Forward Swept Wing Study - Phase 1B Low-Speed Wind Tunnel Testing.
Abstract
Wind tunnel tests of the 0.09-scale D634-20G FSW fighter model were conducted to obtain low speed longitudinal and lateral-directional stability and control characteristics to substantiate the aerodynamic design features of the configuration. The tests were performed at Mach number 0.23 through angles of attack up to 40 deg in the NAAL tunnel. The effectiveness of the lifting surface design twists and cambers were investigated. The all-moveable canard and wing trailing edge control surface effectiveness were evaluated. Lateral-directional tests included build-ups to evaluate the centerline vertical tail. Wing pressures were measured on the upper and lower surfaces and canard pressures on the upper surface at selected stations. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1981
- Accession Number
- ADC027727
Entities
People
- D. Sokolsky
- R. Nishida