AIAA Paper 1992-0020. Presented at the 30th AIAA Aerospace Sciences Meeting & Exhibit, January 6, 1992, pages 1-11. This article is in the public domain. Published by American Institute of Aeronautics and Astronautics.
This paper presents a computational investigation of a tangential slot blowing concept for generating lateral control forces on an aircraft fuselage forebody. The effects of varying both the jet width and jet exit velocity for a fixed location slot are analyzed. This work is aimed at aiding researchers designing future experimental and computational models of tangential slot blowing. The primary influence on the resulting side force of the forebody is seen to be the jet mass flow rate. This influence is insensitive to different combination of slot widths and jet velocities over the range of variables considered. Both an actuator plane and an overset grid technique are used to model the tangential slot. Tile overset method successfully resolves the details of the actual slot geometry, extending the generality of the numerical method. The actuator concept predicts side forces similar to those produced by resolving the actual slot geometry.