飞行马赫数 meaning in Chinese
flight mach number
Examples
- In the range of flight mach number mo = 3 ~ 7 , in order to take the advantage of ramjet and scramjet , a fix - shaped dual - mode scramjet , in which both subsonic and supersonic combustion can be obtained , is used for hypersonic vehicle
在飞行马赫数m _ = 3 - 7的范围内，为充分发挥冲压发动机的性能优势，高超声速飞行器采用了既能在亚声速燃烧模态，又能在超声速燃烧模态下工作的固定几何形状的双模态冲压发动机。 - Dual - mode ramjet engine which gathers the advantages of both ramjet and scramjet is a new - style airbreathing propulsion device . it can operate over a wide mach number ranges ( m = 3 - 8 ) . it is of remarkable performance and great potential application for hypersonic vehicle
双模态冲压发动机是综合了亚燃冲压发动机和超燃冲压发动机优势的一种新型的吸气式动力装置，它可以在比较宽广的飞行马赫数范围内工作( m 3 8 ) ，具有良好的工作性能和广阔的应用前景。 - On the basis of these results , the relations of total - pressure recovery coefficient or flow coefficient and flight mach number , angle of attack and the second movable wedge angle of the inlet have been founded by hypersurface fitting , then the mathematical model of the inlet is established
根据流场计算结果并利用超曲面拟合方法建立了进气道总压恢复系数、流量系数与飞行马赫数、进气道攻角及二级可调斜板角度之间的关系，由此得到了二元混压式超声速进气道数学模型。 - The design point of the designed forebody / inlet is flight mach number m = 6 and flight attitude h = 25km . the three - ramp , mixed external and internal compression hypersonic / inlet is chosen as representative geometry to be designed . nine types of hypersonic / inlet model with difference forebody length and total turning angle are obtained that the incidence angle of the first ramp and height of isolator are given
根据飞行任务要求，以飞行马赫数6 ，飞行高度25km为设计点，给定前体预压缩角、隔离段高度，对具有不同前体长度和不同总压缩转角的带隔离段的前体进气道进行了设计。 - The calculation results indicate that the starting performance of forebody / inlet with wedge - shaped lip is better than that with plane lip at low flight mach number . at high flight mach number , the performance of the forebody / inlets designed by the two methods is approximate . at low flight mach number , the starting performance of forebody / inlet designed by the method of constant shock wave intensity is better
结果表明：唇口带楔角的进气道在低飞行马赫数下的起动性能优于唇口平直的进气道；采用等激波强度和等激波角度方法设计的进气道在高飞行马赫数下的性能相近，在低飞行马赫数下，采用等激波强度方法设计的进气道起动性能较优。