介绍在CAAA的FD04电孤风洞上进行的翼前缘防热材料烧蚀试验结果.试验模型由高温陶瓷制成,后掠角53°,高75 mm,长55 mm,前缘半径2 mm,对称截面半锥角为5°.试验设备包括20 MW电弧加热器、混合室、矩形超声速喷管、试验段、轨道模拟系统及真空系统等.使用的矩形超声速喷管的马赫数为3.6,以3个台阶的轨道模拟翼前缘热环境,试验时间为77.0 s.试验结果表明高温陶瓷具有优良的抗烧蚀性能,两件试验模型在试验过程中均未出现破损现象,试验还得到了翼前缘模型试验过程中的内部温度响应.
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 radi- us 2 mm and symmetric cross section made up of a 5° wedge 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 rec- tangular 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.
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