An experimental study of the effects of injectant properties on the aerothermal characteristics of transpiration-cooled cones in hypersonic flow
Abstract
An experimental study was conducted to examine the effects of coolant properties on heat transfer and skin friction on a transpiration-cooled sharp cone in hypersonic flow. The study was conducted at Mach number 11 and local Reynolds number 1 x 10 to the 8th. Measurements of the reduction in heating and skin friction to the cone were made for blowing rates from 0.10 to 5.0. Holographic measurements gave definitive indications of boundary-layer behavior with blowing. Correlations of the measurments with those from earlier studies indicate that significantly larger cooling effectiveness can be obtained at hypersonic speeds compared to supersonc speeds. Correlations of the heat transfer and skin friction measurements for different injectants indicate that their relative effectiveness may be expressed in terms of either the effects of specific heat or molecular weight ratio.
- Publication:
-
AIAA, Fluid Dynamics, 21st Plasma Dynamics and Lasers Conference, 21st, Seattle, WA, June 18-20, 1990. 17 p.
- Pub Date:
- June 1990
- Bibcode:
- 1990fdpd.confR....H
- Keywords:
-
- Aerothermodynamics;
- Fluid Injection;
- Hypersonic Flow;
- Slender Cones;
- Sweat Cooling;
- Turbulent Heat Transfer;
- Mach Number;
- Molecular Weight;
- Reynolds Number;
- Shock Tunnels;
- Specific Heat;
- Fluid Mechanics and Heat Transfer