Analysis of a pneumatic forebody flow control concept about a full aircraft geometryA full aircraft geometry is used to computationally analyze the effectiveness of a pneumatic forebody flow control concept. An overset grid technique is employed to model the aircraft and slot geometry. Steady-state solutions for both isolated forebody and full aircraft configurations are carried out using a thin-layer Navier-Stokes flow solver. A solution obtained using the full aircraft geometry and a flight sideslip condition investigates the effect of sideslip on the leading edge extention vortex burst point. A no-sideslip blowing solution using the isolated forebody at full-scale wind tunnel test conditions is compared with experimental data to determine the accuracy of the numerical method. A solution employing the full geometry and slot blowing at flight conditions is obtained.
Document ID
19920062906
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gee, Ken (MCAT Institute Moffett Field, CA, United States)
Rizk, Yehia M. (NASA Ames Research Center Moffett Field, CA, United States)
Murman, Scott M. (MCAT Institute Moffett Field, CA, United States)
Lanser, Wendy R. (NASA Ames Research Center Moffett Field, CA, United States)
Meyn, Larry A. (NASA Ames Research Center Moffett Field, CA, United States)
Schiff, Lewis B. (NASA Ames Research Center Moffett Field, CA, United States)