Accession Number : AD0382516
Title : SUBSONIC FLUTTER INVESTIGATIONS OF AEROSPACE VEHICLES WITH LARGE FLEXIBLE LIFTING FUSELAGES.
Descriptive Note : Final rept. 1 Jul 65-31 Oct 66,
Corporate Author : NORTH AMERICAN AVIATION INC LOS ANGELES CA LOS ANGELES DIV
Personal Author(s) : Hodson, C. H.
Report Date : APR 1967
Pagination or Media Count : 239
Abstract : Analytical and experimental flutter and response studies were conducted for representative slender lifting body vehicles. The configurations studied were based on a blunt-nosed 80 degree delta planform. Three different vehicle cross-section shapes were investigated. Trends in flutter speed were also determined for variations in weight and stiffness distribution. The studies were confined to the subsonic speed range. A wind tunnel flutter model was tested. Experimental flutter speeds were obtained for eleven different model configurations. Experimental data were also obtained on response to sinusoidal, external excitation of the model during tunnel runs. Vibration, flutter, and response analyses of the model were conducted using oscillatory aerodynamic forces computed by slender body theory. Flutter analyses applicable to the free flight condition were also conducted for sixteen model configurations involving variations in vehicle cross-section shape, stiffness distribution and weight distribution.
Descriptors : (*AEROSPACE CRAFT, FLUTTER), DELTA WINGS, SUBSONIC CHARACTERISTICS, FUSELAGES, FLEXIBLE STRUCTURES, SLENDER BODIES, WIND TUNNEL MODELS, MODEL TESTS, VIBRATION, FORCE(MECHANICS).
Subject Categories : Aerodynamics
Spacecraft Trajectories and Reentry
Distribution Statement : APPROVED FOR PUBLIC RELEASE