Transient Surface Heat Flux and Surface Temperature Engineering Prediction of Hypersonic Vehicle

Using CFD to calculate transient surface heat flux and surface temperature of hypersonic vehicle requires large computer run time,and flight or wind tunnel test costs too much,therefore they are not feasible.An engineering method for calculating transient surface heat flux and surface temperature of hypersonic vehicle is described in this paper,including stagnation point and out of stagnation point.The parameters at the edge of the boundary layer have been calculated both perfect gas and equilibrium gas.Take a blunted 15 deg half-angle cone for example,The results show that the engineering method consumes less time and is workable.Consequently,the valuable reference data are supplied for the aerothermal calculation in initial design and the reasonable choice in TPS of hypersonic vehicle.