Shock-Tube Measurements of Step-Blast Loads on a NASA 64A010 Airfoil
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Report Number: ASD TR 61-219
Author(s): Ruetenik, J. Ray, Herrmann, Walter
Corporate Author(s): Massachusetts Institute of Technology
Laboratory: Flight Dynamics Laboratory
Date of Publication: 1962-02
Pages: 51
Contract: AF 33(616)-6195
DoD Project: 1350
DoD Task: 14045
Identifier: AD0275496
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
Author(s): Ruetenik, J. Ray, Herrmann, Walter
Corporate Author(s): Massachusetts Institute of Technology
Laboratory: Flight Dynamics Laboratory
Date of Publication: 1962-02
Pages: 51
Contract: AF 33(616)-6195
DoD Project: 1350
DoD Task: 14045
Identifier: AD0275496
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