The Aerodynamic Design and Test of an Attack Type Configuration at Supercritical Flow Conditions.
Abstract
Tests in the NSRDC 7 x 10 Foot Transonic Wind Tunnel on an advanced attack configuration are described. The configuration was designed by the Prandtl-Glauert theory (area rule plus finite element method), to yield a near elliptic spanwise loading distribution as well as a uniform wing upper surface isobar distribution at the design condition free stream Mach number equals 0.9 and the lift coefficient equals 0.6. Despite the well-known inadequacies of the linear theory, the tested configuration exhibited reasonably good drag divergence and buffet onset performance, though an inboard unloading and the appearance of a significant lower surface shock at the design condition were undesirable surprises. Configuration changes to eliminate the latter undesirable flow features are then suggested.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1972
- Accession Number
- AD0905070
Entities
People
- Arnold Anderson
- George Pick
- Hideo Yoshihara
- Joseph Fatta
Organizations
- General Dynamics