A coupled viscid-inviscid calculation method for the prediction of unsteady separated flows over an airfoil

Conference · Thu Jan 01 00:00:00 EST 1987

OSTI ID:5712972

Im, B J; Oler, J W; Strickland, J H

A coupled viscid-inviscid aerodynamic model ADAM2 (Advanced Dynamic Airfoil Model in 2 dimensions) is utilized to predict separated and unseparated flows over airfoils in steady and unsteady motion. Calculation results include pre- and post-stall pressure distributions, lift and drag, and trailing wake geometries for airfoils with a constant angle of attack, sinusoidally varying angle of attack, and constant rate pitching to large angles of attack. The principal difficulty yet to be overcome is the detailed representation of the viscid-inviscid interactions in the immediate vicinity of the boundary layer separation point. A persistent feed-back effect has been observed in which the presence of the separated wake surface causes the position of the boundary layer separation point to move progressively toward the leading edge. 10 refs., 10 figs.

• Research Organization: FloWind Corp., Pleasanton, CA (USA); Texas Tech Univ., Lubbock (USA); Sandia National Labs., Albuquerque, NM (USA)
• DOE Contract Number: AC04-76DP00789
• OSTI ID: 5712972
• Report Number(s): SAND-87-2745C; CONF-880139-1; ON: DE88003391
• Resource Relation: Conference: 26. AIAA aerospace conference, Reno, NV, USA, 10 Jan 1988; Other Information: Portions of this document are illegible in microfiche products
• Country of Publication: United States
• Language: English

Related Subjects

75 CONDENSED MATTER PHYSICS
SUPERCONDUCTIVITY AND SUPERFLUIDITY
99 GENERAL AND MISCELLANEOUS//MATHEMATICS, COMPUTING, AND INFORMATION SCIENCE
AIRFOILS
FLOW MODELS
A CODES
BOUNDARY LAYERS
EXPERIMENTAL DATA
FINITE ELEMENT METHOD
THEORETICAL DATA
COMPUTER CODES
DATA
INFORMATION
LAYERS
MATHEMATICAL MODELS
NUMERICAL DATA
NUMERICAL SOLUTION
640410* - Fluid Physics- General Fluid Dynamics
990220 - Computers
Computerized Models
& Computer Programs- (1987-1989)