An apparatus for alleviating high angle of attack side force on slender pointed cylindrical forebodies such as fighter aircraft, missiles and the like is described. A symmetrical pair of helical separation trips was employed to disrupt the leeside vortices normally attained. The symmetrical pair of trips starts at either a common point or at space points on the upper surface of the forebody and extends along separate helical paths along the circumference of the forebody.
Aerodynamic Side-Force Alleviator Means
1979
7 pages
Report
No indication
English
Aerodynamics , Aircraft , Missile Technology , Government Inventions for Licensing , Patents , Aerodynamic stalling , Angle of attack , Boundary layer control , Control surfaces , Cross flow , Cylindrical bodies , Forebodies , Aerodynamic characteristics , Boundary layer separation , Leading edges , Sweep angle , PAT-CL-244-130 , PAT-CL-102-56R , PAT-CL-102-92.1 , PAT-CL-244-119
Aerodynamic side-force alleviator means
NTRS | 1980
|Aerodynamic Side-Force Alleviator Means
NTIS | 1979
|NTRS | 1969
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