Development of a dual strain gage balance system for measuring light loads

Author

Roberts, Paul W.

Author_Institution

NASA Langley Res. Center, Hampton, VA, USA

fYear

1989

fDate

18-21 Sep 1989

Firstpage

422

Lastpage

433

Abstract

A strain gage balance force measurement system is described which was designed to meet light load requirements for an airfoil model tested in NASA Langley´s low-turbulence pressure tunnel (LTPT). This system was developed to obtain direct force data needed to verify calculated pressure to force correlations used in previous aerodynamic tests. The three-component force measurement system was designed so that the strain gage balances would simultaneously support and measure the following loads: weight of the airfoil (approximately 3.0 lb_f); 8.0 lb _f of lift; 0.5 lb_f of drag; and 16.0 in. lb_f of pitching moment. In addition to these design loads, the system was required to withstand 100% overload on all three components. The system comprises an airfoil, two strain gaged balances, a thermal flexure, and a mounting plate. Installation of the system in the LTPT is also discussed

Keywords

balances; calibration; force measurement; strain gauges; wind tunnels; NASA; aerodynamic tests; aerospace test facilities; airfoil model; calibration; dual strain gage balance; force data; force measurement; low-turbulence pressure tunnel; mounting plate; thermal flexure; wind tunnel; Aerodynamics; Automotive components; Bars; Capacitive sensors; Drag; Force measurement; NASA; Strain measurement; System testing; Thermal expansion;

fLanguage

English

Publisher

ieee

Conference_Titel

Instrumentation in Aerospace Simulation Facilities, 1989. ICIASF '89 Record., International Congress on

Conference_Location

Gottingen

Type

conf

DOI

10.1109/ICIASF.1989.77697

Filename

77697