Accession Number:

AD0905070

Title:

The Aerodynamic Design and Test of an Attack Type Configuration at Supercritical Flow Conditions.

Descriptive Note:

Final technical rept. 20 May 71-19 May 72,

Corporate Author:

GENERAL DYNAMICS SAN DIEGO CALIF CONVAIR AEROSPACE DIV

Report Date:

1972-09-01

Pagination or Media Count:

105.0

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.

Subject Categories:

  • Aerodynamics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE