Incipient separation on flared bodies at hypersonic speeds

Aeronautical Journal

Volumn 103, Issue 1027, 1999, Pages 405-414

  Kontis, K ^a   Stollery, J L ^b  

^a NAGOYA UNIVERSITY   (Japan)

^b CRANFIELD UNIVERSITY   (United Kingdom)

Author keywords

[No Author keywords available]

Indexed keywords

BOUNDARY LAYER FLOW; CYLINDERS (SHAPES); ENTROPY; FLOW VISUALIZATION; LAMINAR FLOW; NOSE CONES; PRESSURE MEASUREMENT; REYNOLDS NUMBER; SHOCK WAVES; TURBULENT FLOW;

FLARED BODIES; INCIPIENT FLOW SEPARATION;

HYPERSONIC AERODYNAMICS;

EID: 0033338981     PISSN: 00019240     EISSN: None     Source Type: Trade Journal    
DOI: 10.1017/S0001924000027950     Document Type: Article

References (46)

1. COLEMAN, G.T. and STOLLERY, J.L. Incipient separation of axially symmetric hypersonic turbulent boundary layers, AIAA J, January 1974, 12, pp 119-120.
2. KUEHN, D.M. Laminar boundary-layer separation induced by flares on cylinders with highly cooled boundary layers at a Mach number of 15, NASA TN D-2610, 1965.
3. KUEHN, D.M. Turbulent boundary-layer separation induced by flares on cylinders at zero angle of attack, NASA TR-R-117, 1961.
4. KUEHN, D.M. Laminar boundary-layer separation induced by flares on cylinders at zero angle of attack. NASA TR-R-146, 1962.
5. GRAY, J. Investigation of the effect of flare and ramp angle on the upstream influence of laminar and transitional reattaching flows from Mach 3 to 7, AEDC TR-66-190, 1967.
6. GINOUX, J.J. On some properties of reattaching laminar and transitional high speed flows, VKI TN-53, 1969.
7. NEEDHAM, D.A. and STOLLERY, J.L. Boundary layer separation in hypersonic flow, AIAA-66-455, 1966.
8. INGER, G.R. Scaling of incipient separation in high speed laminar flows, AIAA-93-3435, 1993.
9. COLEMAN, G.T. and STOLLERY, J.L. Heat transfer from hypersonic turbulent flow at a wedge compression corner, J Fluid Mech, 1972, 56, (4), pp 741-752.
10. ELFSTROM, G.M. Turbulent separation in hypersonic flow, IC Aero Report 71-16, 1971.
11. COLEMAN, G.T. A study of hypersonic boundary layers over a family of axisymmetric bodies at zero incidence, IC Aero Report 73-06, 1973.
12. STOLLERY, J.L. and BATES, L. Turbulent hypersonic viscous interaction, J Fluid Mech, 1974, 63, (1), pp 145-156.
13. VERMEULEN, J.P. and SIMEONIDES, G. Parametric studies of shockwave boundary layer interactions in two dimensional compression corners at Mach 6, VKI TN-181, 1992.
14. EDWARDS, C.L.W. and ANDERS, J.B. Low density, leading edge bluntness and ablation effects on wedge induced laminar boundary layer separation at moderate enthalpies in hypersonic flows, NASA TN D-4829, 1968.
15. KUMAR, D. Hypersonic Control Effectiveness, PhD Thesis, Cranfield University, 1995.
16. COET, M.C., DELERY, J. and CHANETZ, B. Experiments on shock wave-boundary layer interaction at high mach number with entropy layer effect, IUTAM Symposium, Marseille, France, 1992.
17. TOWNSEND, J.C. The effects of leading edge bluntness and ramp deflection angle on laminar boundary layer separation in hypersonic flow, NASA TN D-3290, 1966.
18. HOLDEN, M.S. and MOSELLE, J.R. A database of aerothermal measurements in hypersonic flow for CFD validation, AIAA-92-4023, 1992.
19. STOLLERY, J.L., MAULL, D.J. and BELCHER, D.A. The Imperial College hypersonic gun tunnel, J Royal Aero Soc, 1960, 64, pp 634-641.
20. NEEDHAM, D.A. Progress report on the Imperial College hypersonic gun tunnel, IC Aero TN-118, 1963.
21. KONTIS, K. and STOLLERY, J.L. Control effectiveness of a jet-slender body combination at hypersonic speeds, J Spacecraft and Rockets, 1997, 34, pp 762-768.
22. KONTIS, K. Projectile Aerodynamics: Measurement and Computation, PhD Thesis, Cranfield University, 1997.
23. OPATOWSKI, T. An Experimental Study of the Flow Around and the Forces Developed by Hypersonic Lifting Vehicles, PhD Thesis, University of London, 1967.
24. COLEMAN, G.T. Hypersonic Boundary Layer Studies, PhD thesis, University of London, 1973.
25. BROWER, W. Theory, Tables and Data for Compressible Flow, New York:Hemisphere, 1990.
26. SCHWARTZ, L.W. Comment on an empirical expression for drag coefficients of cones at supersonic speeds, AIAA J, 1969, 7, pp 345-351.
27. Ames research staff, Equations, tables and charts for compressible flows, NACA Report 1135, 1952.
28. RASMUSSEN, M. Hypersonic Flow, Wiley-Interscience Publication, New York, 1994.
29. ROSE, W.C., PAGE, R.J. and CHILDS, M.E. Incipient separation pressure rise for a Mach 3.8 turbulent boundary layer, AIAA J, 1973, 11, pp 761-764.
30. BABINSKY, H. and EDWARDS, J.A. On the incipient separation of a turbulent hypersonic boundary layer, Aeronaut J, 1996, 100, (996), pp 209-214.
31. APPELS, C. and RICHARDS, B.E. Incipient separation of a compression turbulent boundary layer, AGARD CP-168, 1975.
32. SPAID, F.W. and FRISHETT, J.L. Incipient separation of a supersonic, turbulent boundary layer, including effect of heat transfer, AIAA J, 1972, 10, pp 915-922.
33. BECKER, J.V. and KORYCINSKI, P.F. Heat transfer and pressure distribution at a Mach number of 6.8 on bodies with conical flares and extensive flow separation, NASA TN D-1260, 1956.
34. KUEHN, D.M. Experimental investigation of the pressure rise required for the incipient separation of turbulent boundary in two-dimentional supersonic flow, NACA Memorandum 1-21-59A, 1958.
35. FERGUSON, H. and SCHAEFER, J.W. Heat transfer and pressure distribution on cone-cylinder-flare configuration with boundary-layer separation, NASA TN D-1436, 1962.
36. DRUGGE, G. An experimental investigation of the influence of strong adverse pressure gradients on turbulent boundary layers at supersonic speeds, FFA Report 47, 1953.
37. HOLDEN, M.S. Experimental studies of shock wave boundary layer interaction, VKI-LS-62, 1974.
38. KESSLER, W.C., Reilly, J.F. and Mockapetris, L.J. Supersonic turbulent boundary layer interaction with an expansion ramp and compression corner, Mc Donnell Douglas Report, MDC E0264, 1970.
39. LAW, H.C. Supersonic turbulent boundary layer separation measurements at Reynolds numbers of 107 to 108, AIAA-73-665, 1973.
40. STERRETT, J.R. and EMERY, J.C. Experimental separation studies for two-dimensional wedges and curved surfaces at Mach numbers of 4.8 to 6.2, NASA TN D-1014, 1962.
41. ROSHKO, A. and THOMKE, G.J. Flare-induced interaction lengths in supersonic, turbulent boundary layers, AIAA J, 1974, 14, pp 873-879.
42. APPELS, C. Turbulent boundary layer separation at Mach 12, VKI TN-90, 1973.
43. SIMEONIDES, G., HASSE, W. and MANNA, M. Experimental, analytical and computational methods applied to hypersonic compression ramp flows, AIAA J, 1994, 32, pp 189-195.
44. HORTON, H.P. The calculation of adiabatic laminar boundary layer shock wave interactions in axi-symmetric flow: Part I - Hollow cylinder-flare bodies with zero spin, VKI TN-63, 1970.
45. GRAY, D.J. Laminar boundary-layer separation on flared bodies at supersonic and hypersonic speeds, AEDC-TDR-64-277, 1965.
46. GOODRICH, W.D., LI, C.P., HOUSTON, C.K., CHIU, P.B. and OLMEDO, L. Numerical computations of orbiter flowfields and laminar heating rates, J Spacecraft and Rockets, 1977, 14, pp 257-264.