Estimation of the Damping in Roll of Supersonic-Leading-Edge Wing-Body Combinations
Abstract
A description is given of a linear-theory method for the estimation of the damping in roll of super sonic-leading-edge wings mounted on cylindrical bodies. The error resxilting from an approximation essential to the method is shown to be small. The damping in roll is calculated for configurations having rectangular and triangular wings; for most of the range of variables the net effect of the body is to decrease the damping in roll. The body effect is small for body diameters less than about 3O percent of the wing span but increases rapidly with body size above this value.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1950
- Accession Number
- ADA380479
Entities
People
- Robert O. Piland
- Warren A. Tucker
Organizations
- National Aeronautics and Space Administration