THEORETICAL SUPERSONIC CHARACTERISTICS OF INBOARD TRAILING-EDGE FLAPS HAVING ARBITRARY SWEEP AND TAPER MACH LINES BEHIND FLAP LEADING AND TRAILING EDGES

摘要

Generalized expressions in closed form have been obtained by means )f linearized theory for the aerodynamic characteristics (lift-, rolling-moment-, pitching-moment-, and hinge-moment-coefficient derivatives) due. to deflection of inboard trailing-edge flaps. The analysis considers the effects of Mach number and flap aspect ratio, taper ratio, and sweep for the conditions where the Mach lines lie behind the flap leading and trailing edges. The flap configurations analyzed are limited to the case of streamwise tips where the foremost Mach lines from the flap tips do not intersect the root and tip chords of the wing. The expressions for the hinge-moment-coefficient derivative are limited to configurations where the flap-root-chord Mach line does not intersect the flap tip chord.