Abstract
Copper calorimeter, based on a calorimetric principle, offers a solution for heat transfer measurement in high enthalpy situation, especially in the erosive flow of high enthalpy shock tunnels. In this study, we numerically investigated the measuring performance of copper calorimeters. Non-ideal effects, such as heat loss to the insulator around and replacement of the average temperature of the copper element by the junction temperature, were discussed in detail. The influences of copper element thickness, copper/constantan wires thickness and sensor diameter were also estimated, with the aim to provide theoretical guidance for the design of copper calorimeter. In addition, corresponding experiments in JF10 high enthalpy shock tunnel were carried out against the data of coaxial thermocouples for verification. Results showed that the non-ideal thermal environment of a copper calorimeter (heat exchange with its surroundings) would result in a smaller measuring heat flux comparing to the one actually loaded; proper thickness of copper element matching the effective test time of shock tunnel was suggested. Besides, preliminary experimental results with corrections showed reasonable agreement with the heat flux of thermocouples, with an average deviation of 8%. Over all, this gauge developed extends and supplements the high enthalpy shock tunnel heat transfer measurements made by other techniques.
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Qin J., Ning D.P., Feng Y, Zhang J.L., Feng S., Bao W. A new method of thermal protection by opposing jet for a hypersonic aero-heating strut. Journal of Thermal Science, 2017, 26(3): 282–288.
Lu H.B, Liu W.Q. Thermal protection efficiency of forward-facing cavity and opposing jet combinational configuration. Journal of Thermal Science, 2012, 21(4): 342–347.
Gai S.L., Nudford N.R. Stagnation point heat flux in hypersonic high enthalpy flows. Shock Waves, 1992, 2(1): 43 7.
Hanamitsu A., Kishimoto T., Bito H. High enthalpy flow computation and experiment around the simple bodies, Tokyo: Special Publication of National Aerospace Laboratory SP-29, 1996: 99–107.
Miller C.G.I. Comparison of thin film resistance heat transfer gauges with thin-skin transient calorimeter gauges in conventional HW tunnels, NSAS Sti/recon Technical Report N, 1982.
Wannenwetsch G., Ticatch L., Kidd C., Arterbury R., Measurements of wing leading edge heating rates on wind tunnel models using the thin film techniques. 20th Thermophysics Conference, Williamsburg: AIAA-1985-0972, 1985.
Saito T., Kuribayashi T., Menzes V., Sun M., Jagadeesh G., Takayama K. Unsteady convective surface heat flux measurements on a cylinder for CFD code validation studies. Shock Waves, 2004, 13(5): 327–337.
Saravanan S., Jagadeesh G., Reddy K.P.J. Convective heat transfer rate distribution over a missile shaped body flying at hypersonic speeds. Experimental Thermal and Fluid Science, 2009, 33(4): 782–790.
Sanderson S.R, Sturtevant B. Transient heat flux measurement using a surface junction thermocouple. Review of Scientific Instruments, 2002, 73(7): 2781–2787.
Menezes V., Bhat S. A coaxial thermocouple for shock tunnel applications. Review of Scientific Instruments, 2010, 81(10): 104905.
Mohammed H.A, Salleh H., Yusoff M.Z., Campo A. Thermal product of type-E fast response temperature sensors. Journal of Thermal Science, 2010, 19(4): 364–371.
Desikan S.L.N, Suresh K., Srinivasan K., Raveendran P.G. Fast response coaxial thermocouple for short duration impulse facilities. Applied Thermal Engineering, 2016, 96: 48–56.
Mohammed H., Salleh H., Yusoff M.Z. Design and fabrication of coaxial surface junction thermocouples for transient heat transfer measurements. International Communications in Heat and Mass Transfer, 2008, 35(7): 853–859.
Schultz D.L, Jones T.V. Heat transfer measurements in short duration hypersonic facilities, Technical Report, AGARD-AG-165, 1973.
Rose P.H. Development of the calorimeter heat transfer gauge for use in shock tubes. Review of Scientific Instruments, 1958, 29(7): 557–564.
Taler J. Theory of transient experimental techniques for surface heat transfer. International Journal of Heat and Mass Transfer, 1996, 39(17): 3733–3748.
Wool M.R, Murphy A.J, Rindal R.A. Calorimeter measurement of heat transfer at hypersonic conditions. Journal of Spacecraft and Rockets, 1974, 11(6): 363–367.
Nakakita K., Osafune T., Asai K., Global heat transfer measurement in a hypersonic shock tunnel using temperature sensitive paint. 41st AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, AIAA-2003-0743, 2003.
Nagai H., Ohmi S., Asai K., Nakakita K. Effect of temperature-sensitive-paint thickness on global heat transfer measurement in hypersonic flow. Journal of Thermophysics and Heat Transfer, 2008, 22(3): 373–381.
Merski N.R., Reduction of analysis of phosphor thermography data with the IHEAT software package. 36th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, AIAA-1998-0712, 1998.
Merski N.R. Global aero-heating wind tunnel measurements using improved two-color phosphor thermography methods. Journal of Spacecraft and Rockets, 1999, 36(2): 160–170.
Wu S., Shu Y.H, Li J.P, Yu H.R. An integral heat flux sensor with high spatial and temporal resolutions. Chinese Science Bulletin, 2014, 59(27): 3484–3489.
Beck W.H, Klein C., Henne U., Sachs W., Schramm J.M, Wagner A., et al. Application of temperature and pressure sensitive paints to DLR hypersonic facilities: "lessons learned". 53rd AIAA Aerospace Sciences Meeting, Kissimmee, Florida, AIAA-2015-0023, 2015.
Simmons J.M. Measurement techniques in high-enthalpy hypersonic facilities. Experimental Thermal and Fluid Science, 1995, 10(4): 454–469.
Li J.P, Chen H., Zhang S.Z, Zhang X.Y, Yu H.R. On the response of coaxial surface thermocouples for transient aerodynamic heating measurements. Experimental Thermal and Fluid Science, 2017, 86: 141–148.
Nawaz A., Santos J.A., Assessing calorimeter evaluation methods in convective and radiative heat flux environment. 10th AIAA/ASME Joint Thermophysics and Heat Transfer Conference, Chicago, Illinois, AIAA-2010-4905, 2010.
Santos J., Oishi T., Martinez E., Null point calorimeter sweeps with comparisons to thermal FEA model predictions. 41st AIAA Thermophysics Conference, San Antonio, Texas, AIAA-2009-3758, 2009.
Lohle S., Battaglia J.L, Jullien P., Ootegem B.V, Lasserre J.P, Couzi J. Improvement of high heat flux measurement using a null-point calorimeter. Journal of Spacecraft and Rockets, 2008, 45(1): 76–81.
Hoffmann K.A, Chiang S.T. Computational fluid dynamics, fourth ed., Wichita, Kansas: Engineering Education System, 2000.
ASTM Committee E20 on Temperature Measurement. Manual on the use of thermocouples in temperature measurement, fourth ed, American Society for Testing and Materials, 1974.
Zeng Z., Gui Y., Wang A.N, Qin F., Zhang H. Study on error mechanism and uncertainty assessment of heat flux measurement in shock tunnel. Journal of Experiments in Fluid Mechanics, 2015, 29(15): 15–25.
Lu F.K, Marren D.E. Advanced hypersonic test facilities, AIAA: Progress in Astronautics and Aeronautics, 2002.
Jiang Z.L, Yu H.R. Theories and technologies for duplicating hypersonic flight conditions for ground testing. National Science Review, 2017, 4(3): 290–296.
Zhao W., Jiang Z.L, Saito T., Lin J.M, Yu H.R, Takayama K. Performance of a detonation driven shock tunnel. Shock Waves, 2004, 14(1): 53–59.
Wang Q., Zhao W., Yu X.L, Jiang Z.L. Effective test time measurement research for high enthalpy shock tunnel. Acta Aeronautica et Astronautica Sinica, 2015, 36(11): 3534–353.
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This study is financially supported by the National Natural Science Foundation of China (Grant No. 11402275, No. 11472280 and No. 11532014) and the China Scholarship Council.
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Wang, Q., Li, J., Li, J. et al. Performance of Copper Calorimeter for Heat Transfer Measurement in High Enthalpy Shock Tunnel. J. Therm. Sci. 27, 373–381 (2018). https://doi.org/10.1007/s11630-018-1020-5
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DOI: https://doi.org/10.1007/s11630-018-1020-5