| 1. | The effects of trailing edge jets on the vortex breakdown of a delta wing
后缘喷流对三角翼前缘涡的影响 |
| 2. | Effect of apex flap length on leading edge vortex breakdown over delta wings
三角翼前缘涡破裂形式及特性研究 |
| 3. | Leading - edge root extensions lersx
翼前缘延伸面 |
| 4. | Experimental analysis on oscillations of vortex breakdown location over delta wing
三角翼前缘涡破裂点脉动的实验分析 |
| 5. | The effects of vectored jet on leading edge vortex breakdown of 65 176 ; delta wing
矢量喷流对65 176 ;三角翼前缘涡破裂的影响 |
| 6. | Effect of the apex flap on the leading edge vortex breakdown over a 70 176 ; delta wing
尖顶襟翼对70 176 ;三角翼前缘涡破裂的影响 |
| 7. | Experimental studies on leading - edge vortex breakdown and control of flow over 76 176 ; 40 176 ; double delta wing
双三角翼前缘涡破裂及其控制实验研究 |
| 8. | Numerical investigation of the effects of different leading - edge profiles on vortical flows over a double - delta wing
尖顶襟翼长度对三角翼前缘涡破裂的影响 |
| 9. | Experimental investigation for the effects of vectored trailing - edge jets on the leading - edge vortex reakdown of a double delta wing
双三角翼前缘剖面形状对涡运动的影响 |
| 10. | The model is solved with the finite difference method , the simulation software is organized to simulate the transient thermal response of the front region of projectile wing such as those launched by electrothermal chemical guns
采用有限差分法进行数值求解，并编制了较为通用的仿真软件，用于模拟诸如由电热化学炮发射的高超声速穿甲弹弹翼前缘的瞬时热效应。 |
