Accession Number : ADC027727
Title : Forward Swept Wing Study - Phase 1B Low-Speed Wind Tunnel Testing.
Descriptive Note : Final rept. May 78-Apr 79,
Corporate Author : ROCKWELL INTERNATIONAL EL SEGUNDO CA NORTH AMERICAN AIRCRAFT DIV
Personal Author(s) : Nishida, R. ; Sokolsky, D.
Report Date : MAR 1981
Pagination or Media Count : 226
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)
Descriptors : *SWEPTFORWARD WINGS, *AERODYNAMIC STABILITY, AERODYNAMIC CONTROL SURFACES, LIFTING SURFACES, CAMBER, CANARD CONFIGURATIONS, TWIST(AERODYNAMICS), TRAILING EDGES, TAILS(AIRCRAFT), AERODYNAMIC LOADING, RUDDERS, AILERONS, ELEVATORS, SUBSONIC WIND TUNNELS, WIND TUNNEL MODELS, ANGLE OF ATTACK, SCALE MODELS, JET FIGHTERS, WIND TUNNEL TESTS.
Subject Categories : Aerodynamics
Attack and Fighter Aircraft
Distribution Statement : APPROVED FOR PUBLIC RELEASE