Transonic Kernel Function Method for Unsteady Flow Calculations Using a Unified Linear Pressure Panel Procedure.
Final rept. 1 Mar 78-30 May 79,
NORTHROP CORP HAWTHORNE CA AIRCRAFT GROUP
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A transonic kernel function method for unsteady flow calculations has been developed. A unified linear presssure panel procedure is established to solve for two-dimensional problems in the subsonic, transonic, and supersonic flow regimes consequently, a TLP2D computer code is developed. Numerical results are presented for pitching or flapping airfoils in these linear and nonlinear flow regimes. The mixed kernel function procedure is applied to a pitching Guderley airfoil in sonic flow. Comparisons with other results and discussions are given. Additional analytical studies include Landahls general formulation of the phase correction method and the kernel function formulation of the Eckhaus-Landahl shock-jump model. Finally, assessments of and recommendations for the present work are given. Author
- Numerical Mathematics
- Fluid Mechanics