FREE-FLIGHT HEAT-TRANSFER INVESTIGATION AT SUPERSONIC SPEEDS OF TWO SLENDER CONE-CYLINDER BODIES AT AN ANGLE OF ATTACK OF 8° WITH ONE BODY ROTATING

摘要

In a free-flight investigation, wall temperatures were measured on two slender cone-cylinder bodies at an angle of attack of 8° with one body rotating between 4 to 5 revolutions per second. The free-stream Mach number range was from 2.5 to 4.5 and free-stream Reynolds number per foot ranged from 13.5 X 106 to 19.6 x 10. The wall temperatures on the rotating body measured at a station 62.8 percent of the body length were approximately equal to the mean circumferential temperature on the fixed body for the range of free-stream Mach numbers investigated. Along the windward meridian line of the fixed body, the Stanton number showed that the boundary layer was laminar up to 62.8 percent of the body length and up to a free-stream Mach number of 3.5. At Mach numbers above 3.5 the transition point moved forward of this station. The highest heat-transfer rates on the conical section of the fixed body occurred between circumferential angles of 450 and 560. The magnitudes of the heat-transfer coefficients along the windward meridian line of the rotating body were between 0.03 to 0.04 for most of the measuring stations and through most of the Mach number range. The experimental pressure coefficients measured on the conical surface of the fixed body agreed with the trend computed from potential-flow theory.