| 1. | Numerical simulation of windward vortex shocks about supersonic slender bodies at high angles of attack
超声速大攻角旋成体迎风激波数值模拟 |
| 2. | The increase of drag coefficient is significant at higher angles of attack
鸭翼增大升力的同时也增大了阻力;大攻角时，鸭翼带来的阻力增量较大。 |
| 3. | On the sensitivity of aircraft longitudinal flying qualities to aerodynamic derivatives at high angle of attack
飞机纵向飞行品质对大迎角气动导数的敏感性研究 |
| 4. | Then s - style high maneuver trajectory with high angles of attack is simulated by given control commands of angle of pitch
进行了俯仰平面s型轨迹机动飞行仿真，仿真结果说明了大攻角飞行的高机动特性。 |
| 5. | For example , high - lift ( low speed / high angle of attack ) performance may be required as well as low - lift ( high speed / low angle of attack )
例如高扬程(低速/高攻角)表现以及可能需要低扬程(高速/低迎角) |
| 6. | The shm ( single hole microblowing ) as a new perturbation active control technique has been applied to the slender body with different model noses at zero sideslip and high angle of attack
摘要在亚临界流动范围内，对具有不同头部形状的尖拱形细长旋成体在无侧滑大迎角下进行单孔位微吹气扰动控制实验。 |
| 7. | For instance , the velocity distribution can be prescribed for the upper surface at a high angle of attack while simultaneously the velocity distribution can be prescribed for the lower surface at a low angle of attack
比如可指定的速度分布在水面上的高攻角的同时,可以在指定的速度分布在低角度下地面攻击 |
| 8. | The analyses indicate that the shm ' s control ability has strong adaptability to various slender body at high angles of attack , and its control ability is determined by the original state of the flowfield around the slender body
实验分析表明，单孔位微吹气扰动这一大迎角非对称控制手段具有较强的适应能力，其控制能力的大小则由该头部形状的初始状态决定。 |
| 9. | The angle of attack and the sideslip angle are the two important measured quantities for the aircraft navigation / control aerodynamics analysis and structure analysis . for the different kinds of disturbance influence , now the sensors ca n ' t measure it accurately , in the high angle of attack , the error will add with the angle of attack increase
迎角和侧滑角是飞机飞行导航控制、航电等方面重要的两个测量量，由于受到各种干扰因素的影响，现代传感器很难对其精确测量，在超大迎角飞行过程中，其测量误差随迎角增加而增加。 |
| 10. | Compared with a delta wing aircraft , the double - delta wing configuration has better aerodynamic performance at high angles of attack . an operational analysis was introduced as a method for evaluating training effectiveness of trainer aircraft . approaches to the engineering estimation of aerodynamic characteristics for aircraft with a double - delta wing configuration were studied , and the procedures for determining aircraft performance indices formulated . taking training effectiveness as the objective function and geometric parameters of the wing platform as design variables , through a numerical multivariate optimization arithmetic , the conceptual design optimization for a certain fighter trainer aircraft with double - delta wing configuration was carried out under the constraints of tactical and technical requirements and interrelated geometry . agreement of a calculation example with engineering practice indicates that the optimal design has higher training effectiveness than the baseline design , and in addition , improves the structural force - bearing conditions
双三角翼气动布局比三角翼飞机具有更好的大攻角空气动力特性.引入了评估教练机训练效能的作战分析法,研究了双三角机翼布局飞机空气动力特性的工程计算途径以及飞机性能指标的确定方法.以训练效能作为目标函数并选取机翼平面形状的几何参数为设计变量,采用多变量数值寻优方法,在战术技术指标及相关几何约束条件下,对某高级教练机的双三角机翼气动布局方案进行了优化选择.算例表明最优方案不仅比原准方案具有更高的训练效能,还改善了结构的受力情况,与工程实践吻合 |
