Transonic Flow Computations with Separate Treatment of the Subsonic and Supersonic Regions

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Report Number: AFWAL TR 80-3091
Author(s): Guderly, K. G.
Corporate Author(s): University of Dayton Research institute
Date of Publication: 1980-08-01
Pages: 35
Contract: AFOSR 78-3524
DoD Project: 2304
DoD Task: 2304N1
Identifier: ADA090327

The report outlines a method for the computation of transonic flow fields in which one applies a finite element approach to the subsonic region, and the method of characteristic for the supersonic region and matches the two results at the sonic line and at the shock. The equations for the subsonic region can be obtained from Bateman's extremum principle. In each iteration step a preliminary location of the sonic line and of the shock is obtained. A new iteration step computes for this approximation of the sonic line and the given profile contour an exact supersonic flow field, and in addition, still from the supersonic region, the changes which occur in this field at the current sonic line and at the current shock location, if one changes the shape of the sonic line in a systematic manner.

Provenance: IIT

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