A Study of Slender, Thin Conically Cambered Wings with Flow Separation. Revision.
Abstract
Efficient wing design for high speed flight, good transonic manoeuverability and satisfactory near-to-ground performance requires detailed understanding of flow around leading edges with and without separations. Slender body theory with exact boundary condition has been used to calculate flow past thin conically camberged wings. The flow separations have been modelled as vortex-cut arrangements. Leading edge camber has a very marked effect on wing pressures, hence on the overall aerodynamic force. The lift drag ratio can be enhanced by leading edge droop. An interesting feature is the indication of multiple-valued solution for realistic cambers, and points to existence of more than one pair of vortex separation systems. The method may be extended to include thickness effects, secondary vortices, vortex sheet seperations, planform effects, leading edge devices or extensions. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1980
- Accession Number
- ADA139199
Entities
People
- R. K. Nangia
Organizations
- University of Bristol