Redesign of a supercritical wing in the presence of an engine nacelle
type: Item
instance of: scholarly article
title: Redesign of a supercritical wing in the presence of an engine nacelle
zbMATH Open document ID: 0631.76062
DOI: 10.1016/0021-9991(87)90135-5
author: David S. Ross
published in: Journal of Computational Physics
publication date: 1987-01-01T00:00:00Z
review text: A method for modelling an engine nacelle in a compressible flow using a source distribution is described. The incorporation of this technique into a free boundary supercritical wing design code is discussed. Results of calculations made with this code are presented. A method for calculating wave drag is also described.
Mathematics Subject Classification ID: 76H05
Mathematics Subject Classification ID: 76M99
zbMATH DE Number: 4027052
zbMATH Keywords: modelling an engine nacelle
zbMATH Keywords: compressible flow
zbMATH Keywords: source distribution
zbMATH Keywords: free boundary supercritical wing design code
MaRDI profile type: Publication
full work available at URL: 0021-9991(87)90135-5
OpenAlex ID: W2069047297
cites work: A theory of supercritical wing sections, with computer programs and examples
cites work: Supercritical wing sections II. A handbook
cites work: Supercritical wing sections. III
cites work: Computation of wave drag for transonic flow
cites work: Design of supercritical swept wings
cites work: Numerical Calculation of Transonic Potential Flow about Wing-Body Combinations
cites work: Calculation of plane steady transonic flows
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description: scientific article; zbMATH DE number 4027052