EFFECTIVENESS OF AN AEROSPIKE FOR REDUCTION OF HYPERSONIC AERODYNAMIC HEATING

摘要

A series of hypersonic wind tunnel tests has been performed at a Mach number of 7 to estimate the effect of nose configuration of aerospike attached on a hemispherical body on reduction of surface pressure and heat transfer. The surface temperature data on the hemisphere were obtained by using temperature sensitive paints with the fluorescent phosphor. The results indicate that the pressure and heat flux peak on the hemisphere becomes lower as the bluntness of spike nose increases.