Author(s): D. Fokin, L. Gebhardt, Th. Lutz and S. Wagner
The purpose of the present work is to develop a mathematically sound and
efficient field-panel method for the analysis of inviscid transonic flow over 3D
aircraft configurations taking the effects of (weak) shock waves into account.
The problem is reduced to a system of two nonlinear integro-differential
equations for the disturbance potential in the field and the singularity dis-
tribution on a reference surface.
An iteration procedure incorporating the
boundary element method to satisfy the impermeability conditions on the
body (Neumann formulation), coupled with a correction for compressibility
effects based on the full potential equation has been developed.
ficial viscosity concept is used to stabilize the process for transonic cases.
Exemplary results of...
Size: 1,141 kb
Paper DOI: 10.2495/BE010181
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