Admittance Techniques In high Speed Flutter Model Testing. Part I. Experimental Results

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Report Number: WADD TR 61-31 Part I
Author(s): Asher, Gifford W., Watanabe, Roy K.
Corporate Author(s): Boeing Company
Laboratory: Flight Dynamics Laboratory
Date of Publication: 1961-07
Pages: 53
Contract: AF 33(616)-6836
DoD Project: 1370
DoD Task: 13478
Identifier: AD0267352

This report presents a new method of high speed flutter model testing is. The method obtains free flight flutter information from restrained models in the wind tunnel through the use of mechanical admittance measurements. Flutter test data for a representative high speed wing-body configuration are presented at a Mach number of 1.5. Brief descriptions of the application of admittance techniques in the determination of aerodynamic data, in the determination of control surface transfer functions, and in the determination of atmospheric gust loads through elastic model tests are presented together with recommendations for future research in this area.

Provenance: Lockheed Martin Missiles & Fire Control

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