We studied the influence of 2d supersoni c slope flow to the far field intensity distribution of 10 . 6um and 1 . 315um laser beam when flow is in different inflow mach number 研究了二维超音速绕楔流动在不同马赫数下的流场时均参数分布对波长分别为10 . 6 m 、 1 . 315 m的激光束的远场强度分布的影响。
Therefore , the quasi - static solutions can be recovered from the extreme of dynamic solutions when the mach number goes to zero for the elastic - viscoplastic constitutive model employed in this paper 因此，对于本文所采用的弹粘塑性本构模型，动态解在马赫数趋于零时的极限情况能够还原为准静态解。
The wind tunnel " s control system is a large and complicated system , which including three set control system : mach number system , model attitude system , compressor surveillance - control system 该风洞控制系统较为庞大复杂，共有三套系统：马赫数控制系统、模型姿态控制系统和压缩机控制系统。
The results show that to design a supersonic / hypersonic nozzle of wind tunnel must consider the effect of variable specific heat , which gives reference to nozzle and wind tunnel design 考虑这一因素后，喷管出口马赫数接近设计马赫数，其设计精度有较大提高。本方法可为超音速高超声速喷管设计和反设计提供参考。
Supercritical wings have been widely used on modern civil airplanes and military transports due to their higher aerodynamic efficiency , higher cruising mach number and greater relative thickness 超临界机翼由于其具有较高的气动效率、较高的巡航马赫数及较大的机翼相对厚度而被广泛应用于新一代民用飞机及军用运输机上。
When the serpentine inlet is running at the exit mach number ma ( subscript e ) = 0 . 45 , the total pressure recovery coefficient equals 0 . 90 , and synthesis distortion equals 13 . 85 % 本研究的蛇形进气道在出口马赫数为0 . 45时，总压恢复系数为0 . 90 ，综合畸变指数为13 . 85 % ，总压恢复较低，畸变较大，超出了一般航空发动机的承受范围。
Based on this , adopting labwindows / cvi , the american national instrument corporation " s virtual instrument developing software , develop control system software platform of mach number control 在此基础上，采用美国nationalinstrument公司的虚拟仪器开发软件labwindows / cvi作为测控软件开发工具，开发了马赫数控制系统软件平台。
The verification results show that the theoretical analysis of nozzle is correct , the curve of the nozzle contour satisfies the design requirements , and the designed nozzle has reached the general industry criterion 给出了流场的马赫数分布和出口截面的马赫数。校核结果表明喷管理论分析正确,喷管型面曲线符合设计要求,喷管设计达到行业标准。
Abstract : with an optical probe based on the principle of multi - wavelength light extinction , size and concentration of droplet were measured in a transonic wind tunnel . this paper presents the measurement results 文摘:应用基于多波长消光法原理发展的光学探针，测量了跨声速风洞中不同马赫数湿空气流自发凝结形成的水滴尺寸及浓度，并给出了实验结果。
Numerical fluxes considered in the explicit portion of the algorithm were evaluated by an implicit high - order compact scheme to augment stability . meanwhile , an implicit high - order compact numerical filter was used 显式一边的空间导数采用具有较高精度和良好数值稳定性的隐式高阶紧致差分格式，同时采用适于低马赫数流动计算的隐式高阶数值过滤方法。
