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在冲压发动机研究计划范围内,在政府部门支持下,法国国家航空空间研究院研制了一种在巡航段由固体燃料冲压发动机推进的火箭冲压发动机试验导弹。本文的目的,是介绍一些气动试验和计算方法,即能确定和最优选择此类模型进气道的方法。为此,制作了一个比例为1比3、包括多种形式的模型,以便在莫当-阿夫里尔(Modaile-Avrieux)试验中心超音速风洞S2中进行M数为1.8～3的试验。综合试验是在高超音速风洞S4中进行的,这个风洞的喷管M数为2,实际进气情况与零高度相当。文中介绍了比例效应,然后将首次弹道飞行得到的数据与试验结果作了比较。
Within the framework of the ramjet research program, with the support of government agencies, the French National Aeronautics and Space Administration has developed a rocket-stamped engine test missile propelled by a solid fuel-stamped engine during the cruise. The purpose of this article is to introduce some of the aerodynamic tests and computational methods that determine and optimally select the inlet of such a model. For this purpose, a ratio of 1 to 3 was made to include a variety of models for the M-1.8 test at supersonic wind tunnel S2 in the Modaile-Avrieux pilot center . The integrated test was conducted in the hypersonic wind tunnel S4, where the number of nozzles M in the wind tunnel was 2, and the actual intake condition was equivalent to zero height. The paper introduced the proportional effect and then compared the data obtained from the first ballistic flight with the experimental results.