临界马赫数

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

前掠机翼拥有许多优越的气动特性，如临界马赫数高、波阻小和翼尖失速度大等优点。

Forward-swept wing has many advantages in aerodynamic characteristics , such as high critical Mach number , low wave drag and no wingtip stalling .

超音速时，存在临界马赫数Macr，出现极限环运动。

In the supersonic , there exists a critical Ma cr , and it becomes a circular limit motion .

气流密度，平板密度影响着系统的初始能量，薄板长宽比影响着系统发生颤振的临界马赫数。

Air density and plate density decided the initial energy of the system , the length and width ratio affects the critical Mach number when the flutter occurs .

分析了相同的回转椭球体在不同介质中的临界马赫数以及相同来流马赫数下不同介质中压缩性影响程度。

The critical Mach number of the same spheroids in the different medium is deduced and the effect of compressibility under the same Mach number of main flow is analyzed .

前掠翼飞机气动特性优越，具有包括临界马赫数高、波阻低和克服翼尖失速等很多优点，但扭转发散问题也是制约前掠翼机广泛实用化的障碍。

Torsional divergence problem is an obstacle in the application of forward-swept wing aircraft , despite its many advantages in aerodynamic characteristics , such as high critical Mach number , low wave drag and no wingtip stalling .

当来流马赫数很高时，槽道激波前的当地最高马赫数控制在1.25左右，有效的降低了叶栅的损失，并且有着较高的叶栅临界马赫数。

When the mach number of inflow is high , the mach number where is in front of the shock is controlled about 1.25 . It effectually reduces the energy loss , and increases the critical mach number of the cascade .

第一部分是忽略了平衡方程中的非线性项，运用伽辽金法研究了超声速气流中平板系统的颤振，分析了不同参数对平板稳定性的影响，得出了系统的临界马赫数。

One part is that we neglected the influence of the nonlinearity and studied the flutter of plate in supersonic air flow . Beside this , we analyzed the influence of the parameters on the stability of the panel and came to the critical Mach number .

这与叶栅通道内声速区产生的临界进口马赫数0.3吻合，说明了叶栅中激波系结构对通道内的端壁区三维流动有改善作用。

This fits the critical sound velocity area produced in the blade channels when the inlet Mach number is 0.3 , and shows the shock wave structure in the blade channels can help wall three dimensional flow area improved .