Drag and Heat-flux Assessment of Hypersonic Flow on an Asymmetric Blunt Shaped Body

Abstract

Assessment of aerodynamic forces and heat-transfer rates for certain flight conditions is an essential task in designing a hypersonic vehicle. Experimental investigation of impulse ground-based type facilities is researchers standard practice for such purposes. However, due to extremely short test times of the flow, measurement of aerodynamic forces and heat-transfer rates in such facilities causes many technical issues. This study presents a series of drag and heat-flux measurements taken in the shock tunnel. An asymmetric blunt shaped forebody was tested at a nominal Mach 6. A conventional accelerometer-based drag balance system was applied to the test model during force measurements. K-type thermocouple sensors were used to measure surface heat-transfer rates. A comprehensive procedure for implementation and calibration of each measurement technique is provided in a single manuscript.