| 1. | It is a resistance device without pressure recovery .
这是一种没有压力补偿的阻尼式装置。 |
| 2. | Liquid pressure recovery factor
液体压力恢复系数 |
| 3. | The value of exercise test systolic pressure recovery rate in diagnosis of coronary heart disease
运动试验收缩压恢复比对冠心病的诊断 |
| 4. | Pressure recovery system ( prs ) is one of the key techniques for the high energy chemical lasers ( hecl )
压力恢复系统( prs )是高能化学激光器的关键技术之一。 |
| 5. | When there are struts at the divergent parts of inlet , the total pressure recovery coefficients and the kinetic energy coefficients of inlet decrease , and the flow distortion index increases obviously
当进气道扩压段有侧向支柱存在时，进气道总压恢复系数和动能系数均有所降低，而流场畸变指数则显著增大。 |
| 6. | 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。 |
| 7. | 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。 |
| 8. | 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。 |
| 9. | The keep - up pressure recovery of most oil - gas reservoirs and the gas storage measurement on some depletion reservoirs have been made in china , which have endlessly caused variation of pressure difference between inside - pore and outside - pore , followed by always changes of compressibility , porosity and permeability of rocks due to injection and production time and again of reservoir fluids
摘要目前我国许多油气藏进行了保压开采措施及对部分衰竭油气藏进行储气库改造措施，油气藏流体反复注采，使得孔隙内外压差不断变化，导致岩石压缩系数、孔隙度、渗透率发生着不断的变化。 |
| 10. | 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。 |
