Accession Number : ADP005022
Title : Recent Developments in Rotary-Balance Testing of Fighter Aircraft Configurations at NASA Ames Research Center,
Corporate Author : NATIONAL AERONUATICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCH CENTER
Personal Author(s) : Malcolm,Gerald N. ; Schiff,Lewis B.
Report Date : NOV 1985
Pagination or Media Count : 25
Abstract : NASA-ARC has an ongoing research program to investigate high-angle-of-attack aerodynamic phenomena associated with high-performance aircraft. As part of this research, two rotary-balance apparatuses have recently been developed for testing airplane models in a coning motion. A new large-scale apparatus, developed for use in the 12-Foot Pressure Wind Tunnel primarily to permit testing at high Reynolds numbers, was recently used to investigate the aerodynamics of a 0.05-scale model of the F-15 fighter aircraft. Effects of Reynolds number, spin-rate parameter, model attitude, presence of a nose boom, and model/sting mounting angle were investigated. A smaller apparatus has been used in the 6- by 6-foot supersonic wind tunnel to investigate the aerodynamic behavior of a simple representation of a modern fighter, the Standard Dynamics Model (SDM). Effects of spin-rate parameter and model attitude were investigated. This paper presents a description of the two rigs and a discussion of some of the results obtained in the respective tests.
Descriptors : *SPINNING(MOTION), RATES, JET FIGHTERS, HIGH ANGLES, WIND TUNNEL TESTS, WIND TUNNEL MODELS, REYNOLDS NUMBER, ATTITUDE(INCLINATION), ANGLE OF ATTACK, TEST EQUIPMENT, ROTATION, BALANCES, SUPERSONIC WIND TUNNELS
Distribution Statement : APPROVED FOR PUBLIC RELEASE