[en] Panel methods for unsteady supersonic flow, such as the Mach box, doublet point and harmonic gradient approaches, calculate the influence of complete panels on each control point, even when only part of a panel lies in the upstream Mach cone of that point. Consequently, the resulting unsteady pressure distributions tend to be discontinuous and noisy. This work presents an alternative unsteady supersonic panel method, whereby the induced potential is calculated using the exact area of each panel that lies in the upstream Mach cone of each control point, including the self-influence. The method is validated through an application to two wind tunnel experiments from the literature, one forced pitching motion test case and one flutter test case.
Disciplines :
Aerospace & aeronautics engineering
Author, co-author :
Dimitriadis, Grigorios ; Université de Liège - ULiège > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale
Kilimtzidis, Spyridon; University of Patras
Language :
English
Title :
An Unsteady Supersonic Mach Panel Method
Publication date :
January 2025
Event name :
AIAA SciTech Forum and Exposition
Event organizer :
American Institute of Aeronautics and Astronautics
