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Unsteady Navier-Stokes Calculations in an Accelerated Reference Frame.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
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The purpose of this project was to develop a numerical method capable of calculating the laminar flow about a two dimensional accelerating body using the incompressible Navier-Stokes equations. This problem arises in the calculation of the dynamic stall of an airfoil and in the calculation of pitching and heaving stability derivatives for an isolated airfoil. It is also a first step toward solving the three dimensional flow about a complete wing undergoing arbitrary motion at high angles of attack, including departure, spin, and post-stall maneuvers. Numerical calculations to date have not been satisfactory. Test cases presented are Stokes first problem, a circular cylinder translating at a Reynolds number of 20, and a rotating stationary circular cylinder. Keywords include Aerodynamics, Airfoils, Difference equations, Navier Stokes equations.
APPROVED FOR PUBLIC RELEASE