Charts for the Conical Part of the Downwash Field of Swept Wings at Supersonic Speeds
Abstract
Analytical expressions have been derived for the downwash throughout the entire induced flow field of lifting triangles of infinite chord with leading edges either in front of or behind the Mach cone. These expressions have been determined from the line-pressure source theory of R. T. Jones and the lifting-triangle investigation of H. J. Stewart. Eased on these analytical results, downwash charts have been prepared from which the downwash field may be determined for any practical combination of leading-edge sweep angle and flight Mach number. These charts for the lifting triangle of infinite chord are basic to the solution for the downwash field of any finite swept wing wherein the contributions of the tips and the trailing edges are to be determined by the method of lift cancellation as employed by Lagerstrom and others. The conical part of the downwash is obtained from the charts, and the nonconical part must be obtained by other means such as the lift-cancellation method.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1948
- Accession Number
- ADA380749
Entities
People
- Edward W. Perkins
- Jack N. Nielsen
Organizations
- National Aeronautics and Space Administration