The solutions to some key techniques using infrared thermographic technique in hypersonic wind tunnel, such as
temperature measurement under great measurement angle, the corresponding relation between model spatial coordinates
and the ones in infrared map, the measurement uncertainty analysis of the test data etc., are studied. The typical results in
the hypersonic wind tunnel test are presented, including the comparison of the transfer rates on a thin skin flat plate
model with a wedge measured with infrared thermography and thermocouple, the experimental study heating effect on
the flat plate model impinged by plume flow and the aerodynamic heating on the lift model.