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