Effects of simulated wing damage on the aerodynamic characteristics of a swept-wing airplane model

Abstract

An investigation has been conducted to determine the effects of simulated wing damage on the aerodynamic characteristics of a swept-wing airplane model.Wing damage was simulated by removal of either a leading-edge portion o r a trailing-edge portion of one wing panel or by removal of an entire wing panel.The investigation was conducted at Mach numbers from 1.70 to 2.86 at a constant Reynolds number of 2.25 X lo6 per foot (7.38 X 106 per meter).The results of the investigation indicated that removing the leading-o r trailingedge portion of the wing or removing the entire wing panel led to a decrease in both liftcurve slope and maximum lift-drag ratio.At the lower Mach numbers, removal of the trailing edge caused a rolling moment slightly larger than that caused by removal of the leading edge.At the higher Mach numbers, however, the effect on rolling moment due to removal of the trailing edge was l e s s than that caused by removal of the leading edge even though a larger a r e a of the wing was removed.Except when the entire wing panel was removed, the roll induced by wing asymmetry could be offset by sideslip within reasonable limits of angle of attack and sideslip.