Accession Number : ADP007812
Title : Numerical Simulation of Shock Stall Flutter of an Airfoil using the Navier Stokes,
Corporate Author : NATIONAL AEROSPACE LAB TOKYO (JAPAN)
Personal Author(s) : Isogai, K.
Report Date : MAR 1992
Pagination or Media Count : 12
Abstract : In order to confirm, qualitatively, the unusual flutter phenomenon, which has been observed experimentally for the high-aspect-ratio (non-tailored) forward swept wing model, as a shock-stall flutter, the aeroelastic response calculation of a two dimensional airfoil whose vibration characteristics are similar to those of the typical section of a forward swept wing, has been performed by using the compressible Navier-Stokes equations as a flow solver.
Descriptors : *FLUTTER, *SWEPTFORWARD WINGS, AIRFOILS, EQUATIONS, MODELS, NAVIER STOKES EQUATIONS, RESPONSE, SHOCK, TWO DIMENSIONAL, VIBRATION, JAPAN, ASPECT RATIO, STALLING, COMPRESSIBLE FLOW.
Subject Categories : Aerodynamics
Distribution Statement : APPROVED FOR PUBLIC RELEASE