An experimental study has been undertaken to examine the influence of
the blowing nozzle exit geometry on the effectiveness of the aft blowi
ng technique for forebody vortex control. The experiments were conduct
ed with a 3.0-caliber tangent ogive model at subsonic velocities and a
Reynolds number of 8.4 X 10(4) based on the model diameter. Asymmetri
c aft blowing was accomplished using both a single nozzle and a double
nozzle configuration. Detailed surface pressure measurements on the m
odel were obtained and local side forces determined. The experimental
results show that both the height and the width of the blowing nozzle
exit geometry are important parameters that determine the effectivenes
s of aft blowing; a broad, low-positioned blowing nozzle exit geometry
is found to be most effective for the forebody vortex control techniq
ue using aft blowing.