| 1. | The velocity at the stagnation points is zero .
在停滞点处，流速为零。 |
| 2. | Flow noise scaling at the stagnation point of an axisymmetric body
回转体驻点处的流噪声相似律 |
| 3. | The key factors affecting the stagnation point position of l - type pipeline section are the setting position of bellows type expansion joint and the bend angle degree
影响水平转角管段驻点位置的主要因素为波纹管补偿器设置位置、弯头角度。 |
| 4. | The calculation of stagnation point position of straight pipeline section with both movable ends and l - type pipeline section with bend at one end and bellows type expansion joint at other end is discussed
摘要探讨了两侧为活动端的直管段及一侧活动端为弯头，而另一侧活动端为波纹管补偿器的水平转角管段驻点位置的计算。 |
| 5. | Abstract : approximate methods for calculating aerodynamic heating rates on space shuttles are discussed . various methods are given for predicting the heating rate at axisymmetric stagnation points , general three dimensional stagnationpoints and the leading edge stagnation point of wings . numerous laminar and turbulent heating techniques for flat plates and cones are analyzed and compared . a brief review of some methods is presented to predict heating rate for winward centerline and lateral direction off the symmetry plane . the results show that the methods are simpler and can guarantee enought precision for predicting aerodynamic heating environment of space shuttles
文摘:介绍了国内外预测航天飞机气动加热的工程计算方法.给出了轴对称、非轴对称和机翼前缘等各种外形驻点热流密度的计算，分析和比较了平板、锥体的层流和湍流热流密度计算的各种方法，概述了航天飞机迎风面中心线和离开中心线横向热流密度的计算.计算结果表明，本文方法用在航天飞机气动热环境初步设计中比较简单并且有足够精度 |
| 6. | The results show that , for reynolds number of 4400 ~ 23800 , heat transfer coefficients at stagnation point always increase with the increasement of reynolds number ; the average deviation of heat transfer coefficients at stagnation point from published results is about 10 . 8 % , which shows the system is reliable for temperature measurement
实验结果表明，在re = 4400 28300范围内，驻点区换热系数随雷诺数的增大而增大；驻点区换热系数与前人的实验结果相比平均误差10 . 8 ，实验系统具有很好的可靠性。 |
| 7. | The main numerical method of this code is coming from scheme ( jameson , schimit and turkel ) : using cell - centered finite volume method as spatial discretization tools , and a system of ordinary differential equations for time variable is obtained , which is solved by utilizing five - step runge - kutta scheme as time marching method , introducing artificial dissipation to damp high frequency oscillations near the shock and stagnation point
本论文采用欧拉方程作为控制方程，利用中心有限体积法进行空间离散，得到对时间变量的常微分方程组，采用龙格库塔多步法进行时间积分，加入人工粘性以消除激波和驻点附近的压力振荡等方法来对naca0012翼型的实际流动进行并行数值模拟。 |
| 8. | It is found that , the heat transfer coefficients in the area after at stagnation point is higher than that of common jetting although the heat transfer coefficients are smaller at stagnation point , and , comparing to common jetting , rotary jetting contributes to the even distribution of heat transfer coefficients near stagnation point
结果表明，尽管旋转射流的努谢尔特数在驻点附近低于普通射流的努谢尔特数，但在壁面射流区高于普通射流的努谢尔特数。与普通射流相比，旋转射流导致驻点附近区域的换热特性趋于均匀化。 |
