为了应用试验结果，根据翼段模型试验确定的平尾升力曲线斜率可能要作些修正。
The tail lift curve slope as determined from the panel model may require adjustment in order to apply the test results.
这个方法采用了叶型升力曲线的非线性理论和多流管的理论模型，并对展弦比的影响进行了修正，从而具有广泛的适用性。
Since this method adopts non-linearized theory of the lift coefficient curve of the blade section and multiple streamtube model, and has revised the aspect ratio influence, so it has wide suitability.
升力体模型对流换热系数测量不确定度大致为15%左右。
The uncertainty in measured convective heat-transfer coefficient on lifting body model was about 15%.
利用螺旋的升力线模型和变分法原理对螺旋桨叶片环量分布进行了数值优化。
The optimum distribution of circulation on a marine propeller blade is numerically determined by using the lift_line vortex model and variational calculus.
基于附着流状态下的旋翼非定常翼型气动模型，给出了计算该状态下的翼型非定常升力、阻力和俯仰力矩的数值计算方法。
A numerical method is given to calculate the unsteady lift, pitching moment and drag acting on an airfoil of rotors under attached-flow conditions in a compressible flow.
使用控制理论方法建立了对翼型最大升力优化设计的模型。
A numerical optimization method of airfoil maximum lift design by solving adjoint equations based on ns equations is studied in this paper.
将高速滑体制成相似的机翼模型，进行风洞试验，即可测定滑坡凌空飞行的空气动力学参数，从而计算大型高速滑坡凌空飞行的空气动力升力、飞行速度和飞行距离等。
If we make a wing model which is similar to sliding mass, we can determine aerodynamic parameters by the wind tunnel testing and thus calculate the lift.
从高速水翼双体船受力分析的角度，提出了其静水中垂荡和纵摇运动的数学模型，其中对水翼所产生的升力进行了较为详尽的分析。
In this paper, by analyzing the forces on hydrofoil catamaran, the mathematical model of its heaving and pitching motion is proposed.
采用基于涡系理论的模型建立刚性圆柱尾迹和预定尾迹模型的升力面法预测程序，对无偏航情况的风力机性能进行了预测。
Based on the vortex theory, lifting surface method is used to establish wind turbine performance prediction model with rigid cylinder wake model, prescribed wake model and free-wake method.
哈尔滨工程大学博士学位论文应用三维数值模型模拟不同展弦比机翼的突然起动问题，将计算升力系数与线性理论比较，检验算法的可行性。
To verify three-dimensional numerical scheme, calculated lift coefficients for impulsively started problem of wings with different aspect ratio are compared with linear theory.
基于桨叶二阶升力线理论和旋翼自由尾迹模型，本文在第三章建立了一个适合于直升机旋翼尾迹结构及桨-涡干扰气动特性分析的方法和模型。
In Chapter 3, based upon the blade second-order lifting-line model and rotor free-wake model, an analytical method is developed for predicting the rotor wake structure and BVI airload.
建立了旋翼升力线模型和广义尾迹模型，在计算角迹涡线诱导速度时，采用了快速收效方法。
Both lift line model and generalized wake model are founded in this paper. A method is given for calculating induced velocities by a wake vortex line which results in a rapid convergence.
建立了旋翼升力线模型和广义尾迹模型，在计算角迹涡线诱导速度时，采用了快速收效方法。
Both lift line model and generalized wake model are founded in this paper. A method is given for calculating induced velocities by a wake vortex line which results in a rapid convergence.
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