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Title
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Admittance Techniques In high Speed Flutter Model Testing. Part I. Experimental Results
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Date
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1961
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Index Abstract
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Contrails and DTIC
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Photo Quality
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Incomplete
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Report Number
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WADD TR 61-31 Part I
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Creator
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Asher, Gifford W.
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Watanabe, Roy K.
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Corporate Author
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Boeing Company
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Laboratory
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Flight Dynamics Laboratory
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Extent
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53
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Identifier
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AD0267352
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AD0267352
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Access Rights
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OTS
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Distribution Classification
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1
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Contract
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AF 33(616)-6836
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DoD Project
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1370
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DoD Task
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13478
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DTIC Record Exists
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Yes
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Distribution Change Authority Correspondence
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None
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Report Availability
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Full text available by request
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Date Issued
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1961-07
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Abstract
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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.
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Subject
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Flutter Simulators
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Gust Loads
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Wing Body Configurations
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Admittance
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Aerodynamic Configurations
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Atmospheres
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Data Transmission Systems
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Elastic Properties
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Equations
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Experimental Data
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Flight Paths
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Flight Testing
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Mechanical Properties
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Motion
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Oscillators
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Supersonic Flow
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Tables (Data)
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Wind Tunnel Models
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Publisher
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Wright-Patterson Air Force Base, OH : Aeronautical Systems Division, Air Force Systems Command, United States Air Force
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Distribution Conflict
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No
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Type
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report
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Provenance
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Lockheed Martin Missiles & Fire Control
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Format
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53 pages ; 28 cm.