Regenerative cooling is a key cooling method for scramjet engines, and the design of its cooling channels plays a crucial role in heat transfer performance. Aimed at reducing the average wall temperature and the inlet-outlet pressure difference，the topology optimization design of the regenerative cooling channel was conducted under the fluid inlet velocity of 0.6 m/s. Based on the characteristic shape generated from the optimized topology results, an S-shaped cooling channel model was fabricated. Subsequently, electric heating was used to control the heat flux, and RP-3 aviation kerosene was used as the cooling fluid. Heat transfer characteristics of both the straight channel and the S-shaped channel （optimized topology channel） were experimentally tested under the supercritical pressure of 4 MPa, with heat flux of 143, 207, 420, and 715 kW/m² applied to the inner wall. Experimental results indicate that the design of optimized topology channel effectively reduces the temperature of the outer wall. Under the four heat fluxes, the average Nusselt numbers of the optimized topology channel increase by 124%, 87%, 26%, and 11%, respectively. Notably, at the lower heat flux, the optimized topology channel exhibites a more significant reduction in outer wall temperature, with the temperature reduction primarily occurring at the bend of the channel.