Accession Number:

ADP005022

Title:

Recent Developments in Rotary-Balance Testing of Fighter Aircraft Configurations at NASA Ames Research Center,

Descriptive Note:

Corporate Author:

NATIONAL AERONUATICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCH CENTER

Personal Author(s):

Report Date:

1985-11-01

Pagination or Media Count:

25.0

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 modelsting 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.

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE