A Panel Method for Supersonic Flow
2003 (English)Licentiate thesis, monograph (Other academic)
Supersonic airflow is usually described by a nonlinear hyperbolic system of equations. In this thesis we consider an aircraft represented by a union of thin plates orthogonal to the direction of Right, and describe the derivation of an approximate linear model for the airflow around it. The linear model is reduced to a system of integral equations.
We propose a new set of functions to approximate the solution to the integral equation system and a panel method to solve the system in the stationary case based on those functions. A set of exact solutions on an infinite strip is derived and is used to verify the method.
Place, publisher, year, edition, pages
Linköping: Linköpings universitet , 2003. , 54 p.
Linköping Studies in Science and Technology. Thesis, ISSN 0280-7971 ; 1039
IdentifiersURN: urn:nbn:se:liu:diva-23166Local ID: 2571ISBN: 91-7373-735-6OAI: oai:DiVA.org:liu-23166DiVA: diva2:243480
2003-12-01, Lärosal Schrödinger, Fysikhuset, Linköpings universitet, Linköping, 10:15 (Swedish)
Weinerfeldt, Per, Docent