Abstract: The Görtler vortex characteristics and heat flow distribution in the hypersonic compression ramp flow were studied experimentally. In the Mach 6 low-noise wind tunnel, the heat flow distribution image on the compression ramp was obtained by using temperature sensitive paint (TSP) technology and the heat flux algorithm based on discrete Fourier law. By changing the ramp angle and total pressure, the Görtler vortex characteristics and the heat flow distribution on the compression ramp were studied under different ramp angles and unit Reynolds numbers. The results show that when the angle of ramp or the unit Reynolds number increases, the Görtler vortex wavelength decreases, while the oneset of the vortex is closer to the corner. As the unit Reynolds number increases, the average heat flux on the ramp increases, and the peak heat flux moves forward. After the peak of heat flux, the area where the heat flow slowly decreases corresponds to the Görtler vortex position.