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A wind-tunnel investigation has been made of two unswept, partial-span, flap-type controls (differing only in hinge-line location) mounted on a 60 degree delta wing. One control was unbalanced and the other has a 100-percent overhang balance. Control hinge moments as well as aerodynamic characteristics of the complete wing-body combination were obtained for control deflections from 0 to 40 degrees over an angle-of-attack range of plus or minus 12 degrees at Mach numbers from 0.75 to 1.96. Reynolds numbers varied between 2,200,000 and 2,200,000. Expressions derived from linear theory for the hinge-moment coefficient due to angle of attack for unswept partial-span controls (which extend neither to the wing tip nor to the wing center line) on triangular wings having subsonic leading edges are given in an appendix.
An investigation of a semi-span wing-fuselage model having an 80 degree swept pointed wing with either an unbalanced constant-chord control or an overhang-balanced swept hinge-line control was conducted in the Langley 9- by 12-inch blowdown tunnel. Control hinge moments and effectiveness characteristics were obtained over an angle-of-attack range of plus or minus 16 degrees at control deflections up to 25 degrees. Data were obtained at Mach numbers from 0.75 to 1.96.
Elevon hinge moments were determined from measured surface pressures on a typical delta-wing shuttle orbiter model at selective deflection angles for comparison with the extensive experimental and analytical hinge-moment data previously reported for a simple 75 [degrees] delta wing with a trailing-edge control. The angles of attack were from 0 [degrees] to 55 [degrees] at elevondeflection angles of -45.5 [degrees], O [degrees], and 20°. The results show that the elevon hinge moments on the shuttle orbiter are essentially the same as those measured earlier for the more basic model. Also included is an appendix describing a cubic spline function technique used to determine the hinge moments from elevon surface-pressure measurements.