Aerodynamic heating measurements on nose and elevon of hypersonic flight experiment vehicle

Aerodynamic heating on the nose and the eleven of the hypersonic flight exp eriment vehicle was measured using a newly developed sensor, which was cali brated at the heating level corresponding to the level at the real flight c ondition by a tamp heating test. The calibration test result shows that the sensor could be applicable to the present flight environment, The results of the aerodynamic heating measurements on the nose and the eleven of the v ehicle were compared with predictions based on cold hypersonic wind-tunnel tests and computational fluid dynamics (CFD) calculations. The flight-test results on the stagnation region at around t = 100 s were lower than the pr edictions based on the wind-tunnel tests. The comparisons with CFD results assuming either a fully catalytic wall or noncatalytic wall indicate that t he discrepancy could be due to the real gas effect and might be explained q ualitatively. For the measurements on the eleven, an increase in aerodynami c heating caused by boundary-layer transition was observed just before it w as observed on the windward fuselage.