Measurement of Drag on a Scramjet Engine in a Shock Tunnel

Abstract

The net drag on a non-fuelled, internal compression, constant-area combustor scramjet engine was measured using a single-component accelerometer balance in a shock tunnel at a freestream Mach number of 8 and a flow total enthalpy of 1.35 MJ/kg. The flow fields of the model were simulated using a commercial CFD code in order to understand the aerodynamics of the engine and compare with the measured net drag co-efficient. Measured and computed values of the net drag co-efficient were found to be in a good agreement.