Entrance of space module into atmosphere is one of the very critical phases of any space mission. Due to formation of bow shock (Detached) in front of the module, the air temperature drastically increases to thousands of Kelvin. One, suggested in order to find the amount of heat transfer to the space module at the reentry phase, we can setup an experiment on the ground with a scaled model in the wind tunnel. The proposed scaled model is . / times and is located in a wind tunnel with a maximum air velocity 100 times less than actual velocity of the module. The density of the air at the reentry zone is almost 1000 times less than air density at the sea level, where the wind turbine is located. The see level air Prandtl number is approximately the same as reentry zone. But the dynamic viscosity of air at the reentry condition is almost 3.59 times of the sea level air viscosity. The Thermal conductivity of air in the reentry condition is 4.356 times of the sea level condition. Apollo 9 re-entry vehicle at San Diego Air and Space Museum. In the wind tunnel for the air temperature difference of 100o C between air and the scaled model the energy transfer due to the heat was measured to be about 400W. At the reentry condition with 1500o C Temperature how much is the energy transfer due to the heat to the module