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- The results prove that: (1) When the Mach number of the flow at the exit increases, the total pressure recovery decreases, and the circular steady total pressure distortion coefficient, turbulence intensity and synthesis distortion increase. 研究结果表明：(1)地面工作状态下，随着出口马赫数的增加，蛇形进气道出口截面的总压恢复系数不断下降，而稳态周向畸变指数、紊流度和综合畸变指数均上升，稳态径向畸变指数变化不大。
- inlet total pressure distortion index 进气总压畸变指数
- static total pressure distortion coefficient 静态总压畸变指数
- total pressure recoveryi circular total pressure distortion 气流分离
- Analysis of flow loss induced by inlet total pressure distortion in a small fan 某小型风扇内进口总压畸变引起流动损失分析
- Aerodynamic stability analysis of inlet total pressure distortion for turbofan 某型涡扇发动机进气总压畸变的试验研究
- Experimental Study on the Inlet Total Pressure Distortion of a Turbojet Engine 某型涡喷发动机进气总压畸变的试验研究
- Characteristic and Calculation of Eddy Scale in Total Pressure Distortion Flow at Typical Engine Inlet 某型发动机进气总压畸变流场中涡旋尺度的计算及其变化特征
- The Dynamic Pressure Turbulence Calculation of a Turbofan Engine Total Pressure Distortion Test 涡扇发动机进气总压畸变试验动态总压紊流度计算分析
- Measurements of Dynamic Total Pressure Distortion for Engine Inlet and Analysis of Effective Factors 发动机进气总压动态畸变流场测试及影响因素分析
- Effect of Inlet Total Pressure Distortion on the Performance of a Certain-type Turbofan Engine 进气总压畸变对某型涡扇发动机性能的影响
- Experimental investigation on caret inlet's total pressure distortion controlled by vortex break fence 涡破碎片控制尖脊进气道总压畸变的试验研究
- Ultimate pressure is measured as total pressure. 最后压力是全程压力测量值。
- Inlet total pressure distortion 进气总压畸变
- total pressure distortion 压力畸变
- 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
- Response of an Transonic Two-Stage Compressor to Steady Circumferential Total Pressure Distortions 跨声速双级轴流压气机对周向进气总压畸变的响应特性分析
- Experimental results of the air pumping of a serpentine inlet under ground running show that the total pressure recovery at the exit is low and the distortion at the exit is large. 摘要对一种蛇形进气道开展了地面工作状态下的抽吸试验研究，结果表明，在该状态下进气道出口截面的总压恢复系数较低、流场畸变较大。
- The maximum pressure distortion in the inlet surface increases with the stator moving to the right then has decreasing tendency. 随着静子叶片右移，在进口截面处最大压力畸变逐渐增大，之后呈下降趋势；
- The results show that the circumferential layout of exit-guide-vane can affect the pressure distortion in upstream area effectively. 结果表明，支板和上游叶片的周向相对位置的变化可以有效地改变上游区域的压力畸变分布；
