Abstract: Local overheat causing by the protuberance on the surface of reentry spacecraft in the condition of hypersonic and supersonic flow is discussed briefly.Using the pre processing and after processing software ARIES and calculation program NASTRAN,the distributions of temperature on the protuberance under the test thermal environment and trajectory thermal environment condition are calculated respectively.Then the result of calculation are compared with the result of the test and they are very identical,which is proved that the way treating local overheat causing by the protuberance is practicable and advanced.