Accession Number:

AD0296158

Title:

STRESS AND THERMAL ANALYSIS OF THE THROAT SECTIONS 50-INCH MACH 10-12 TUNNEL

Descriptive Note:

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

Report Date:

1963-02-01

Pagination or Media Count:

54.0

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.

Subject Categories:

  • Mechanics
  • Test Facilities, Equipment and Methods

Distribution Statement:

APPROVED FOR PUBLIC RELEASE