Hostname: page-component-cd9895bd7-gxg78 Total loading time: 0 Render date: 2024-12-22T11:23:27.013Z Has data issue: false hasContentIssue false
  • English
  • Français

Incipient separation on flared bodies at hypersonic speeds

Published online by Cambridge University Press:  04 July 2016

K. Kontis  and
J. L. Stollery
K. Kontis
Affiliation:
Gas Dynamics LaboratoryNagoya UniversityNagoya, Japan
J. L. Stollery
Affiliation:
Cranfield College of AeronauticsCranfield UniversityCranfield, UK
Get access Rights & Permissions [Opens in a new window]

Abstract

The aerodynamic effectiveness of a cylinder-flare body at zero incidence under laminar and turbulent boundary-layer conditions has been studied experimentally. Two nose geometries, namely a 10° half-angle sharp cone and a hemisphere, were used. The study has been carried out in a hypersonic gun tunnel at a Mach number of 8·2 and a Reynolds number of 158,100, based on the cylinder diameter, at flare angles 0°, 10°, 20°, 30° and 45°. The surface flow was studied using oil-dot and liquid crystal techniques. Some information regarding the shock layer was obtained from schlieren pictures. The effects of entropy layer and boundary-layer state on flare effectiveness were deduced from pressure measurements over the cylinder and the flare.

Type
Research Article
Information
The Aeronautical Journal , Volume 103 , Issue 1027 , September 1999 , pp. 405 - 414
Copyright
Copyright © Royal Aeronautical Society 1999 

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. Coleman, G.T. and Stollery, J.L. Incipient separation of axially symmetric hypersonic turbulent boundary layers, AIAA J, January 1974, 12, pp 119–120.Google Scholar
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.Google Scholar
3. Kuehn, D.M. Turbulent boundary-layer separation induced by flares on cylinders at zero angle of attack, NASA TR-R-117, 1961.Google Scholar
4. Kuehn, D.M. Laminar boundary-layer separation induced by flares on cylinders at zero angle of attack, NASA TR-R-146, 1962.Google Scholar
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.Google Scholar
6. Ginoux, J.J. On some properties of reattaching laminar and transitional high speed flows, VKI TN-53, 1969.Google Scholar
7. Needham, D.A. and Stollery, J.L. Boundary layer separation in hypersonic flow, AIAA-66-455,1966.Google Scholar
8. Inoer, G.R. Scaling of incipient separation in high speed laminar flows, AIAA-93-3435, 1993.Google Scholar
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.Google Scholar
10. Elfstrom, G.M. Turbulent separation in hypersonic flow, IC Aero Report 71-16, 1971.Google Scholar
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.Google Scholar
12. Stollery, J.L. and Bates, L. Turbulent hypersonic viscous interaction, J Fluid Mech, 1974, 63, (1), pp 145–156.Google Scholar
13. Vermeulen, J.P. and Simeonides, G. Parametric studies of Shockwave boundary layer interactions in two dimensional compression corners at Mach6,VKITN-181, 1992.Google Scholar
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.Google Scholar
15. Kumar, D. Hypersonic Control Effectiveness, PhD Thesis, Cranfield University, 1995.Google Scholar
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.Google Scholar
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.Google Scholar
18. Holden, M.S. and Moselle, J.R. A database of aerothermal measurements in hypersonic flow for CFD validation, AIAA-92-4023, 1992.Google Scholar
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.Google Scholar
20. Needham, D.A. Progress report on the Imperial College hypersonic gun tunnel, IC Aero TN-118, 1963.Google Scholar
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.Google Scholar
22. Kontis, K. Projectile Aerodynamics: Measurement and Computation, PhD Thesis, Cranfield University, 1997.Google Scholar
23. Opatowski, T. An Experimental Study of the Flow Around and the Forces Developed by Hypersonic Lifting Vehicles, PhD Thesis, University of London, 1967.Google Scholar
24. Coleman, G.T. Hypersonic Boundary Layer Studies, PhD thesis, University of London, 1973.Google Scholar
25. Brower, W. Theory, Tables and Data for Compressible Flow, New York:Hemisphere, 1990.Google Scholar
26. Schwartz, L.W. Comment on an empirical expression for drag coefficients of cones at supersonic speeds, A1AA J, 1969, 7, pp 345–351.Google Scholar
27. Ames research staff, Equations, tables and charts for compressible flows, NACA Report 1135, 1952.Google Scholar
28. Rasmussen, M. Hypersonic Flow, Wiley-Interscience Publication, New York, 1994.Google Scholar
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.Google Scholar
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.Google Scholar
31. Appels, C. and Richards, B.E. Incipient separation of a compression turbulent boundary layer, AGARD CP-168, 1975.Google Scholar
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.Google Scholar
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.Google Scholar
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.Google Scholar
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.Google Scholar
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.Google Scholar
37. Holden, M.S. Experimental studies of shock wave boundary layer interaction, VKI-LS-62, 1974.Google Scholar
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.Google Scholar
39. Law, H.C. Supersonic turbulent boundary layer separation measurements at Reynolds numbers of 107 to 108, AIAA-73-665, 1973.Google Scholar
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.Google Scholar
41. Roshko, A. and Thomke, G.J. Flare-induced interaction lengths in supersonic, turbulent boundary layers, AIAA J, 1916, 14, pp 873–879.Google Scholar
42. APPELS, C. Turbulent boundary layer separation at Mach 12, VKITN-90, 1973.Google Scholar
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.Google Scholar
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.Google Scholar
45. Gray, D.J. Laminar boundary-layer separation on flared bodies at supersonic and hypersonic speeds, AEDC-TDR-64-277, 1965.Google Scholar
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.Google Scholar