2011•17th AIAA International Space Planes and Hypersonic Systems and Technologies ConferenceRequires access
Experimental investigation of hypersonic boundary layer transition on a cone model in the High Enthalpy Shock Tunnel (HEG) at Mach 7.5
Alexander Wagner, Viola Wartemann, Stuart J. Laurence, Jan Martinez Schramm, Klaus Hannemann, Heinrich Lüdeke, Hideyuki Tanno, Katsuhiro Ito
Open publisher page 13 citations
Abstract
Hypersonic boundary-layer transition on a 7 half-angle cone was investigated experimentally in the DLR High Enthalpy Shock Tunnel G�ottingen (HEG) at Mach 7.5. The cone model, provided by the Japan Aerospace Exploration Agency (JAXA), has a length of 1100mm and was tested with nose radii of 2:25mm and 5mm. The free stream unit Reynolds number was varied over the range of 1:2 106=m to 6:2 106=m at a stagnation enthalpy of H0 = 3:3MJ=kg. The model was equipped with co-axial thermocouples to determine the transition location by means of the surface heat-ux distribution. Ten ush mountedpiezoelectric fast-response pressure transducers were used to measure the pressure uctuations in the boundary-layer associated with second mode instabilities. The results are compared to stability calculations conducted with the DLR NOn-LOcal Transition analysis code, NOLOT.