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Program VSAERO theory document: A computer program for calculating nonlinear aerodynamic characteristics of arbitrary configurationsThe VSAERO low order panel method formulation is described for the calculation of subsonic aerodynamic characteristics of general configurations. The method is based on piecewise constant doublet and source singularities. Two forms of the internal Dirichlet boundary condition are discussed and the source distribution is determined by the external Neumann boundary condition. A number of basic test cases are examined. Calculations are compared with higher order solutions for a number of cases. It is demonstrated that for comparable density of control points where the boundary conditions are satisfied, the low order method gives comparable accuracy to the higher order solutions. It is also shown that problems associated with some earlier low order panel methods, e.g., leakage in internal flows and junctions and also poor trailing edge solutions, do not appear for the present method. Further, the application of the Kutta conditions is extremely simple; no extra equation or trailing edge velocity point is required. The method has very low computing costs and this has made it practical for application to nonlinear problems requiring iterative solutions for wake shape and surface boundary layer effects.
Document ID
19900004884
Document Type
Contractor Report (CR)
Authors
Maskew, Brian (Analytical Methods, Inc. Redmond, WA, United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1987
Subject Category
AERODYNAMICS
Report/Patent Number
NAS 1.26:4023
NASA-CR-4023
AMI-8416
Funding Number(s)
CONTRACT_GRANT: NAS2-11945
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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