飞行马赫数的英文

• flight mach number

• "飞行"英文翻译    flight; flying; aviate; voya ...
• "马赫数"英文翻译    Mach number
• "火箭发动机工作时的飞行马赫数" 英文翻译 :    rocket mach
• "大马赫数飞行" 英文翻译 :    high mach flight
• "马赫数" 英文翻译 :    [物理学] mach number◇马赫数表 machmeter; 马赫数计算机 mach-number computer; 马赫数效应 mach number effect
• "飞行高度与飞行马赫关系图" 英文翻译 :    mach-altitude
• "飞马赫数的速度飞行" 英文翻译 :    make mach
• "马赫数受限制的飞行高度" 英文翻译 :    mach limit altitude
• "变马赫数" 英文翻译 :    varying mach number
• "表观马赫数" 英文翻译 :    apparent mach number
• "出口马赫数" 英文翻译 :    exit mach number
• "磁马赫数" 英文翻译 :    magnetic mach number
• "达到马赫数" 英文翻译 :    hit mach
• "当地马赫数" 英文翻译 :    local mach number
• "等马赫数线" 英文翻译 :    contour; mach number
• "低马赫数" 英文翻译 :    low mach number
• "低马赫数区" 英文翻译 :    low mach region
• "发射马赫数" 英文翻译 :    launch mach number
• "风油马赫数" 英文翻译 :    tunnel mach number
• "固定马赫数" 英文翻译 :    constant mach
• "基准马赫数" 英文翻译 :    datum mach number; reference mach number
• "机翼马赫数" 英文翻译 :    mach number of wing
• "激波马赫数" 英文翻译 :    shock mach number
• "进口马赫数" 英文翻译 :    inflow mach number; inlet mach number
• "近壁马赫数" 英文翻译 :    wall mach number

• 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。
• The main results are : supersonic region and subsonic region can co - exist in flow path simultaneously , subsonic flow is insignificance for engine performance ; total pressure of primary rocket should be decreased when mach number is increased . in the experimental aspect , some components of ejectorjet experimental system were improved , ejectorjet experiments using alcohol as secondary fuel were conducted
  由数值计算获得的结论为：引射火箭内的一般流态为超音速区与亚音速区共存，亚音速区不具备做功能力；飞行马赫数增大，引射火箭内更易于产生壅塞；为了获得最佳的性能，随着飞行马赫数的提高，应当降低一次火箭的工作压强。
• In this paper , maccormack explicit time - split scheme , baldwin - lomax algebraic turbulent model and two - steps hydrogen - air nonequilibrium chemical kinetics model are employed to simulate the 2 - d flow fields in a fixed geometry scramjet combustor in different injecting way of fuel in different flight conditions . the results show , in the same entrance condition , the operating mode of scramjet combustor is influenced by the control of fuel
  本文采用maccormack显式时间分裂法、 b - l代数涡粘性湍流模型及氢-空气两步非平衡化学动力学反应模型，模拟了在不同的飞行马赫数条件下，固定几何的双模态燃烧室在不同供油规律下的二维燃烧流场。