Abstract: Wind tunnel experiment is a key means to research and predict aeroheating for hypersonic vehicles. The flow field parameters and model scales in wind tunnel are different from flight condition, owing to the limitation of its simulation capability. The aeroheating data obtained from wind tunnel experiments can not be directly used for the aeroheating prediction and thermal protection system design in flight condition. So the method of predicting the aeroheating environment on flight condition, by using the wind tunnel experimental data, has been a technically difficult problem. In the past, the correlation and extrapolation method of wind tunnel aeroheating experiment data for specific aircrafts has a strong directionality, because this method is a kind of data fitting based on aeroheating data and does not take into account the specific parameters of aeroheating. It has certain limitations and is difficult to extrapolate to other shapes of aircraft. To solve the problem of the wind tunnel experimental data extrapolation, the main parameters of the influence of aeroheating were analyzed on the basis of the dimensionless Navier-Stokes equations and boundary layer equations, and the correlation and extrapolation method was developed for laminar and turbulence conditions by deducing the approximate solution of the aeroheating. Because the parameters of the local boundary layer edge can be taken into consideration, the correlation method has certain versatility. Then the experimental data of scale model on Reentry-F was obtained from wind tunnel experiments, the correlation analysis and validation for Reentry-F configuration was accomplished, the wind tunnel experimental data was extrapolated to flight condition by the extrapolation method and it agreed well with flight data. It showed that the method can be used for extrapolation of aeroheating experimental data, and multiple points of flight condition can be extrapolated from a few experimental results.