ESDU AERO A.S.06.03.01
Stability derivative Lp rolling moment due to rolling for wings at supersonic speeds.
Abstract:ESDU Aero A.S.06.03.01 presents graphs plotting the rolling moment derivative at zero lift for rigid uncambered wings with streamwise tips as a function of aspect ratio, mid-chord sweep angle and the compressibility factor. Five graphs are given for taper ratios of 0, 0.25, 0.5, 0.75 and 1. The curves are based on linearised supersonic flow theory but where experimental results show that the theory becomes unreliable, for wings of low aspect ratio, a linear interpolation is made to the limiting values provided by slender wing theory. The effect of angle of attack is believed to be small for low lift coefficients. Due to flexibility, measured values will, in general, be less than those predicted by the method. Even for rigid wings, experimental results suggest that for wings of sharp-nosed leading-edge section measured values lie between 90 and 100 per cent of those predicted by theory while for round-nosed sections measured values lie between 70 and 90 per cent of theoretical, except for rectangular wings when measured values lie between 80 and 100 per cent of the theoretical. It is noted that for rectangular wings of both section types experimental data were inferred from triform (three-wing) lay-outs. The effect of body interference may be treated using ESDU Aero A.S.06.03.02 and, for missile applications, interference between half wings used in triform or cruciform (four-wing) arrangements may be treated using ESDU Aero A.S.06.03.03.
- Cruciform Fins/wings
- Delta Wings
- Rectangular Wings
- Rolling Moment Due To Rolling (Lp or Clp)
- Wing-Body Combination
|Data Item ESDU AERO A.S.06.03.01|