超临界CO2流体声速随压力和温度变化规律，对超声技术强化超临界流体萃取应用具有理论指导作用。
The laws of ultrasonic velocity with respect to pressure and temperature in supercritical fluid CO2 can provide a theoretical guide in ultrasonic enhancing supercritical fluid extraction.
得到了高速旋转工况下对应于不同来流攻角和旋转角速度，临界工况时，超声速进气道内外流场复杂的波系结构。
Complex wave structures of supersonic inlet at different Angle of attack and spinning velocity related to high speed spinning and critical status were achieved.
本文采用二维可压缩非定常N-S方程模拟了带有上下开槽壁的跨声速二维管风洞中超临界翼型绕流的流场。
Transonic tube wind tunnel flows over supercritical airfoils with slots on both upper and lower walls have been simulated by using compressible unsteady two dimensional Navier-Stokes equations.
通过跨声速标模算例AGARD445.6机翼的颤振计算，计算的颤振临界速度与实验值有5%左右的误差，验证本方法的正确性。
The computing AGARD445.6 wing flutter results validate the physical law of a typical transonic flutter "dip" with the bottom near the domain which Mach number is 1.
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.
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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