当来流以亚声速度v∞（相应的流动马赫数Ma∞，比如小于0.6）流过翼型时，上翼面的最大速度点c的vc>v∞，因为有可压缩性的影响，点c处的温度最低，该点处的声速也最小，故点c的局部马赫数Mac是流场中最大的，比如说现在Mac<1.0。
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热空气可使之在超过临界马赫数之前达到更快的速度。
The hot air permitted higher speeds before the critical Mach number was exceeded.
可燃气体初始温度和压力对起爆临界马赫数都有影响，但是初始温度的影响大得多。
The critical Mach number is influenced by the initial pressure and temperature, but the temperature is the main factor.
针对各种温度、压力下，马赫数2．5流场中超临界煤油的超声速燃烧性能进行了实验研究。
Characteristics of supersonic combustion by injecting supercritical kerosene fuel into a Mach 2.5 crossflow at various preheat temperatures and pressures were investigated experimentally.
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