A Study of Flows Over Highly-Swept Wings Designed for Manoeuvre at Supersonic Speeds
Abstract
A wind-tunnel investigation into supersonic free-stream flows over two wing-body configurations, having wings of different design, suitable for combat aircraft, is described. Both wings have the same quasi-delta planform of 60 deg inboard leading-edge sweep and the same 4% thickness distribution but have differing camber distributions. Following a description of the design of the wings, the test procedures are discussed and the general features of the flows at conditions close to those for sustained manoeuvre are identified and contrasted. Comparisons between calculations by CFD methods and measurement are presented, and it is shown that a multiblock method for solving the Euler equations is suitable for designing wings for efficient manoeuvre at supersonic speeds. (edc)
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1988
- Accession Number
- ADA216837
Entities
People
- J. L. Fulker
- M. J. Simmons
- P. R. Ashill
Organizations
- Royal Aircraft Establishment