Effect of Aspect Ratio on Undamped Torsional Oscillations of a Thin Rectangular Wing in Supersonic Flow
Abstract
The theory for single-degree torsional instability of a two-dimensional wing oscillating in a supersonic stream is extended so as to apply to a finite rectangular wing oscillating in a supersonic stream. The velocity potential and aerodynamic-torsional-moment coefficient based on the linearized equations of motion for small disturbances are derived by means of appropriate distributions of moving sources and doublets. The aerodynamic-torsional-moment coefficient thus derived is combined with a mechanical-damping coefficient to study the effect of aspect ratio on the undamped torsional oscillations of a finite rectangular wing. Decreasing the aspect ratio of the wing is found to have a highly stabilizing effect on the undamped torsional oscillations. Results of some selected calculations are presented in several figures. It is pointed out that second-order thickness effects may be of significance.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1949
- Accession Number
- ADA380463
Entities
People
- Charles E. Watkins
Organizations
- National Aeronautics and Space Administration