TAWFIVE computer program calculates transonic flow over transport-type wing and fuselage. Combines multigrid acceleration technique in iterative solution of potential equation with use of integral-form boundary-layer equations to provide software tool computationally efficient, yet accurate enough for use in design. Simplifies solution process by breaking problem into loosely coupled set of modified equations. Inviscid-flow method, using standard inviscid-flow equations, valid in "outer" region away from wing, whereas boundary-layer equations valid in thin region near solid surface of wing. Written in FORTRAN 77.
Analyzing Transonic Flow Over A Wing And Fuselage
NASA Tech Briefs ; 17 , 2
1993-02-01
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Englisch
Transonic flow over wing/fuselage configurations
NTRS | 1981
|Transonic Navier-Stokes Flow Computations over Wing-Fuselage Geometries
Online Contents | 1993
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