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Constant temperature hot-wire measurements in a short duration supersonic wind tunnel

Published online by Cambridge University Press:  04 July 2016

J. Weiss ,
H. Knauss ,
S. Wagner  and
A. D. Kosinov
J. Weiss
Affiliation:
Institut für Aerodynamik und Gasdynamik (IAG) Universität Stuttgart, Germany
H. Knauss
Affiliation:
Institut für Aerodynamik und Gasdynamik (IAG) Universität Stuttgart, Germany
S. Wagner
Affiliation:
Institut für Aerodynamik und Gasdynamik (IAG) Universität Stuttgart, Germany
A. D. Kosinov
Affiliation:
Institute for Theoretical and Applied Mechanics (ITAM) Novosibirsk, Russia
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Abstract

A constant temperature hot-wire anemometer enabling automatic rapid scanning of the wire overheat was built to perform free stream disturbance measurements in the shock wind tunnel of the Institute for Aerodynamics and Gasdynamics at Stuttgart University. It is shown that such a system brings real advantages in terms of testing time. The change of bridge dynamic behaviour with wire temperature is taken into account by measuring the bridge frequency response with a very fast electrical test and postprocessing the data. The method of operation is validated in a supersonic suck down wind tunnel and a comparison with a commercial constant temperature bridge shows good agreement. Results of free stream disturbance measurements in a short duration supersonic wind tunnel of 120ms testing time are presented.

Type
Research Article
Information
The Aeronautical Journal , Volume 105 , Issue 1050 , August 2001 , pp. 435 - 450
Copyright
Copyright © Royal Aeronautical Society 2001 

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References

1. Knauss, H., Riedel, R. and Wagner, S. The shock wind tunnel of Stuttgart University, a facility for testing hypersonic vehicles, AIAA 99-4959, 1999.Google Scholar
2. Schneider, S.P. Effect of high-speed tunnel noise on laminar-turbulent transition, AIAA 2000-2205, 2000.Google Scholar
3. Kovásznay, L.S.G. Turbulence in supersonic flow, J Aero Sci, 1953, 20 (10), pp 657–674.Google Scholar
4. Morkovin, M.V. Fluctuations and hot-wire anemometry in compress ible flows, AGARDograph, 1956, 24.Google Scholar
5. Morkovin, M.V. On transition experiments at moderate supersonic speeds, J Aero Sci, 1957, 24, pp 480–486.Google Scholar
6. Morkovin, M.V. On supersonic wind tunnels with low free stream disturbances, J Appl Mech, 1959, 26, (3), pp 319–323.Google Scholar
7. Laufer, J. Aerodynamic noise in supersonic wind tunnels, J Aero Sci, 1961, 28, (9), pp 685–692.Google Scholar
8. Bruun, H.H. Hot-wire Anemometry, Principles and Signal Analysis, 1995, Oxford University Press.Google Scholar
9. Fingerson, L.M. Thermal anemometry, current state, and future directions, Rev Sci Instrum, 1994, 65, (2), pp 285–300.Google Scholar
10. Kovasznay, L.S.G. The hot-wire anemometer in supersonic flow, J Aero Sci, 1950,17, (9), pp 565–573.Google Scholar
11. Sarma, G.R., Comte-Bei.Lot, G. and Faure, T.M. Software corrected hot-wire thermal lag for the constant voltage anemometer featuring a constant bandwidth at the selected compensation setting. Rev Sci Instrum, 1998, 69, (9), pp 3223–3231.Google Scholar
12. Lebiga, V.A. and Zinoviev, V.N. Hot-wire measurements in compressible flows, 1989. Proc of Int Conf on Instrumentation in Aerospace Simulations, DLR Gdttingen, Germany, IEEE 89CH2762-3, pp 385–393.Google Scholar
13. Smits, A.J., Hayakawa, K. and Muck, K.C. Constant temperature hot-wire anemometer practice in supersonic flows, Exp Fluids, 1983,1, pp 83–92.Google Scholar
14. Walker, D.A. Ng, W.F. and Walker, M.D. Experimental comparison of two hot-wire techniques in supersonic flow, AIAA J, 1989. 27. (8), pp 1074–1080.Google Scholar
15. Smits, A.J. and Dussauge, J.P. Hot-wire anemometry in supersonic flows, 1989, AGARDograph 315, 5.1-5.14.Google Scholar
16. Bestion, D.. Gaviglio, J. and Bonnet, J.P. Comparison between constant-current and constant-temperature hot-wire anemometers in high speed flows, Rev Sci Iustrum, 1983, 54, (II), pp 1513–1524.Google Scholar
17. Kosinov, A.D., Semionov, N.V. and Yermolaev, Y.G. Automated measuring method of noise level in T-325 test section, 1996, Proceed ings of the international conference on the methods of Aerophysical Research, Novosibirsk, Russia, 2, pp 131–136.Google Scholar
18. Kosinov, A.D. and Repkov, V.V. Design and application of CTA in supersonic flow, 1998, Proceedings of the international conference on the methods of aerophysical research, Novosibirsk, Russia, unpublished.Google Scholar
19. Freymuth, P. Über einige spezielle Probleme der Hitzdrahtmeßtechnik, 1966, Deutsche Luft-und Raumfahrt, Report 66-03.Google Scholar
20. Freymuth, P. Feedback control theory for constant-temperature hot-wire anemometers, Rev Sci Instrum, 1967, 38, (5), pp 677–681.Google Scholar
21. Freymuth, P. and Fingerson, L.M. Electronic testing of frequency response for thermal anemometers, TS1 Quarterly, 1977, 3, pp 5–12.Google Scholar
22. Perry, A.E. and Morrison, G.L. A study of the constant-temperature hot-wire anemometer, J Fluid Mech, 1971, 47, (3), pp 577–599.Google Scholar
23. Wood, N.B. A method for determination and control of the frequency response of the constant-temperature hot-wire anemometer, J Fluid Mech, 1975, 67, (4), pp 769–786.Google Scholar
24. Watmuff, J.H. An investigation of the constant-temperature hot-wire anemometer, Exp Thermal Fluid Sci, 1995, 11, pp 117–134.Google Scholar
25. Freymuth, P. On higher order dynamics of constant-temperature hot wire anemometers, Meas Sci Technol, 1998, 9, pp 534–535.Google Scholar
26. Walker, D.A. and Walker, M.D. Method for fast sine-wave calibration of hot-wire frequency response, Rev Sci Instrum, 1990, 61, (3), pp 1131–1135.Google Scholar
27. Weiss, J., Knauss, H., and Wagner, S. Method for the determination of frequency response and signal to noise ratio for constant-temperature hot-wire anemometers, Rev Sci Instrum, 2001, 72, (3), pp 1904–1909.Google Scholar
28. Freymuth, P. Noise in hot-wire anemometers, Rev Sci Instrum, 1968, 39, (4), pp 550–557.Google Scholar
29. Saddoughi, S.G. and Veeravalli, S.V. Hot-wire anemometry behaviour at very high frequencies, Meas Sci Technol, 1996,7, pp 1297–1300.Google Scholar
30. Kosinov, A.D., Semionov, N.V. and Yermolaev, Y.G. Disturbances in test section of T-325 supersonic wind tunnel, 1999, ITAM preprint 6–99.Google Scholar