Publication Date:
2019-07-13
Description:
An improved higher order panel method for linearized supersonic flow is described. Each panel, defined by four points on the surface, is divided into eight subpanels in such a way that all subpanel and panel edges are contiguous. By prescribing a quadratic distribution of the doublet on each subpanel, the doublet strength is made strictly continuous on the paneled surface. A linear source distribution is also used. Numerical results are smoother and in better agreement with experiment than the previous method with less strict continuity. A brief discussion of superinclined panels used to eliminate interior interference in nacelles is included.
Keywords:
AERODYNAMICS
Type:
AIAA PAPER 78-15
,
Aerospace Sciences Meeting; Jan 16, 1978 - Jan 18, 1978; Huntsville, AL
Format:
text
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