STRESS AND THERMAL ANALYSIS OF THE THROAT SECTIONS 50-INCH MACH 10-12 TUNNEL
Abstract
The design analysis of the throat section for a large (50-inch-diameter test section), continuous flow, axisymmetric wind tunnel is described. The maximum stagnation conditions are 2000 psia and 1450 F. The as-built article, which in essence is simply a water-cooled liner house in a pressure shell, is described, and a method, which allows reasonable selections of geometry and cooling requirements, outlined. This method is extended to enable forecast of temperature distribution and result at stress along the throat section and is applied, not only to the Mach 10 configuration, but also to a proposed interchangeable counterpart which would permit aerodynamic testing at Mach 12. Maximum stagnation conditions therein would be 2400 psia and 1940 F.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1963
- Accession Number
- AD0296158
Entities
People
- J. P. Cook
- R. Sherman
Organizations
- Arnold Engineering Development Complex