DTIC ADA062318: Computerized Heat Transfer and Stress pdf

DTIC ADA062318: Computerized Heat Transfer and Stress

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Description of the Book:

This study presents a computerized approach to analyze the structural integrity of wind tunnel coverging-diverging nozzles or liners. In order to maintain liner configurations to produce accurate test conditions, the liners must be externally cooled, usually with water. Thermal gradients are set up in the liner and an analysis must be made to ensure adequate design. One of the most difficult problems in analyzing the liner is determining the airside, forced-convection, heat-transfer coefficient. The main reason it is so difficult is due to the boundary layer that develops along the contour of the liner. Sivells, ARO, Inc., derived, programmed, and experimentally checked a method for calculating the turbulent boundary-layer properties in the supersonic section of a liner. Using the results from Sivells’ program and an iterative radial heat balance, one can write a subroutine, called HEAT, to determine: (1) The thermal gradient through the thickness of the liner; (2) The temperature profile along the length of the liner; and (3) The total stresses at any point in the liner.

Included in the subroutine is a method for determining the same three conditions for the subsonic section of the liner

• Creator/s: Defense Technical Information Center
• Date: 11/1/1978
• Year: 1978
• Book Topics/Themes: DTIC Archive, Akers, Dennis T, ARO INC ARNOLD AFS TN, *COMPUTER PROGRAMS, *COMPUTERIZED SIMULATION, *HEAT TRANSFER, *SUPERSONIC WIND TUNNELS, *TURBULENT BOUNDARY LAYER, *WIND TUNNEL NOZZLES, LININGS, MATHEMATICAL MODELS, STRESS ANALYSIS, SUBSONIC FLOW, SUPERSONIC FLOW, THROATS(EQUIPMENT), WIND TUNNEL TESTS, WIND TUNNELS

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