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Calibration of transonic and supersonic wind tunnelsState-of-the art instrumentation and procedures for calibrating transonic (0.6 less than M less than 1.4) and supersonic (M less than or equal to 3.5) wind tunnels were reviewed and evaluated. Major emphasis was given to transonic tunnels. Continuous, blowdown and intermittent tunnels were considered. The required measurements of pressure, temperature, flow angularity, noise and humidity were discussed, and the effects of measurement uncertainties were summarized. A comprehensive review of instrumentation currently used to calibrate empty tunnel flow conditions was included. The recent results of relevant research are noted and recommendations for achieving improved data accuracy are made where appropriate. It is concluded, for general testing purposes, that satisfactory calibration measurements can be achieved in both transonic and supersonic tunnels. The goal of calibrating transonic tunnels to within 0.001 in centerline Mach number appears to be feasible with existing instrumentation, provided correct calibration procedures are carefully followed. A comparable accuracy can be achieved off-centerline with carefully designed, conventional probes, except near Mach 1. In the range 0.95 less than M less than 1.05, the laser Doppler velocimeter appears to offer the most promise for improved calibration accuracy off-centerline.
Document ID
19780007115
Document Type
Contractor Report (CR)
Authors
Reed, T. D. (Vought Corp. Advanced Technology Center, Inc. Dallas, TX, United States)
Pope, T. C. (Vought Corp. Advanced Technology Center, Inc. Dallas, TX, United States)
Cooksey, J. M. (Vought Corp. Advanced Technology Center, Inc. Dallas, TX, United States)
Date Acquired
September 3, 2013
Publication Date
November 1, 1977
Subject Category
RESEARCH AND SUPPORT FACILITIES (AIR)
Report/Patent Number
NASA-CR-2920
Funding Number(s)
CONTRACT_GRANT: NAS2-8606
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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