Accession Number : ADA299308

Title :   Estimation of Aerodynamic Load Distributions on the F/A-18 Aircraft Using a CFD Panel Code,

Corporate Author : DEFENCE SCIENCE AND TECHNOLOGY ORGANIZATION CANBERRA (AUSTRALIA)

Personal Author(s) : Quick, H. A.

PDF Url : ADA299308

Report Date : MAR 1995

Pagination or Media Count : 44

Abstract : The computational fluid dynamics panel method code VSAERO has been used to estimate the aerodynamic load distributions on the stabilators, fins and aft fuselage of the F/A-18 aircraft for steady sideslip and steady roll conditions. Three separate VSAERO models have been developed to obtain results for these conditions. These are a symmetric F/A-18 model, a starboard fin model and a starboard stabilator and fin model. Difficulties in modelling the vortices separating from the leading edges of the stabilators and fins at moderate angles of attack have restricted the range of conditions for which the method has been used. (AN)

Descriptors :   *COMPUTATIONAL FLUID DYNAMICS, *AERODYNAMIC LOADING, *JET FIGHTERS, MATHEMATICAL MODELS, FLIGHT TESTING, LOAD DISTRIBUTION, PITCH(MOTION), AERODYNAMIC STABILITY, VORTICES, ANGLE OF ATTACK, MATHEMATICAL PROGRAMMING, MATHEMATICAL PREDICTION, FUSELAGES, AERODYNAMIC FORCES, WIND TUNNEL TESTS, WAKE, HYDRODYNAMIC CODES, SIDESLIP, LEADING EDGES, FLIGHT ENVELOPE, FLIGHT MANEUVERS, AUSTRALIA, INVISCID FLOW, PRESSURE DISTRIBUTION, INCOMPRESSIBLE FLOW, FATIGUE TESTS(MECHANICS), AERIAL RUDDERS.

Subject Categories : Aerodynamics
      Fluid Mechanics
      Attack and Fighter Aircraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE