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

Item

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