Calibration of the Tailored Interface 8 Inches x 10 Inches Shock Tunnel
Abstract
The work presents the design considerations and the calibration of a shock tunnel for aerodynamic measurements at hypersonic Mach numbers. The shock tunnel is composed of a shock tube which is used for the production of high temperature and high pressure air reservoir, which is then expanded through a supersonic nozzle, thereby attaining high Mach number flow in the test section. In order to obtain maximum test time a 'tailored' mode of operation is used for this shock tunnel. A method for calculating the optimum ratio of the compression Chamber length to the low pressure tube length for a given total shock tube length that will result in a maximum test duration is presented. The flow in the test section is calibrated using a total pressure rake and by static pressure measurements and measurements of stagnation point heat transfer rates at various points in the test section. The flow conditions are then calculated using the theoretical relations for stagnation point heat transfer rates. The experimental results show the flow in the horizontal plane with a relatively thin boundary layer.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1971
- Accession Number
- AD0728734
Entities
People
- A. Kuritzky
- J. Rom
Organizations
- Technion – Israel Institute of Technology