On the Effect of Subsonic Trailing Edges on Damping in Roll and Pitch of Thin Sweptback Wings in a Supersonic Stream
Abstract
The principal effect of subsonic trailing edges on the damping in roll and pitch of thin sweptback wings in a supersonic stream is evaluated with the aid of some conical and quasi-conical flows previously derived. This effect is expressed in the form of approximate correction terms to be added to the corresponding expressions that are obtained when the trailing-edge disturbance is ignored. The results are limited to those plan forms and Mach numbers for which the trailing-edge disturbance does not extend beyond the leading edge and for which the area of mutual interference between tips and trailing edge is not large. Practical applicability is subject to the limitations of linearized potential theory.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1950
- Accession Number
- ADA380685
Entities
People
- Herbert S. Ribner
Organizations
- National Aeronautics and Space Administration