Flow and Heat Transfer During the Injection of Coolants into a Supersonic Flow,
FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO
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Some information is presented on the results of an experimental study of the flow and heat transfer on the surface of sharp circular cones with 10 deg half-angle and base diameter of 80 mm with the injection of the air or helium through a slit along the smooth cone surface and also through slits or permeable sections established in circular recesses of varied length and depth. The tests were made at Mach number 5, stagnation temperature 250C, and stagnation pressure 8 bar.
- Fluid Mechanics