Wind-tunnel investigation of the effects of steady rolling on the aerodynamic loading characteristics of a 45 degree sweptback wing at high subsonic speeds

An investigation has been conducted in the Langley high- speed 7- by 10-foot tunnel to determine the effect of steady rolling on the aerodynamic loading characteristics of a 45° sweptback wing of aspect ratio 4 in combination with a fuselage. The investigation covered Mach numbers of 0.70, 0.85, and 0.91 at angles of attack up to 13°.

The r esults indicate that the loss in damping in roll previously noted for this wing is due to stalling of the tip sections. The effects of rolling velocity on the span load distrib~tion can be satisfactorily estimated if measured pressure-distribution data in pitch are available.