The present investigation was conducted to measure the effects of spanwise blowing on the surface pressures of a 44 swept trapezoidal wing. Wind-tunnel data were obtained at a free-stream Mach number of 0.26 for a range of model angle of attack, jet thrust coefficient, and jet location. Results of this study showed that the sectional effects of spanwise blowing were strongly dependent on angle of attack, jet thrust coefficient, and span location;the largest effects occurred at the highest angles of attack and thrust coefficients and on the inboard portion of the wing. Full vortex lift was achieved at the inboard span station with a small blowing rate, but successively higher blowing rates were necessary to achieve full vortex lift at increased span distances. Spanwise blowing increased lift throughout the angle-of-attack range, delayed wing stall to higher angles of attack, and improved the induced-drag polars. The leading-edge suction analogy can be used to estimate the section and total lifts resulting from spanwise blowing.
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