The variation of the rolling moment with sideslip and the variation of the derivative with aspect ratio and Mach number were investigated.

The variation of the yawing moment with sideslip and the variation of the stability derivative with aspect ratio and Mach number were investigated.

A method is presented for determining the rolling and yawing moments of swept-back wings in steady sideslip at supersonic speeds. The case treated in particular

Beskriver principperne i f.m. konstruktionen af styrede missiler.