Shock-Tube Measurements of Step-Blast Loads on a NASA 64A010 Airfoil

Item

Title
Shock-Tube Measurements of Step-Blast Loads on a NASA 64A010 Airfoil
Description
Measurements of the transient loads on a two-dimensional airfoil set at various fixed angles of attack and subjected to a step-blast wave in the MIT-ASD shock tube are reported. The free-stream Mach number range employed was 0.4 to 1.0 and the angles of attack ranged from 15 to 60 degrees. Measurements were made using both an interferometer and pressure transducers flush-mounted in the airfoil. During the diffraction period, good agreement was obtained with linearized theory, even up to an angle of attack of 60 degrees. In the post-diffraction period the departures from linearized theory became very large after the leading-edge vortex approached the trailing edge. The transient stalling behavior is examined in detail.
Date
1962
Index Abstract
Contrails and DTIC
Photo Quality
Incomplete
Report Number
ASD TR 61-219
Creator
Ruetenik, J. Ray
Herrmann, Walter
Corporate Author
Massachusetts Institute of Technology
Laboratory
Flight Dynamics Laboratory
Extent
51
Identifier
AD0275496
AD0275496
Access Rights
OTS
Distribution Classification
1
Contract
AF 33(616)-6195
DoD Project
1350
DoD Task
14045
DTIC Record Exists
Yes
Distribution Change Authority Correspondence
None
Report Availability
Full text available by request
Date Issued
1962-02
Abstract
Measurements of the transient loads on a two-dimensional airfoil set at various fixed angles of attack and subjected to a step-blast wave in the MIT-ASD shock tube are reported. The free-stream Mach number range employed was 0.4 to 1.0 and the angles of attack ranged from 15 to 60 degrees. Measurements were made using both an interferometer and pressure transducers flush-mounted in the airfoil. During the diffraction period, good agreement was obtained with linearized theory, even up to an angle of attack of 60 degrees. In the post-diffraction period the departures from linearized theory became very large after the leading-edge vortex approached the trailing edge. The transient stalling behavior is examined in detail.
Provenance
AFRL/VACA
Type
report
Format
vii, 51 pages : ill. ; 28 cm.
Subject
Airfoils
Shock Waves
Aerodynamic Configurations
Blast
Boundary Layer
Compressible Flow
Load Distribution
Measurement
Model Tests
Pressure
Shock Tubes
Subsonic Flow
Transonic Characteristics
Vortices
Publisher
Wright-Patterson Air Force Base, OH : Flight Dynamics Laboratory, Aeronautical Systems Division, Air Force Systems Command,
Distribution Conflict
No

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