Hostname: page-component-586b7cd67f-2brh9 Total loading time: 0 Render date: 2024-11-24T22:35:40.036Z Has data issue: false hasContentIssue false
  • English
  • Français

A surface flow visualisation technique for use in cryogenic wind tunnels

Published online by Cambridge University Press:  04 July 2016

D. M. Kell
D. M. Kell*
Affiliation:
Production Engineering Department, British Aerospace, Weybridge
Get access Rights & Permissions [Opens in a new window]

Extract

In recent years the need for high Reynolds number wind tunnel facilities has led to the development of the Cryo-genic Wind Tunnel. In this type of tunnel, the flow is cooled to extremely low temperatures, with the result that at constant Mach number the Reynolds number is greatly increased whilst the power required to drive the tunnel is reduced. The cryogenic tunnel incorporates a means of injecting liquid nitrogen into the free stream. The evaporation of this liquid cools the flow and some or all of the tunnel structure. Once the required low temperature has been reached a steady flow of liquid nitrogen into the tunnel and gaseous nitrogen out balances the heat input through the walls and from the fan and maintains constant pressure in the circuit. In addition to providing increased Reynolds numbers at reduced drive power, the cryogenic wind tunnel possesses numerous other advantages over its ambient temperature counterpart. For a detailed theory see Ref. 1.

Type
Technical Note
Information
The Aeronautical Journal , Volume 82 , Issue 815 , November 1978 , pp. 484 - 487
Copyright
Copyright © Royal Aeronautical Society 1978 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Kilgore, R. A., Goodyer, M. J., Adcock, J. B. and Davenport, E. E. The cryogenic wind tunnel concept for high Reynolds number testing. NASA Technical Note TN D-7762, November 1974.Google Scholar
2. Goodyer, M. J. The 0·1 m subsonic cryogenic tunnel at the University of Southampton. NASA Contractor Report CR 145305, January 1978.Google Scholar
3. Vargaftik, N. B. Tables on the thermophysical properties of liquids and gases, 2nd Ed. Hemisphere, 1975.Google Scholar
4. Mckinney, L. W. and Howell, R. R. The characteristics of the planned National Transonic Facility. Presented at the AIAA Ninth Aerodynamic Testing Conference, Arlington, Texas, June 1976.Google Scholar