Hypersonic Rarefied Transitional Flow Pneumatic Heat Associated With The Calculation Method

A correlation method of heat transfer rate in hypersonic rarefied flow was present in this paper. Flow criterion was introduced for stagnation point region and the body of the vehicle. On the basis of therotical analysis, the raefied heat transfer rate correlation parameter-Cheng's parameter was modified. A set of correlation parameters, which could be used to analysis rarefied flow heating to hypersonic vehicles with attack angle, has been established through coupling with pressure coefficient. According to correlating many Low-dencity wind tunnels experimental dates at home and abroad, the least squares procedure adopted to fit the data, a engineering method of rarefied heat transfer rates on the surface of vehicle with attack angle has been established. In order to calcalate rarefied heat transfer on the surface of arbitrariness configuration, combined the inviscid surface streamlines and axisymmtric annalog, the engineer calculational method of rarefied heat transfer on the surface of vehicle with attack angle was been established. Calculational results showed heat transfer rates (along upwind and leeside generatrix, circumferential direction) were well agreement with the experimental data.