Accession Number : AD0804305
Title : METHODS OF CALCULATING AERODYNAMIC LOADS ON AIRCRAFT STRUCTURES: PART II - NONLINEAR EFFECTS.
Descriptive Note : Final rept. Oct 64-Apr 66,
Corporate Author : MASSACHUSETTS INST OF TECH CAMBRIDGE
Personal Author(s) : Chamberlain, Thomas E.
Report Date : AUG 1966
Pagination or Media Count : 53
Abstract : A method is presented for analysis of the nonlinear aerodynamics of slender configurations with vortex separation. Primary emphasis is on the nonlinear component of the aerodynamic characteristics. The theory is intended to be mathematically tenable yet give results of acceptable accuracy. A technique for analyzing the nonlinear aeroelastic problem is given followed by a method for obtaining the nonlinear aerodynamics of wings, bodies, and their combinations. Comparisons with experiment are provided. The experimental comparisons with the wing results indicate that the theory overestimates the nonlinear forces at high angles of attack. The results indicate directions for further research. (Author)
Descriptors : (*WING BODY CONFIGURATIONS, AERODYNAMIC LOADING), (*THIN WINGS, AERODYNAMIC LOADING), (*FUSELAGES, AERODYNAMIC LOADING), SLENDER BODIES, THEORY, AEROELASTICITY, NONLINEAR SYSTEMS, PRESSURE, LOAD DISTRIBUTION, FLOW FIELDS, VORTICES, PRESSURE, DELTA WINGS, MATHEMATICAL MODELS.
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE