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Experimental Facilities and Measuring Techniques

Published online by Cambridge University Press:  04 July 2016

D. W. Holder
D. W. Holder*
Affiliation:
Aerodynamics Division, National Physical Laboratory
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Summary

Some of the aerodynamic problems that arise in flight at hypersonic speeds can be studied experimentally with wind tunnels and measuring techniques that do not differ in principle from those used for research on supersonic flow. If, however, it is required to simulate the very high temperatures of hypersonic flight, it is usually necessary to use heaters and tunnels of unconventional design, frequently having a very short running time, or to make tests with a model launched or propelled at high velocity.

The short running times sometimes involve the use of measuring techniques that differ considerably from those of conventional wind tunnel practice. Also, in the presence of high temperature, real gas effects, it is sometimes necessary to measure additional quantities in order to define the state of the gas. The paper contains a brief introductory review of these topics, and of the extent to which experimental test facilities can reproduce the conditions of full-scale hypersonic flight.

Type
Hypersonic Flow
Information
The Aeronautical Journal , Volume 63 , Issue 585 , September 1959 , pp. 493 - 502
Copyright
Copyright © Royal Aeronautical Society 1959

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References

1.Smelt, R. and Sivells, J. C. (1957). Design and Operation of Hypersonic Wind Tunnels. AGARD Report 135, 1957.Google Scholar
2.Bogdonoff, S. M. (1957). Exploratory Studies of Hypersonic Fluid Mechanics. AGARD Report 142, 1957.Google Scholar
3.Hammitt, A. G. (1954). The Development of a Helium Hypersonic Wind Tunnel and the Investigation of Hypersonic Flow about Simple Bodies, Princeton University Aeronautical Engineering Report 253, 1954.Google Scholar
4.Purser, P. E. and Bond, A. C. (1957). NACA Hypersonic Rocket and High-Temperature Jet Facilities. AGARD Report 140, 1957.Google Scholar
5.Giannini, G. M. (1957). The Plasma Jet. Scientific American, Vol. 197, p. 80, August 1957.CrossRefGoogle Scholar
6.Heldenfels, R. R. and Kotanchik, J. N. (1958). Electric Arc-Powered Air Jets for Materials and Structures Testing at Temperatures to 10,000°R. Summer Meeting, I.A.S., Los Angeles, July 1958.Google Scholar
7.Brogan, T. R. (1958). Electric Gas Heaters for Re-entry Simulation and Space Propulsion. Proceedings American Rocket Society, 13th Annual Meeting, New York, 1958.Google Scholar
8.Lai, W., Gustavson, J. and Talbot, L. Design Consideration and Initial Evaluation of Model B Plasma Generator. University of California Institute of Engineering Research Technical Report HE-150-161.Google Scholar
9.Ferri, A. and Libby, P. A. (1957). The Hypersonic Facility of the Polytechnic Institute of Brooklyn and its Application to Problems of Hypersonic Flight. AGARD Report 136, 1957. Google Scholar
10.Cox, R. N. and Winter, D. F. T. (1957). The Light Gas Hypersonic Gun Tunnel at ARDE, Fort Halstead, Kent. AGARD Report No. 139, July 1957.Google Scholar
11.Bray, K. N. C., Pennelegion, L. and East, R. A. (1959). Performance Studies for the University of Southampton Hypersonic Gun Tunnel. Proceedings of the Colston Symposium, University of Bristol, 1959.Google Scholar
12.Glass, I. I. (1953). A Theoretical and Experimental Study of the Shock Tube. University of Toronto Institute of Aerophysics Report No. 2, November 1953.Google Scholar
13.Lukasiewicz, J. Shock Tube Theory and Applications, National Aeronautical Establishment, Canada, Report 15. 10.Google Scholar
14.Henshall, B. D. (1956). The Use of Multiple Diaphragms in Shock Tubes. A.R.C., Current Paper 291, 1956.Google Scholar
15.Henshall, B. D. (1959). Experimental Results from the NPL Hypersonic Shock Tunnel. Proceedings of the Colston Symposium, University of Bristol, 1959.Google Scholar
16.Vitale, A. J., Kaegi, E. M., Diaconis, N. S. and Warren, W. R. (1958). Results from Aerodynamic Studies of Blunt Bodies in Hypersonic Flow of Partially Dissociated Air. Heat Transfer and Fluid Mechanics Institute Report, California, June 1958.Google Scholar
17.Nagamatsu, H. T. (1958). Shock Tube Technology and Design, General Electric Research Laboratory Report No. 58-RL-2107, 1958.Google Scholar
18.Hertzberg, A. (1957). The Shock Tunnel and Its Application to Hypersonic Flight. AGARD Report 144, 1957.Google Scholar
19.Wittliff, C. E., Wilson, M. R. and Hertzberg, A. (1959). The Tailored-Interface Hypersonic Shock Tunnel. Journal of the Aeronautical Sciences, Vol. 16, p. 219, April 1959.Google Scholar
20.Lukasiewicz, J. (1958). Experimental Investigation of Hypervelocity Flight. Proc. First International Congress of the Aeronautical Sciences, Madrid, 1958, Pergamon Press, 1959.Google Scholar
21.Perry, R. S. and MacDermott, W. N. (1958). Development of the Spark-Heated, Hypervelocity, Blowdown Tunnel-Hotshot. Arnold Engineering Development Center Report AEDC-TR-58-6, June 1958.Google Scholar
22.Seiff, A. (1957). The Use of Gun-Launched Models for Experimental Research at Hypersonic Speeds. AGARD Report 138, 1957.Google Scholar
23.Lobb, R. K. (1959). Hypersonic Research at the Naval Ordnance Laboratory. Proceedings of the Colston Symposium, University of Bristol, 1959.Google Scholar
24.Bray, K. N. C. (1958). Departure from Dissociation Equilibrium in a Hypersonic Nozzle. Aeronautical Research Council Report ARC 19983, 1958.Google Scholar
25.Mulkey, M. R., Earheart, W. T. and McAdams, E. E. (1958). Pressure Measurements in an Arc Discharge Wind Tunnel. Arnold Engineering Development Center. Report AEDC-TN-58-16, 1958.Google Scholar
26.Dimeff, J. (1958). A Survey of New Developments in Pressure Measuring Techniques in the NACA. AGARD Report 166, 1958.Google Scholar
27. Technical Literature from: - Swiss Locomotive and Machine Works, Winterthur, Switzerland.Google Scholar
28. Technical Literature from:- Atlantic Research Corporation, Alexandria, Virginia, U.S.A.Google Scholar
29.Rose, P. H. and Stark, W. I. (1958). Stagnation Point Hea-Transfer Measurements in Dissociated Air. Journal of the Aeronautical Sciences, Vol. 25, p. 86, February 1958.Google Scholar
30.Henshall, B. D. and Schultz, D. L. (1958). Some notes on the Use of Resistance Thermometers for the Measurement of Heat Transfer Rates in Shock Tubes. A.R.C. Report ARC 20,204, 1958.Google Scholar
31.Rose, P. H. (1958). Development of the Calorimeter Heat Transfer Gauge for use in Shock Tubes. Avco Research Corporation, RR 17, 1958.Google Scholar
32.Holder, D. W. and North, R. J. (1956). Optical Methods for Examining the Flow in High-Speed Wind Tunnels, Part I AGARDograph No. 23, 1956.Google Scholar
33.North, R. J. (1958). A Cranz-Schardin Camera for Use with a Hypersonic Shock Tunnel. 4th International Conference on High-Speed Photography, Cologne, 1958.Google Scholar
34.Electron-Optical Study of Low-Density Gas Flow. National Bureau of Standards, Technical News Bulletin, p. 158, October 1957.Google Scholar
35.Clouston, J. G., Gaydon, A. G. and Glass, I. I. (1958). Temperature Measurements of Shock Waves by the Spectrum-line Reversal Method. Proc. Roy. Soc. A. Vol. 248. p. 429, December 1958.Google Scholar
36.Lapworth, K. C. (1959). Shock Tube Research at the National Physical Laboratory on the Properties of Gases at High Temperatures. Part II Preliminary Spectrographic Measurements Report NPL/Aero/374, February 1959.Google Scholar
37.Petschek, H. E., Rose, P. H., Glick, H. S., Kane, A. and Kantrowitz, A. (1955). Spectrographic Studies of Highly Ionized Argon produced by Shock Waves. J. App. Phys, Vol. 26, p. 83, January 1955.Google Scholar
38.Turner, E. B. The Production of Very High Temperatures in the Shock Tube with an Application to the Study of Spectral Line Broadening. Engineering Research Institute of the University of Michigan, Project 2189.Google Scholar
39.Byron, S. R. Interferometric Measurement of the Rate of Dissociation of Oxygen heated by Strong Shock Waves. Graduate School of Aeronautical Engineering, Cornell University.Google Scholar
40.Venable, D. and Kaplan, D. E. (1955). Electron Beam Method for determining Density Profiles across Shock Waves. J. App. Phys., Vol. 26, No. 5, May 1955.Google Scholar
41.Duff, R. E., Knight, H. J. and Rink, J. P. (1958). Precision Flash X-ray Determination of Density Ratio in Gaseous Detonations. Physics of Fluids, Vol. 1, p. 393. September 1958.CrossRefGoogle Scholar
42.Schultz, D. L. (1959). Shock Tube Research at the National Physical Laboratory on the Properties of Gases at High Temperatures, Part I, Ionization Measurements. Proceedings of the Colston Symposium. University of Bristol, 1959.Google Scholar
43.Lin, S. C., Resler, E. L. and Kantrowitz, A. (1955). Electrical Conductivity of Highly Ionized Argon produced by Shock Waves. J. App. Phys., Vol. 26, p. 95, January 1955.CrossRefGoogle Scholar