Ground Testing Synthesis of the LAPCAT II Small Scale Flight Experiment Configuration Scramjet Flow Path

Abstract

This paper reports on the experiments on a a scramjet powered flight experiment configuration. The 1.5 m long wind tunnel model consists of intake, combustor and thrust nozzle and is designed for a flight Mach number of 7.4. The outer mold line of this small scale flight configuration (SSFE) was derived from the full scale Mach 8 cruiser MR 2 proposed by ESA-ESTEC within the EC co-funded LAPCAT II project. In the framework of LAPCAT II, the two major European free jet facilities, namely the High Enthalpy Shock Tunnel Göttingen (HEG) of the German Aerospace Center (DLR) and the F4 hot shot facility of the French Aerospace Lab (ONERA) were used to perform these measurements. The core tests in HEG and F4 is emphasizing the Mach 7.4-8 flight conditions. The paper gives an experimental synthesis on both campaigns and discusses the complementary results in both facilities.