The Damping Due to Roll of Triangular, Trapezoidal, and Related Plan Forms in Supersonic Flow
Abstract
Within the limitations of linearized potential theory for supersonic flow, solutions have been obtained for the damping in roll of triangular, trapezoidal, rectangular, and two swept-back plan forms. The results indicate that as the aspect ratio is increased the limiting value of the damping in roll for trapezoidal (with a finite, fixed rake angle) and rectangular plan forms is equal to the value for two-dimensional flow which is twice the limiting value for triangular plan forms. For the swept-back plan forms having the Mach cone and leading edge coincident or very nearly coincident, the damping in roll even exceeded the value for two-dimensional flow. In addition, an investigation of the effect of reversal of the plan-form position relative to the stream direction was made for the majority of the plan forms considered and the results show that this reversal had no effect on the value of the damping-in-roll stability derivative.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1948
- Accession Number
- ADA380720
Entities
People
- Alberta Alksne
- Arthur L. Jones
Organizations
- National Aeronautics and Space Administration