1.
An aircraft instrument that indicates speed in Mach numbers.
马赫表装于飞机上的一种以马赫数来显示速度的仪器
2.
Mach limit altitude
马赫数受限制的飞行高度
3.
Empirical results are needed in the transonic Mach regime.
在跨音速马赫数范围内需要经验结果。
4.
The main flow is approximately dependent only on Mach number.
主流仍然近似地只同马赫数有关。
5.
③height H=11000m, Mach number M=1.4, attack angle α=0, sideslip angleβ = 10 deg.
③高度11000米,马赫数为1.4,10侧滑角。
6.
②height H=11000m, Mach number M=1.4, attack angle α = 10deg, sideslip angle β=0;
②高度11000米,马赫数为1.4,10度攻角;
7.
Implicit algorithms for viscous flow simulation at arbitrary Mach number
计算全马赫数下粘性流动的隐式算法
8.
Experimental study on the vortex tubes with different Mach number nozzles
喷嘴马赫数对涡流管性能影响的实验
9.
Boundary Conditions for Solving Flowfields at Low Mach Numbers by Preconditioning
预处理方法求解低马赫数流场的边界条件
10.
Conceptual design of Mach number 3.5 air-breathing propulsion system
最大飞行马赫数3.5的吸气式动力方案初步研究
11.
Effects of incoming Mach number on secondary mass flow rate
来流马赫数对引射火箭引射量的影响研究
12.
Convergence Characteristics of Preconditioned Euler Equations at Low Mach Numbers
低马赫数流动中的预处理Euler方程的收敛特性
13.
however,the difference decrease to 2.6% when the inflow Mach number increases to Ma 8.
而当来流马赫数为8.09时,侧板前掠的进气道流量系数仅高2.6%。
14.
When Ma(subscript e)=0.45 the relative suction flow rate equals 0.043, the total pressure recovery increases by 2.6%.
在出口马赫数为0.45，相对抽吸量为0.043时总压恢复系数提高了2.6%。
15.
Unsteady numerical simulation of the inlet with a bleed slot in oscillating flow
马赫数振荡状态下带抽吸槽进气道非定常数值模拟
16.
Direct numerical simulation of a spatially evolving hypersonic blunt cone turbulent boundary layer at Mach 6
马赫数为6的高超声速钝锥湍流边界层空间演化的直接数值模拟
17.
Numerical study of the cold flowfield of Mach number 2.5 supersonic combustor with supersonic/subsonic streamwise vortices mixing
马赫数2.5超燃室中超/亚声流流向涡掺混冷态流场数值研究
18.
Ramjets work Best at speeds of Mach 2 (twice the speed of sound) and higher.
冲压式喷射发动机在马赫数为2(音速的两倍)或更高时工作得最好。