在非结构自适应笛卡尔网格基础上构建了一种基于笛卡尔动网格的非定常气动力计算方法。
A unsteady flow calculational method is developed in this article. This method is based on the Cartesian grid.
对跨声速飞机机翼作了跨声速非定常气动力计算，对跨声速民航机机翼的颤振模型作了颤振计算，与TDLM的比较表明，两者结果有较好的一致性。
The unsteady aerodynamic results of the transonic wing are presented, and flutter calculation is made. The comparison with TDLM shows that the agreement is very good.
在颤振特性分析中所需要的广义气动力是根据亚音速非定常升力面理论，采用马蹄涡—振荡压力偶极子格网法计算的。
The generalized aerodynamic force required in analysis is calculated by using horse shoe vortex— vibrational pressure doublet grid method, based on theory of subsonic unsteady lifting plane.
作为算例用它计算了后掠超音速平板叶栅由于振动引起的非定常空气动力功。
Program and unsteady aerodynamic work caused by oscillation of sweepback supersonic plate cascade were provided as an example of its application.
完全非定常气动力由格林函数方法直接计算，颤振分析结果准确。
For fully unsteady aerodynamic force is calculated with Green's Function method, the results of flutter analysis are accurate.
用欧拉方程计算非定常气动力，在时域内求解结构运动方程。
Euler equations are applied to calculate the aerodynamic forces, when the time-domain method is used to solve structural motion equations.
桨叶气动力计算采用时域非定常空气动力计算模型，包括非线性分离和动态失速的影响。
Blade element theory was used to calculate unsteady aerodynamic loads in linear and nonlinear regimes.
通过对叶片表面非定常气动力及其所做非定常气动功的计算分析，采用能量法对叶片颤振与否进行预估判断。
Through the computation and analysis of unsteady aerodynamic forces loading on the cascades and aerodynamic work, the probability of blade flutter is predicted through the energy method.
可以提供更详细的多学科计算流体动力学的非定常空气动力学过程的认识，涉及现代制导武器系统机动飞行。
Multidisciplinary computations can provide detailed fluid dynamic understanding of the unsteady aerodynamics processes involving the maneuvering flight of modern guided weapon systems.
在流体域的动网格上，通过求解非定常的雷诺平均N - S方程，计算出翼型表面的非定常气动力。
In the aerodynamics domain, the time-dependant aerodynamic force on the surface of the airfoil is computed by solving the unsteady Reynolds averaged Navier-Stokes equation.
但在实际问题中，常需要了解亚音速机翼作完全非定常运动时气动力的变化规律，目前能作这种计算的方法还不多。
The method is capable of computing the varying aerodynamic force or velocity field in time domain over wings with arbitrary motion.
但在实际问题中，常需要了解亚音速机翼作完全非定常运动时气动力的变化规律，目前能作这种计算的方法还不多。
The method is capable of computing the varying aerodynamic force or velocity field in time domain over wings with arbitrary motion.
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