Accession Number:

ADP007812

Title:

Numerical Simulation of Shock Stall Flutter of an Airfoil using the Navier Stokes,

Descriptive Note:

Corporate Author:

NATIONAL AEROSPACE LAB TOKYO (JAPAN)

Personal Author(s):

• Isogai, K.

Report Date:

1992-03-01

Pagination or Media Count:

12.0

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