Accession Number : ADC027944
Title : Forward Swept Wing Study - Phase IB High-Speed Wind Tunnel Testing. Volume I.
Descriptive Note : Final rept. May 78-Jun 80,
Corporate Author : ROCKWELL INTERNATIONAL EL SEGUNDO CA NORTH AMERICAN AIRCRAFT DIV
Personal Author(s) : Panageas, G. ; Nishida, R. ; Sokolsky, O.
Report Date : MAR 1981
Pagination or Media Count : 145
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).
Descriptors : *SWEPTFORWARD WINGS, AERODYNAMIC CONTROL SURFACES, TRANSONIC CHARACTERISTICS, WIND TUNNEL TESTS, PITCH(MOTION), LIFT, AERODYNAMIC DRAG, TRIM(AERODYNAMICS), ANGLE OF INCIDENCE, LIFT TO DRAG RATIO, OPTIMIZATION, CAMBER, AILERONS, TRAILING EDGES, FENCES, CANARD CONFIGURATIONS, JET FIGHTERS, WIND TUNNEL MODELS, REYNOLDS NUMBER.
Subject Categories : Aerodynamics
Attack and Fighter Aircraft
Distribution Statement : APPROVED FOR PUBLIC RELEASE