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The sports wing flow field Euler equation solving

Author: ZhouChengGang
Tutor: SongWenPing;LuYingYu
School: Northwestern Polytechnical University
Course: Fluid Mechanics
Keywords: Airfoil Euler equation Finite volume method Two - time method Dynamic Grid
CLC: V211.41
Type: Master's thesis
Year: 2002
Downloads: 220
Quote: 2
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The paper uses the finite volume method combined with double- time to promote the technology value solving the three-dimensional non-stationary constant Euler equations , to simulate a wing in the state of motion of non-stationary constant flow field , double- time propulsion method for solving non regular Euler equation , can greatly improve the unsteady flow field calculation efficiency . An example shows , this paper calculated in good agreement with the experimental data . The main work is reflected in the following aspects: 1 . In which the campaign grid technology . Based on the theory of infinite interpolation using generalized the infinite interpolation to generate grid around the wing OH , the calculated results show that the grid generation method is feasible and effective . 2. Suitable for the calculation of the unsteady flow field is derived Euler equations , and solving the unsteady flow field of the moving wing . Periodic motion changes over time due to the wing , Euler equations in the absolute coordinate system , control the physical parameters of the equation is the absolute coordinate system variables to facilitate analysis . In order to improve the computational efficiency , double- time marching method for solving the unsteady flow field of the moving wing . 3. This article uses the finite volume method for spatial discretization , the two - time method for time advancing pseudo - time integral of a five-step Rung-Kutta method to solve unsteady flow field sports wing ; using the local time step method , implicit residual accelerate the convergence of technologies such as smoothing ; causing changes in the flow field variables for the deformation of the grid in the wing during exercise , He Shouheng law to guarantee the conservation of flow field variables . And NACA64A010 to NACA0012 airfoil wing D unsteady calculations show a good agreement with the experimental results of this calculation .

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CLC: > Aviation, aerospace > Aviation > Basic theory and experiments > Aerodynamics > Aircraft aerodynamics > Wing aerodynamics
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