Abstract: As the benchmark data for the design and evaluation of the thermal protection system, as well as the assessment data of the calculation method, the accuracy of thermal environment measurement data is of great importance. In this paper, the measurement discrepancy caused by the difference between the sensor surface and the surrounding heat-resistant material temperature is studied. A numerical stimulation program based on Navier-Stokes equations is used to calculate the heat flux distribution on the sensor and peripheral area of the sensor, and the mechanism of local heat flux changes and the main factors influencing the thermal environment change are studied by the field-coordination theory. The results indicate that when there is difference between the temperature of the sensor surface and the peripheral material, the temperature and pressure of the local flow field is changed, causing dramatic changes of the heat flux on sensor surface. When the Mach number and altitude of the flux are the same, the angle of attack of the flux mainly affects the distribution of normal velocity:as the temperature difference remains the same, the larger the angle of attack, the smaller the increase in aeroheating. The total temperature of the flux mainly affects the distribution of normal temperature gradient:as the temperature difference remains the same, the larger the total temperature, the smaller the increase in aeroheating. The study can avoid misjudgment of the measured heat flux, providing a method for analyzing and validating thermal environment test data.

Key words: hypersonic, sensor, heat flux measurement, difference of temperature, heat flux distribution