Rolling Moment Due to Yaw of Flat Wings of Trapezoidal Planform at Supersonic Speeds

Citation

Lampert, Seymour (1948) Rolling Moment Due to Yaw of Flat Wings of Trapezoidal Planform at Supersonic Speeds. Engineer's thesis, California Institute of Technology. doi:10.7907/HDT1-PR91. https://resolver.caltech.edu/CaltechETD:etd-12162008-140210

Abstract

NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in .pdf document. The purpose of this thesis is to determine the effect of yaw on the rolling moment characteristics of rectangular and trapezoidal planforms of zero thickness. The method used is that of applying the superposition of solutions of linearized conical flow to the problem of the yawed wing. The solutions particularly applicable are those where W = [...] is symmetrical with respect to the plane of the wing, i.e., (lifting case). For the wings considered in this report it was necessary to determine uniquely W = W(b,[...], t) in the following regions: 1) subsonic leading edge, 2) subsonic trailing edge, 3) infinitely swept wing, 4) supersonic leading edges. The rolling moment and lift coefficients were calculated and the effect of varying the angle of side edge and yew angle of the wing in respect to these parameters can be computed. The rolling moment coefficient for a rectangular wing of different aspect ratios was computed and it was found that the variation of rolling moment with angle of yaw [...] increases almost linearly to a maximum and then falls off. There is also an increase in [...] with increasing aspect ratio.

Thesis Files