SHOCK-TUBE MEASUREMENTS OF STEP-BLAST LOADS ON A NASA 64A010 AIRFOIL
Abstract
Measurements of the transient loads on a twodimensional airfoil set at various fixed angles of attack and subjected to a step-blast wave in 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 egrees. 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 i detail. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1962
- Accession Number
- AD0275496
Entities
People
- J. Ray Ruetenik
- Walter Herrmann
Organizations
- Massachusetts Institute of Technology