945.
5. Simmons, J. M. and Weidner, E. H., "Design of scramjet inlets with rectangular to circular shape transition," NASA TM No. 87752, June 1986.
6. Billig, F. S., "Supersonic Combustion Ramjet Missile," Journal of Propulsion and Power, Vol. 11, No. 6, pp 1139-1146, 1995.
7. Smart, M. K., "Calculation of streamtraced hypersonic inlet performance on and off design," paper No. 5330, 21st International Symposium on Shock Waves, Great Keppel, Australia, July 1997.
8. Salas, M. D., "Shock fitted method for complicated two-dimensional supersonic flows," AIAA Journal, vol. 14, No. 5, pp 583-588, 1976.
9. Amtec Engineering TECPLOT™ version 6 Users Manual, Amtec Engineering Inc, 1993.
10. Barger, R. L., "A procedure for designing forebodies with constraints on cross-section shape and axial area distribution," NASA TP 1881, 1981.
11. Korkegi, R. H., "Comparison of shock induced two and three-dimensional incipient turbulent separation," AIAA Journal, Vol. 13, No. 4, pp534-535, 1975.
12. Aerosoft Inc. GASP version 3 Users Manual, Aerosoft Inc, Blacksburg, Virginia, 1996.
13. Singh, D. J., Trexler, C. A. and Young, J. A., "Threedimensional simulation of a translating strut inlet," Journal of Propulsion and Power, Vol. 10, No. 2, pp 191-197, 1994.
14. Cebeci, T. and Bradshaw, P, "Physical and Computational Aspects of Convective Heat Transfer," Springer-Verlag, New York, 1994.
15. Keller, H. B., "A new difference scheme for parabolic problems"; in Numerical Solution of Partial Differential Equations (J. Bramble, ed.), Vol. 2, Academic, New York, 1970.
16. Cebeci, T. and Smith, A. M. O., "Analysis of Turbulent Boundary Layers," Academic, New York, 1974.
17. Molder, S., McGregor, R. J., and Paisley, T. W., "A comparison of three hypersonic inlets"; section 6 of "Investigations in the fluid mechanics of scramjet inlets," U. S. Airforce Report WL-TR-2091, 1993.