Flow Fluctuation Measurements at Mach Number 4 in the Test Section of the 12-Inch Supersonic Tunnel (D)
Abstract
Hot-wire anemometry measurements were made in the 12-in. supersonic tunnel of the von Karman gas dynamics facility to determine the level of flow fluctuations in the free stream. Supplementary acoustic measurements were made using a microphone mounted flush with the top surface of a flat plate. Data were obtained at Mach number 4. Reynolds number, based on the wire diameter (d = 0.0001 in.), ranged from 5.0 to 24.0. The hot-wire anemometry results presented are based on the mode concept of Kovasznay and the techniques of Morkovin for hot-wire data reduction. The free-stream results, which are similar to those published by Dr. John Laufer, can be explained by the assumption of a sound source traveling in the tunnel wall boundary layer at a supersonic velocity relative to the free stream.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1971
- Accession Number
- AD0728630
Entities
People
- J. C. Donaldson
- J. P. Wallace
Organizations
- Arnold Engineering Development Complex