Abstract
Although important flow parameters as Mach number, Reynolds number and total enthalpy can be reproduced in most hypersonic experiments quite well, due to different surface temperature effects in wind tunnel and flight, scaling as well as specific flow properties of shock wave/boundary layer interactions are different. This especially holds for short-duration facilities like, e.g. shock tunnels where due to short running times the models remain more or less at ambient temperature. To overcome this shortcoming, an experimental study has been conducted using a preheatable ramp model with 15° ramp angle. This allowed us to adjust the surfaces to an arbitrary temperature just before the experiment started. Pressure and heat flux measurements clearly showed the effect of varying surface and free stream temperatures. These results are supported by schlieren pictures and infrared measurements. The comparison of the measurements with theoretical and numerical results shows a good agreement. Separation bubble scaling laws proposed by Katzer and Davis have been applied and partially confirmed using the local conditions of the boundary layer at separation.
Similar content being viewed by others
References
Charbonnier J.M. (1998) Hot wall testing in high speed flows, Project Report VKI Reprint 1998-24. Von Karman Institute for Fluid Dynamics, Brussels
Davis J.P., Sturtevant B. (2000) Separation length in high-enthalphy shock/boundary-layer interaction. Phys. Fluids 12, 2661–2687
Delery J., Marvin J.G. (1989) Shock-wave boundary layer interactions, AGARD Report 761. NATO, Brussels
Elfstrom G.M. (1971) Turbulent hypersonic flow at a wedge compression corner, Aeroreport 71-16. Imperial College, London
Hirschel, E.H.: Thermal surface effects in aerothermodynamics. In: Proceedings of the 3rd European Symposium on Aerothermodynamics for Space Vehicles, ESA SP-426, Noordwijk, The Netherlands, pp. 17–31 (1998)
Hung, F.T., Barnett, D.O.: Shock wave-boundary layer interference heating analysis. AIAA paper 72-237 (1973)
Katzer E. (1989) On the lengthscales of laminar shock/ boundary-layer interaction. J. Fluid Mech. 206, 477–496
Kindl, H.: Einfluss des Treibergases auf die Strömung in Stoßwellenkanälen. PhD thesis, Shock Wave Laboratory, RWTH Aachen University (2000)
Lewis J.E., Kubota T., Lees T. (1968) Experimental investigation of supersonic laminar, two-dimensional boundary-layer separation in a compression corner with and without cooling. AIAA J. 6, 7–14
Marini M. (2001) Analysis of hypersonic compression ramp laminar flows under sharp leading edge conditions. Aerosp. Sci. Technol. 5(4): 257–271
Olivier H. (1993) An improved method to determine free stream conditions in hypersonic facilities. Shock Waves 3, 129–139
Olivier, H., Zechner, M.: Slender conical nozzle, MSTP Final Report HT-SF-E34-731-RWTH, Shock Wave Laboratory, RWTH. Aachen University (1996)
Olivier, H., Bleilebens, M.: Final report: Hot experimental testing. Technical Report ESA WP5510. Shock Wave Laboratory, RWTH Aachen University (1999)
Reinartz, B.U., van Keuk, J., Coratekin, T., Ballmann, J.: Computation of wall heat fluxes in hypersonic inlet flows. In: 40th Aerospace Sciences Meeting and Exhibit, AIAA 2002-0506, Reno, USA (2002)
Roshko, A.: Free shear layers, base pressure and bluff-body drag. In: Symposium on Developments in Fluid Dynamics and Aerospace Engineering, Interline, Bangalore, India (1995)
Scortecci, F., Paganucci, F., d’Agostino, L.: Experimental investigation of shock-wave/boundary-layer interactions over an artificially heated model in hypersonic flow. In: Proceedings of the AIAA 8th International Space Planes and Hypersonic Systems and Technologies Conference, AIAA 1998-1571, Norfolk, USA (1998)
Simeonides G., Haase W., Manna M. (1994) Experimental, analytical, and computational methods applied to hypersonic compression ramp flows. AIAA J. 324, 301–310
Simeonides G. (1998) Generalized reference enthalpy formulations and simulation of viscous effects in hypersonic flows. Shock Waves 8, 161–172
Spaid F.W., Frishett J.C. (1972) Incipient separation of a supersonic, turbulent boundary layer, including effects of heat-transfer. AIAA J. 10(7): 915–922
van Driest, E.R.: Investigation of laminar boundary layer in compressible fluids using the Crocco method. NACA Technical Note 2597 (1952)
Author information
Authors and Affiliations
Corresponding author
Additional information
Communicated by B. Milton.
Rights and permissions
About this article
Cite this article
Bleilebens, M., Olivier, H. On the influence of elevated surface temperatures on hypersonic shock wave/boundary layer interaction at a heated ramp model. Shock Waves 15, 301–312 (2006). https://doi.org/10.1007/s00193-006-0025-2
Received:
Accepted:
Published:
Issue Date:
DOI: https://doi.org/10.1007/s00193-006-0025-2