Pressure Distribution and Damping in Steady Pitch at Supersonic Mach Numbers of Flat Swept-Back Wings Having All Edges Subsonic
Abstract
A method is presented for calculating the pressure distribution and damping in steady pitch at supersonic Mach numbers of thin, flat, swept-back wings having all edges straight and subsonic. Although it is adaptable to wings with negative rake at the tips, the method: is applied only to wings with streamwise tips. The method consists of two steps: first, the calculation of a basic pressure distribution, which is identical to that existing on an infinite triangular plan form having leading edges that coincide with those of the swept-back wing; and second, the correction of this basic distribution to account for the effects of the subsonic trailing edges and tips. In calculating the various corrections, use is made of the principle of the superposition of conical flows. The derivative for the damping in pitch is calculated in a similar manner. In applying the method of analysis to a typical configuration, it was found that several of the corrections were small, and, from a practical standpoint, could be dropped By dropping these terms the method is shortened to the extent that it closely parallels previously published methods for calculating the lift, pitching moment, and damping in roll of swept-back wings with subsonic edges. A substantial reduction of the pressure in the vicinity of a subsonic tip was disclosed in the analysis. This effect was also found earlier for the cases of steady lift and steady roll. The method is based upon the usual assumptions and limitations of the linearized potential theory for supersonic flow.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1950
- Accession Number
- ADA380517
Entities
People
- Harold J. Walker
- Mary B. Ballantyne
Organizations
- National Aeronautics and Space Administration