1979•Unpublished venueRequires access

Development of the cryogenic tunnel concept and application to the US National Transonic Facility

R. A. Kilgore

Abstract

A fan-driven, high Reynolds number, transonic cryogenic wind tunnel is described. The tunnel has a 2.5- by 2.5 m test section and is capable of operating from ambient to cryogenic temperatures at stagnation pressures up to 8.8 atm. An overview of the cryogenic concept and discussions of drive power requirements, support systems, and operating characteristics and performance of the wind tunnel are included.

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Available abstract

Key concepts: Transonic, Wind tunnel, Subsonic and transonic wind tunnel, Supersonic wind tunnel, Hypersonic wind tunnel, Cryogenics, Aerospace engineering, Engineering