Abstract: The simulation parameters of different hypersonic test facilities have large influence to the test results. A typical lift body aerodynamic test was conducted in the combustion heated impulse facility and hypersonic wind tunnel. The influence of Reynolds number and wall temperature ratio was analyzed. The aerodynamic changes of the combustion heated impulse facility test were in consistence with those of the hypersonic wind tunnel test, but its drag coefficients were about 15% larger. Numerical analysis indicates that the differences caused by Reynolds number were about 5%, and those caused by the wall temperature ratio were about 10%, and therefore the change of velocity boundary layer is the main factor.