Conjugate heat transfer studies are presented for high speed aerospace vehicle using commercial CFD software. Navier Stokes equations in the fluid domain and transient heat conduction equations in the solid domain are solved simultaneously to obtain the skin temperature history and other flow parameters. The computational methodology is applied to predict the surface temperature of high speed aerospace vehicle after validating the methodology against experimental results. Validation cases include laminar flow past axisymmetric double cone at Mach 4.57 and turbulent flow past circular cylinder at Mach 6.7. Computed flow field including cold wall heat flux, surface temperature distribution, surface temperature history match nicely with experimental as well as other numerical results. Temperature dependent material properties are found to have significant effect on the surface temperature prediction. Computed surface temperature of a high speed aerospace vehicle show good overall match with flight measured values.