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Improve performance of various control 

 surfaces with devices such as snags and 

 strakes which alleviate stall. Apply to 

 leading edge vortex. 



PROPOSAL— to demonstrate that liquid in- 

 jection from propeller leading edge will 

 reduce induced drag, alleviate tip vor- 

 tex, and attenuate noise spectrum. 



Determines scaling parameters for flow in- 

 core region of vortex. Peak tangential 

 velocities generated by OGEE tip substan- 

 tially less than parent tip. 



Simplifies Betz rollup equations and ex- 

 tends them to make estimate of vortex 

 structure behind wings with arbitrary 

 spanwise load distributions. 



It is found that substantial reductions in 

 rolling moment are predicted for certain 

 range of generating and following wing 

 span ratios. 



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Various ways In which vortical regions 

 interact are developed by numerical analy- 

 sis of Inviscid time-dependent convective 

 motions of the vorticity. 



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Vortex core diameter, tangential and 

 axial core velocities via triaxle hot 

 wire. Spanwise lift distribution via 

 pressure taps on wing surfaces. 







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