Forward Swept Wing Study - Phase IB High-Speed Wind Tunnel Testing. Volume I.
Abstract
Wind tunnel tests were conducted to investigate drag and longitudinal stability characteristics of the 0.09-scale D634-20G Forward Swept Wing II fighter configuration with drooped leading edge, wing incidence, canard incidence, and drooped aileron in order to improve trimmed drag due to lift. In addition, configuration modifications were performed 'on-site'. Additionally, wing trailing edge control effectiveness tests were performed. The tests were conducted at Mach numbers from 0.6M to 1.2M at Reynolds numbers from 2.4 million per foot (1.2M) to 3.8 million per foot (0.6M).
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1981
- Accession Number
- ADC027944
Entities
People
- G. Panageas
- O. Sokolsky
- R. Nishida