Содержание
- 2. What are panel methods? Panel methods are techniques for solving incompressible potential flow over thick 2-D
- 3. Analogy between boundary layer and vortices Upper surface boundary layer contains, in general, clockwise rotating vorticity
- 4. Panel method treats the airfoil as a series of line segments On each panel, there is
- 5. Boundary Condition We treat the airfoil surface as a streamline. This ensures that the velocity is
- 6. Stream Function due to freestream The free stream is given by Recall This solution satisfies conservation
- 7. Stream function due to a Counterclockwise Vortex of Strengh Γ
- 8. Stream function Vortex, continued.. Pay attention to the signs. A counter-clockwise vortex is considered “positive” In
- 9. Superposition of All Vortices on all Panels In the panel method we use here, ds0 is
- 10. Adding the freestream and vortex effects.. The unknowns are the vortex strength γ0 on each panel,
- 11. Physical meaning of γ0 Panel of length ds0 on the airfoil Its circulation = ΔΓ =
- 12. Pressure distribution and Loads Since V = -γ0
- 13. Kutta Condition Kutta condition states that the pressure above and below the airfoil trailing edge must
- 14. Summing up.. We need to solve the integral equation derived earlier And, satisfy Kutta condition.
- 15. Numerical Procedure We divide the airfoil into N panels. A typical panel is given the number
- 16. Numerical procedure, continued Notice that we use two indices ‘i’ and ‘j’. The index ‘I’ refers
- 17. Numerical procedure, continued.. We thus have N+1 equations for the unknowns γ0,j (j=1…N) and C. We
- 18. Panel code Our web site contains a Matlab code I have written, if you wish to
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