Accession Number:

ADA148355

Title:

Joined Wing Transonic Design and Test Validation

Descriptive Note:

Final rept. 30 Sep 1982-31 May 1984

Corporate Author:

ROCKWELL INTERNATIONAL LOS ANGELES CA NORTH AMERICAN AIRCRAFT OPERATIONS

Report Date:

1984-06-22

Pagination or Media Count:

157.0

Abstract:

A tactical supercritical flow research model was designed to achieve high aerodynamic efficiency at Mach number 0.90 and lift coefficient 0.50 using numerical transonic design procedures. A wind tunnel model was built and tested in the Rockwell International Trisonic Wind Tunnel at Mach numbers of 0.40, 0. 85, 0.90, 0.95. Lift-drag ratio at the design condition compared favorably with theoretical upper bound levels for the test arrangement and conditions. Six component force measurements for the joined wing are well behaved and near linear over an angle-of-attack range of -4 alpha 10 degrees. Stable stall is naturally achieved for the arrangement. Weak changes in longitudinal and lateral-directional stability and control with pitch angle exist. Originator- supplied keywords include Transonic test, Forward sweep, Aft sweep, and Biplane.

Subject Categories:

  • Numerical Mathematics
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE