Hypersonic Turbulent Research Articles

Film-Cooling Effectiveness and Skin Friction in Hypersonic Turbulent Flow

Experimental equilibrium temperatures and skin friction at the surface of a flat plate cooled by two-dimensional, tangential slot injection are presented for a Mach 6 mainstream. Effects of slot height, slot mass-flow rate, injection gas temperature, and heat conduction to the slot are investigated. Experimental skin friction and effectiveness data in general agree well with predictions from a finite-difference method. Film cooling at Mach 6 was found significantly more effective than at lower speeds, with large reductions in friction drag measured downstream of the slot These results indicate the necessity for a new evaluation of film-cooling systems for hypersonic vehicles.

Reflected wave reverse flow in an electromagnetic shock tube

7 Bertram, M. H. and Neal, L., Jr., Experiments in Hypersonic Turbulent Boundary Layers, Presented at the AGARD Specialists Meeting on Recent Developments in Boundary-Layer Research, Naples, Italy, May 1965. 8 Van Driest, E. R. and Blumer, C. B., Summary Report on Studies on Boundary-Layer Transition for Years 1963-64, SID 64-2191, Dec. 1964, Space Sciences Lab., North American Aviation Inc. 9 Zukoski, E. E. and Spaid, F. W., Secondary Injection of Gases Into a Supersonic Flow, AIAA Journal, Vol. 2, No. 10, Oct. 1964, pp. 1689-1696. 10 Torrence, Marvin, G., Concentration Measurements of an Injected Gas in a Supersonic Stream, TN D-3860, April 1967, NASA. TOP OF SHOCK TUBE -REMOTE FROM DRIVER SECTION.

Experimental Investigations of the Effect of Heat Transfer on Hypersonic Turbulent Boundary-Layer Skin Friction

Experimental Investigations of the Effect of Heat Transfer on Hypersonic Turbulent Boundary-Layer Skin Friction