lift-drag ratio

The favorable method of improving the lift-drag ratio of the figuration is brought forward .

分析提出了进一步提高该乘波体气动布局升阻比的有效途径。

Airfoil buffet boundary is an important aerodynamic parameter which is second only to the lift-drag ratio .

翼型抖振边界是仅次于升阻比的一项重要气动指标。

The results show that the lift-drag ratio of Kriging design increases 81 percents comparing with the referenced airfoil ;

结果表明，Kriging方法的设计结果，升阻比较参考翼型提高了81%；

The characteristics of vortex flow movement induced by vortex flaps and the principle of increasing lift-drag ratio of the wing are analyzed .

分析了涡襟翼的涡流运动特点及其升阻比增大的机理；

A primary objective of aircraft design is optimizing the distributing of the flow , drag reduction , increasing lift and the lift-drag ratio .

飞行器设计的一个重要目标，就是要优化流场分布，减少阻力，增加升力，提高飞行器的升阻比。

Maximum lift-drag ratio is 12.The stalling angle is greeter then 30 degree .

连接翼布局气动特性优于常规翼布局，特别是最大升阻比可达12以上，失速迎角超过30°。

The results show that the best effect of glide extended-rang is obtained with the adoption of maximum lift-drag ratio slide .

由数值分析得到采用最大升阻比的滑翔策略可获得最佳滑翔增程效果。

Comparing with original UAV finally , the experimental results show that the maximum lift-drag ratio of the modified UAV increases by20.6 % .

风洞试验结果表明：和原型机相比，改型机的最大升阻比可提高20.6%。

These studies indicate that the effect of rarefied flow remarkably influenced the aerodynamic characteristics of sphere-bicone configuration , especially axial force coefficient and lift-drag ratio .

研究结果表明：稀薄效应对球双锥外形的气动特性，尤其是轴向力系数和升阻比产生非常大的影响；

Because the middle part of a parafoil contributes more to effective lift , the model with a swept back leading edge achieves the maximal lift-drag ratio .

由于翼伞中部区域对有效升力贡献更大，前缘后掠的翼伞模型获得最大升阻比；

The homotopy map for maximum range problem is built by using homotopy method with a large scope convergence property , and the control law of maximum lift-drag ratio is deduced .

首先利用同伦方法的大范围收敛特性，构造原最大射程问题的同伦映射，推导了最大升阻比控制规律，以最大升阻比弹道作为初始解轨迹。

Modification of winglet is adopted to raise the lift-drag ratio of the UAV for extension endurance , for enlarge range and for increase ceiling .

为延长无人机留空时间，加大航程和提高升限，可采用加装翼尖小翼的方法使无人机的升阻比有所提高。

Compared with models with simple Gurney flap , the models with the lower surface curvature modified have bigger lift-drag ratio , and it increases approximately by 14 % .

而与单纯加装Gurney襟翼的模型相比，修改下表面后缘曲率的模型的升阻比可提高14%左右。

Drag has a great impact on the lift-drag ratio , and the leading edge cut drag , which has only a two-dimensional effect , is one of the main sources of the total drag .

阻力对翼伞升阻比影响很大，前缘切口阻力是总阻力的主要来源之一，且是一种二维效应的阻力。

The lift-drag ratio of the newly developed Rosen-type piezoelectric transformers can reach greater than 950 with loading of 100 M Ω and actuation voltage of 5 V.

开发的Rosen型压电陶瓷变压器使用100MΩ负载在5V的低电压驱动下，升压比能达到950倍以上。

This research indicated that grasps the material preparation and the forming process rule , discusses the material preparation and the forming process material organization lift-drag ratio relations thoroughly , it might the effective instruction actual product development .

该研究表明掌握材料制备与成形过程的规律，深入探讨材料制备与成形过程材料的组织-性能关系，将可有效的指导实际产品的开发。

This method is applied to the aerodynamic optimization design of airfoil , defining the lift-drag ratio as the goal function , when Mach number is 0 . 7 and the angle of attack is 3 ° .

用此方法进行了翼型的气动优化设计，目标函数为来流马赫数为0.7、攻角为3°时升阻比最大。

The aerodynamic performance of the combination body of launch vehicle is similar to traditional launch vehicle except for higher lift-drag ratio , and the longitudinal and directional instability can be controlled effectively by swing nozzles .

运载器上升段气动性能与一般运载火箭类似，只是升阻比偏高，使用摆动喷管后可以保证纵向和横向稳定性。

Different from the traditional , vertical spoilers which tend to produce unstable airflow , the annular spoiler can increase the lift-drag ratio by 30 % to 40 % , vastly improving the operation stability .

与往往产生不稳定的气流的传统、垂直的扰流器不同，环形扰流器可以将升阻比提高30%到40%，极大地提高了运行的稳定性。

In this paper , in order to find the approaches to reduce the drag levels and enhance the lift-drag ratio for grid fin , the aerodynamic characteristics of the grid fin are calculated with TVD finite volume scheme and wind tunnel tests .

为了探索减少格栅翼阻力和提高升阻比的方法和途径，本论文对格栅翼的气动力特性进行了数值模拟和风洞实验研究。

While the result of the response surface method is very poor in the original design space . This status is amended effectively through reducing the design space continuously and the lift-drag ratio increases by 70 % , however the calculation cost is far more expensive than the Kriging method .

在初始设计空间，响应面方法的结果很差，通过不断缩减设计空间，设计得到了有效的改善，升阻比提高了70%，但需要的计算量远远高于Kriging模型。

Blended-Wing-Body ( BWB ) aircraft is a tailless large transport with high lift-drag ratio , and the aerodynamic study for BWB aircraft is a basis of overcoming the technology challenges about it . Firstly , research history on BWB configuration is presented in this paper ;

翼身融合飞机（BlendedWingBodyAircraft-BWBAircraft）是一种新型高升阻比无尾布局的大型运输机，其气动特性的研究是BWB布局飞机克服众多技术难题的基础。

The Lagrange multipliers optimization method is presented for wing + winglet configuration with constraint for lifting coefficient and wing root bending moment . By shaping the wing with winglet , decrease the sum of induced drag and profile drag , increase span efficiency and lift-drag ratio .

采用Lagrange乘数优化方法，约束升力系数和机翼翼根弯矩，通过修改机翼+翼梢小翼组合体的结构外形，减小机翼的诱导阻力和形状阻力，提高机翼的展向效率和升阻比的大小。