EXPERIMENTAL DETERMINATION OF SPANWISE LIFT EFFECTS ON A WING OF INFINITE ASPECT RATIO SPANNING A CIRCULAR JET

The propeller slipstream-wing interaction and its effects on spanwise lift distribution are discussed. Recent theoretical and experimental work is briefly reviewed. A more detailed discussion is given of experiments which make use of circular nonrotating jets for slipstream simulation. Features of the present experimental program are presented with lift distributions showing marked correlation with the theory of Rethorst for a plane wing of infinite span. Additional results are presented for this wing with a .20c split flap at deflection angles of 20 and 40 deg. It is concluded that Rethorst's theory represents the most satisfactory approach to date for analyzing the spanwise effects of the interaction. (Author)