Measurements of Aerodynamic Heat Transfer on a 15 deg Cone-Cylinder-Flare Configuration in Free Flight at Mach Numbers up to 4.7

摘要

Measurements of aerodynamic heat transfer have been made at a number of stations along a cone-cylinder-flare model having a 15 deg. total-angle conical nose and a 10 deg. half-angle flare skirt. The maximum Mach number was 4.7, and local Reynolds numbers based on body length to a measurement station varied from 2 x l0(exp 6) to 138 x 10(exp 6). Local Stanton numbers measured on the nose cone and flare showed fair agreement with laminar and turbulent theories, while the measurements on the cylinder were generally somewhat lower than theory. Experimental recovery factors, determined twice during the test, were un-accountably lower than theoretical values. Local transition Reynolds numbers, based on length from the nose tip, varied from 3 x 10(exp 6) to 18 x 10(exp 6) and were much lower than values previously obtained on the smoother nose of a similar model. At an angle of attack of about 9 deg., the heat transfer on the flare increased to more than twice the theoretical turbulent value for zero angle of attack.