
Accession Number : AD0807297
Title : METHODS OF CALCULATING AERODYNAMIC LOADS ON AIRCRAFT STRUCTURES: PART I  WINGBODY INTERFERENCE EFFECTS.
Descriptive Note : Final rept. Oct 64Jan 66,
Corporate Author : MASSACHUSETTS INST OF TECH CAMBRIDGE
Personal Author(s) : Borland, Christopher J.
Report Date : AUG 1966
Pagination or Media Count : 195
Abstract : Methods are proposed for calculating the distribution of aerodynamic loads due to mutual interference effects between wings and bodies. The methods fall into two ranges of applicability: linear, and nonlinear, with angle of attack. Applicability of the linear loads methods to aeroelastic calculations is discussed. A computer program is presented which may be used to calculate interference loads at subsonic Mach numbers on a configuration consisting of (1) a body of any varying elliptic cross section and camber distribution, and (2) a wing with straight leading and trailing edges of any sweep angle, twist distribution, and camber distribution, located above or below the body centerline. Extension to the supersonic case is indicated. Generally good agreement with experimental data is found. Nonlinear wingbody interference loads are also considered. Several possible methods of representing the separated flow about a wingbody combination are proposed, and analyzed by the slender body theory. Numerical procedures are outlined, and some comparisons with experimental data are made.
Descriptors : (*WING BODY CONFIGURATIONS, INTERACTIONS), AEROELASTICITY, AERODYNAMIC LOADING, INTERFERENCE, AERODYNAMIC CHARACTERISTICS, LIFT, VORTICES, WAKE, FLOW SEPARATION, DOWNWASH, PRESSURE, LOAD DISTRIBUTION, SLENDER BODIES, SWEPT WINGS, ANGLE OF ATTACK, SHEETS, MATHEMATICAL MODELS, NUMERICAL METHODS AND PROCEDURES, COMPUTER PROGRAMMING, SUBROUTINES, SUPERSONIC CHARACTERISTICS.
Subject Categories : Aircraft
Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE