C.P. No. 1326 PROCUREMENT EXECUTIVE, MINISTRY OF DEFENCE
نویسنده
چکیده
SUMMARY Chordwise pressure distributions were measured at several spanwise stations on a two-dimensional model wing fitted with a plain-hinged, trailing-edge flap, at a Reynolds number of 1.9 x IO6 based on chord. The flap was divided into two parts and was deflected to a maximum of 5'. When the flaps were deflected differentially, the transition from a pressure distribution characteristic of the flaps-deflected configuration, to one characteristic of the flaps-up situation, took place within a spanwise distance of about 10% of the chord. This length was independent of the angle of incidence. Integrations for sectional normal force indicated, however, that modifications to the local circulation caused by a discontinuity in angle of flap deflection were apparent more than one chord distance away from the flap junction.
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