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首页> 外文会议>AIAA Modeling and Simulation Technologies Conference 2017 >Modeling Flow Separation for Real-Time Flight Simulation Using Vortex Methods
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Modeling Flow Separation for Real-Time Flight Simulation Using Vortex Methods

机译：使用涡旋法对实时飞行仿真进行流分离建模

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To comply with new requirements for flight simulators regarding stall recovery training, new aerodynamic models are needed. Current computing performance is not sufficient to solve the Navier-Stokes equations numerically in real-time. Hence, a simpler and faster two dimensional unsteady aerodynamic model is developed to predict force and moment coefficients for a flight simulation. The model is based on a potential solver to satisfy the Neumann boundary conditions on an airfoil's surface, a Kutta condition at the trailing edge and a separation condition near the leading edge. A linear solver calculates the strength of sources and vortices on the airfoil's camber line and of two new free vortices that are generated at every time step. The main focus of the model is a fast simulation of the unsteady aerodynamic forces and moments generated by the airfoil and the unsteady wake system behind the airfoil. The wake is modeled by two vortex sheets that form from the free vortices. The strength of the shedding vortices depend on the Kutta and separation conditions. The separation condition is adjusted to achieve a lift polar for the simulated flow that matches a given lift polar for the considered airfoil.
机译：为了符合有关失速恢复训练的飞行模拟器的新要求，需要新的空气动力学模型。当前的计算性能不足以实时地数值求解Navier-Stokes方程。因此，开发了一种更简单，更快的二维非定常空气动力学模型来预测飞行模拟的力和力矩系数。该模型基于电势求解器，可以满足机翼表面的Neumann边界条件，后缘的Kutta条件和前缘附近的分离条件。线性求解器计算机翼弯度线上的源和旋涡的强度，以及在每个时间步长生成的两个新的自由旋涡的强度。该模型的主要重点是快速仿真由翼型和翼型后面的非稳定尾流系统产生的非稳态气动力和力矩。尾流由自由涡流形成的两个涡流片模拟。脱落涡流的强度取决于Kutta和分离条件。调整分离条件以实现模拟流的升力极，该升力极与考虑的机翼的给定升力极匹配。

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