升力系数

在一定的条件下，Gurney襟翼可以明显增加翼型的升力系数但不过多增加阻力系数。

Under some condition , Gurney flap can increase lift coefficient and lift drag ratio of the airfoil .

通过CFD模拟发现，具有后加载造型、相对厚度大于40%的翼型压力面出现明显分离，造成翼型小攻角失速、升力系数下降。

Turbulent separation occurs on pressure surface at small attack angles for the airfoils which relative thickness more than 40 % , making airfoil stall at small attack angles and the lift coefficient decrease .

然后用推进阵面法建立了人-椅系统平面模型的非结构网格，并用Euler方程作为主控方程对某型座椅的气动阻力系数、升力系数和气动力矩系数进行了验证性计算；

Then unstructured grids of two dimensional seat is constructed by the advancing front method , Euler equations are solved and aerodynamic damp , lift and moment coefficients of the seat are calculated at certain attack angles and Mach numbers .

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。

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 .

本文应用有限基本解法（涡格法）及联合流场概念，计算出CK-1机带翼梢小翼的升力系数及诱导阻力系数。

The lift coefficient and induced drag coeffcient of the CK-1 wing with winglets are calculated in . this paper by the vortex-lattice method and the concept of united flowfield being used .

数值模拟了流场的变化特征，分析了各种攻角下，具有方形截面的高层建筑的升力系数、抗力系数和Strouhal数。

The present discrete vortex model combined with singularity method can be easily applied to a building with complicated shape . The characteristics of wind field are numerically simulated , the lift and drag coefficients and Strouhal numbers are analyzed for several angles of attack .

以最大升力系数为目标函数，对前缘缝翼或襟翼的位置和偏角进行优化。

We take the maximum lift coefficient as the objective function .

升力系数不变时跨音速机翼阻力优化设计

Optimization Design of Transonic Wings with Drag Reduction and Constant Lift Coefficients

低雷诺数下旋转圆柱升力系数数值计算分析

Numerical Calculation for Lift Coefficient of Rotating Circle Cylinder at Low Reynolds

非球形颗粒的阻力系数与升力系数的数值求解

Drag and Lift Forces Acting on Rotational Nonspherical Particles

气流中颗粒阻力系数和升力系数讨论

Discussion on drag coefficient and lift coefficient of saltation particles in air flow

特别是其倒车性能良好，此时升力系数比正车高16%。

The lift coefficient when backing is 16 % higher than when advancing .

机翼／机身低亚声速最大升力系数预测方法

A Prediction Method of Maximum Lift Coefficient for Wings / Bodies at Low Subsonic Speeds

汽车在车轮旋转情况下，阻力系数和升力系数比车轮静止情况下的低。

The coefficient of drag and coefficient of lift in the circumstance of rotating wheels is lower .

优化后的举升机构，有较好的举升力系数曲线和油压特性曲线。

The lifting mechanism after optimization features better characteristics curves of lift force factor and hydraulic pressure .

脊状结构的存在对模型升力系数和俯仰力矩系数几乎没有影响。

The riblet structure has almost no influence on the lift coefficient and pitching coefficient of model .

获得了一组在不同升力系数下阻力系数最小的翼型形状。

A set of airfoil shape , which have minimum drag coefficient at different lift coefficient , is obtained .

压强分布和升力系数的计算值与现存文献的数值结果和实验数据是一致的。

Predicted pressure distribution and lift coefficient are in agreement with numerical results and experimental data available in the literature .

其高宽比增加，升力系数增大，阻力系数减小。

When the ratio of height to width increases , the lift coefficient aggrandizes , and the drag coefficient diminishes .

结果表明：所有工况条件下，加襟翼都能够增加升力系数。

The lift and drag coefficients were determined from the surface pressure distributions , which were measured under all tested conditions .

分析表明，单拱阻力系数变异性较小，升力系数与力矩系数变异系数较大。

The results show that drag force coefficients variability is small , and lift coefficients variability and moment variability are big .

当冲角为25°和28°时，网板的升力系数均为1.68。

The lift coefficient was 1.68 and higher than tested other boards when attack angle was 25 ° and 28 ° .

计算结果表明在翼型背部引入适当射流会降低振动，并且基本上不影响翼型的升力系数。

The numerical results show that the appropriate blowing will reduce the oscillation amplitude , without significant influence to the lift coefficient .

首先，给出固定圆柱绕流的数值模拟结果和锁定现象的判别方法：当频率比（振动圆柱的频率和固定圆柱的漩涡脱落频率之比）fr<1时，利用升力系数的频谱图；

The numerical results of the flow about the corresponding fixed cylinder and the identification method of lock-in phenomenon were firstly given .

着重研究了三维圆柱的阻力系数、升力系数和斯脱罗哈数随Re数的变化规律及其三维流动特性。

The simulation is focused on three-dimensional flow characteristics and variation of drag coefficient , lift coefficient and Strouhal number with different Reynolds .

最终所获得优化构型较于初始构型其最大升力系数具有明显的提高。

As a result , the maximum lift coefficient of the final optimized geometries , compared with the initial one , is significantly improved .

此外，对于分析参数，采用单变量升力系数模型时，疲劳分析结果偏于保守。

Besides , on the analysis of parameters , single-variable model for lift coefficient , the fatigue results of the analysis are somewhat conservative .

结果表明，增加尾翼面积对增加阻力系数作用明显，对升力系数及转动力矩系数影响较小。

Results show that the increase of area of wings has significantly increase the drag coefficient , less about lift coefficient and torque coefficient .

此外，后柱升力系数也在一定范围内随气流偏角而线性增长。

Besides , the lift coefficient of the downstream cylinder increases linearly with angular deviation in a suitable range of spacing and angular deviation .

在失速迎角后，尖顶襟翼对升力系数的提高有明显的效果，而对阻力系数的影响不大；

The apex flap deployment had a promising effect on the lift after stalling angle , but it had little effect on the drag .