Effect of Torsional Flexibility on the Rolling Characteristics at Supersonic Speeds of Tapered Upswept Wings.

摘要

An analysis is presented of the effect of torsional flexibility on the roiling characteristics at supersonic speeds of tapered unswept wings with partial-span constant-percent- chord ailerons extending inboard from the wing tip. The geometric variables considered are aspect ratio, taper ratio, aileron span, and aileron chord. The shape of the wing-torsional-stiffness curve is assumed and the twisting moment is considered to result solely from the pressure distribution caused by aileron deflection, so that the necessity of using a successive -approximation method is avoided. because of the complexity of the equations resulting from the analysis, numerical calculations from the equations are presented in a series of figures. A computational form is provided to be used in conjunction with these figures so that calculations can be made without reference to the analysis.