Stress and Thermal Analysis of the Throat Sections 50-Inch Mach 10-12 Tunnel

Abstract

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Mechanical Design of the 50-Inch Mach 10-12 Tunnel

“…However, the most pronounced scaling occurred in the immediate throat area where the heat-transfer rate is highest and the throat liner wall thickness is at a minimum to provide maximum cooling effectiveness and minimum thermal gradient stresses which are additive to the pressure stresses (see Ref. 3). …”

Aerodynamic Design and Calibration of the VKF 50-Inch Hypersonic Wind Tunnels

“…The final values obtained by a heat balance in Ref. 4 were 1059°R for Mach 10 and 1114°R for Mach 12 for maximum operating conditions. Fortunately, the choice of the wall temperature does not seriously influence the boundary-layer calculations.…”