Abstract: The scramjet model with the same flow channel was used in order to study the influence of the performance of scramjet with different simulation methods of combustion wind tunnel. The experiment was executed in the wind tunnel with two kinds of combustion heating methods，the one which was heated by burning alcohol was used to simulate the method of “static temperature and static pressure”，and the other heated by burning hydrogen was used to simulate the method of “total enthalpy and dynamic pressure”. By combining the flight test data and theoretical deduction and analysis，a detailed comparative analysis of experimental data was carried out . The results show that when the performance of scramjet is studied by using the combustion wind tunnel，“enthalpy，dynamic pressure and equivalent ratio” should be chosen as the simulation parameters. In the state of Ma5，the performance results of scramjet are basically consistent in the two tunnels，because the total enthalpy and the dynamic pressure of the flow in the wind tunnel are similar with the practical parameter (smaller than 3%). But in the state of Ma6，there are significant differences of the performance results of scramjet，because the total enthalpies of practical parameters differs by about 10% from the parameters simulated by the wind tunnel which was heated by burning alcohol.

Key words: Combustion heating；Scramjet engine；Experimental investigation

摘要： 为了研究燃烧加热风洞不同模拟方式对超燃冲压发动机性能的影响，采用相同流道的发动机模型，在模拟“静温+静压”的酒精燃烧加热和模拟“焓值+动压”的氢气加热这两种燃烧加热风洞上，开展了不同模拟方式对超然冲压发动机性能对比试验，结合飞行试验数据和对模拟方式的理论推导与分析，对风洞试验数据进行了详细的对比分析。根据分析可知:采用燃烧风洞进行超然冲压发动机性能研究时，模拟参数应该选取“焓值、动压和发动机油气比”等参数；本研究中在Ma5状态时，酒精燃烧风洞来流的“焓值和动压”与实际参数相差不大(小于3%)，其发动机性能与氢气燃烧加热风洞的发动机性能基本一致；在Ma6状态时，酒精燃烧风洞来流的焓值与实际参数相差了约10%，性能也出现了明显的差异。

关键词: 燃烧加热；超然冲压发动机；试验研究