Summary
This paper brings together some of the testing techniques developed for transonic cryogenic tunnels using Nitrogen as the test fluid. It emphasizes techniques which required special development, or were unique because of the opportunities offered by cryogenic operation. The first part of the paper is used to discuss measuring the static aerodynamic coefficients normally used to determine component efficiency. The first topic is testing of two dimensional airfoils at transonic Mach numbers and flight values of Reynolds number. Three dimensional tests of complete configurations and sidewall mounted wings are also described. Since flight Reynolds numbers are of interest, free transition must be allowed. A discussion is given of wind tunnel and model construction effects on transition location.
The second part of the paper deals with time dependent phenomena, fluid mechanics, and measurement techniques. The time dependent, or unsteady, aerodynamic test techniques described include testing for flutter, buffet, and oscillating airfoil characteristics. In describing non-intrusive laser techniques, discussions are given regarding optical access, seeding, forward scatter lasers, two-spot lasers, and laser holography. Methods of detecting transition and separation will be reported and a new type of skin friction balance is described. There are 29 references to assist in obtaining further information.
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References
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© 1991 Springer-Verlag New York, Inc.
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Lawing, P.L. (1991). Aerodynamic Testing in Cryogenic Nitrogen Gas — A Precursor to Testing in Superfluid Helium. In: Donnelly, R.J. (eds) High Reynolds Number Flows Using Liquid and Gaseous Helium. Springer, New York, NY. https://doi.org/10.1007/978-1-4612-3108-0_3
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DOI: https://doi.org/10.1007/978-1-4612-3108-0_3
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