Joined Wing Transonic Design and Test Validation
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 22, 1984
- Accession Number
- ADA148355
Entities
People
- E. Bonner
- J. A. Clyde
- L. Spacht
- T. P. Goebel