FOREBODY TANGENTIAL SLOT BLOWING ON AN AIRCRAFT GEOMETRY

Citation
K. Gee et al., FOREBODY TANGENTIAL SLOT BLOWING ON AN AIRCRAFT GEOMETRY, Journal of aircraft, 31(4), 1994, pp. 922-928
Citations number
NO
Language
INGLESE
art.tipo
Article
Categorie Soggetti
Aerospace Engineering & Tecnology
Journal title
ISSN journal
0021-8669
Volume
31
Issue
4
Year of publication
1994
Pages
922 - 928
Database
ISI
SICI code
0021-8669(1994)31:4<922:FTSBOA>2.0.ZU;2-2
Abstract
The effect of forebody tangential slot blowing on the flowfield about an F/A-18 aircraft is investigated numerically using solutions of the Navier-Stokes equations. Computed solutions are obtained for an aircra ft geometry, which includes the fuselage, a wing with deflected leadin g-edge flap, empennage, and a faired-over engine inlet. The computatio nal slot geometry corresponds to that used in full-scale wind-tunnel t ests. Solutions are computed using flight test conditions and jet mass flow ratios equivalent to wind-tunnel test conditions. The effect of slot location is analyzed by computing two nontime-accurate solutions with a 16-in. slot located 3 in. and 11 in. aft of the nose of the air craft. These computations resolve the trends observed in the full-scal e wind-tunnel test data. The flow aft of the leading-edge extension vo rtex burst is unsteady. A time-accurate solution is obtained to invest igate the flow characteristics aft of the vortex burst, including the effect of blowing on tail buffet.