This paper reports the results of ablation tests conducted in FD04 arc tunnel of China Academy of
Aerospace Aerodynamics (CAAA) for the development of wing leading edge thermal protection materials. The models
were made of high temperature ceramic(HTC), with swept angle 53, height 75 mm, long 55 mm, leading edge radius 2 mm and symmetric cross section made up of a 5wedge on each side. The test facility included 20 MW arc heat
er, mixing chamber, rectangular supersonic nozzle, test box, trajectory simulation and vacuum system etc. The rectangular supersonic nozzle with Mach number 3. 6 was used in tests. The aero heating conditions of the wing leading
edge were simulated by a test trajectory with flow field parameters of three steps. The test duration was 77. 0 s. The
results show that HTC has well ablation performance, and two models had no breakage during the tests. The inner
temperature responses are attained in tests.