Abstract
A technique has been developed to determine the lift and induced drag coefficients across the span of a finite wing utilizing a limited amount of experimental data. The method uses measurements from pairs of pressure ports at selected chordwise and spanwise locations and it is independent of the configuration. Constants required to calculate the lift and induced drag are obtained from two dimensional theoretical code. The technique was applied to a wall mounted wing with an aspect ratio of 5.6, which included taper, twist and aileron deflections. The data calculated using the method gave detailed information across the span of the wing for different configurations. Force balance data were also acquired for the same configurations and comparisons show a very good agreement for a wide range of conditions.
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