关键词: 超燃冲压发动机；机体推进一体化；脉冲燃烧风洞；推力；阻力；比冲

Abstract: Scramjet closely coupled with the aircraft，making it very difficult to directly measure the effec.tive thrust of the engine in the ground test. In order to obtain the engine thrust performance more effectively，an evaluation method based on the aero-propulsion integrated test is proposed. The net thrust of the aircraft with en.gine integrated is obtained directly from the force measuring test of pulsed combustion heated wind tunnel. Thenthe effective thrust of the engine is obtained based on the net thrust plus the external drag of the body. At the sametime，a test technique for measuring the external drag of the aircraft body by a flowmeter is proposed. The mea.surement error is also analyzed(the root mean square error is less than 2.54%). Compared with traditional meth.od which applied the difference of measured total axis forces between fueled and unfueled engine status minus thecomputed flowpath drag to get the engine thrust，this method transforms the calculation of the internal drag of theengine flow path into the calculation or measuring external drag of the aircraft and provides a new idea for thethrust performance evaluation of the scramjet engine.

Key words: Scramjet engine； Aero-propulsion integration； Pulsed combustion heated wind tunnel； Thrust；Drag；Specific impulse