A Navier-Stokes/full potential/free wake method for rotor flows

Navier-Stokes/Full Potential/Free-Wake Method for Rotor Flows

Journal of Aircraft ◽

10.2514/2.2240 ◽

1997 ◽

Vol 34 (5) ◽

pp. 635-640 ◽

Cited By ~ 15

Author(s):

Mert E. Berkman ◽

Lakshmi N. Sankar ◽

Charles R. Berezin ◽

Michael S. Torok

Keyword(s):

Navier Stokes ◽

Full Potential ◽

Free Wake

Download Full-text

A Free-Wake Euler and Navier-Stokes CFD Method and its Application to Helicopter Rotors Including Dynamic Stall

10.21236/ada278000 ◽

1993 ◽

Cited By ~ 7

Author(s):

Ganapathi R. Srinivasan

Keyword(s):

Dynamic Stall ◽

Navier Stokes ◽

Helicopter Rotors ◽

Cfd Method ◽

Free Wake

Download Full-text

THE WING-BODY AEROELASTIC ANALYSES USING THE INVERSE DESIGN METHOD

Modern Physics Letters B ◽

10.1142/s0217984910023918 ◽

2010 ◽

Vol 24 (13) ◽

pp. 1479-1482

Author(s):

SEUNG JUN LEE ◽

DONG-KYUN IM ◽

IN LEE ◽

JANG-HYUK KWON

Keyword(s):

Design Method ◽

The Body ◽

Inverse Design ◽

Navier Stokes ◽

Full Potential ◽

Small Disturbance ◽

Body Effect ◽

Flow Equations ◽

Applicable Range ◽

Inverse Design Method

Flutter phenomenon is one of the most dangerous problems in aeroelasticity. When it occurs, the aircraft structure can fail in a few second. In recent aeroelastic research, computational fluid dynamics (CFD) techniques become important means to predict the aeroelastic unstable responses accurately. Among various flow equations like Navier-Stokes, Euler, full potential and so forth, the transonic small disturbance (TSD) theory is widely recognized as one of the most efficient theories. However, the small disturbance assumption limits the applicable range of the TSD theory to the thin wings. For a missile which usually has small aspect ratio wings, the influence of body aerodynamics on the wing surface may be significant. Thus, the flutter stability including the body effect should be verified. In this research an inverse design method is used to complement the aerodynamic deficiency derived from the fuselage. MGM (modified Garabedian-McFadden) inverse design method is used to optimize the aerodynamic field of a full aircraft model. Furthermore, the present TSD aeroelastic analyses do not require the grid regeneration process. The MGM inverse design method converges faster than other conventional aerodynamic theories. Consequently, the inverse designed aeroelastic analyses show that the flutter stability has been lowered by the body effect.

Download Full-text