Hostname: page-component-78c5997874-lj6df Total loading time: 0 Render date: 2024-11-10T20:13:24.825Z Has data issue: false hasContentIssue false
  • English
  • Français

Heat transfer rate and surface pressure measurements in short duration hypersonic flow

Published online by Cambridge University Press:  18 October 2019

M. Saiprakash Open the ORCID record for M. Saiprakash [Opens in a new window] ,
C. Senthil Kumar ,
G. Kadam Sunil ,
S.P. Rampratap ,
V. Shanmugam  and
G. Balu
M. Saiprakash*
Affiliation:
Department of Aerospace Engineering, MIT Campus, Anna University, Chennai, India
C. Senthil Kumar
Affiliation:
Department of Aerospace Engineering, MIT Campus, Anna University, Chennai, India
G. Kadam Sunil
Affiliation:
Directorate of Aerodynamics, Defence Research and Development Laboratory, Hyderabad, India
S.P. Rampratap
Affiliation:
Directorate of Aerodynamics, Defence Research and Development Laboratory, Hyderabad, India
V. Shanmugam
Affiliation:
Directorate of Aerodynamics, Defence Research and Development Laboratory, Hyderabad, India
G. Balu
Affiliation:
Directorate of Aerodynamics, Defence Research and Development Laboratory, Hyderabad, India
*
saiaero87@gmail.com
Get access Rights & Permissions [Opens in a new window]

Abstract

Experiments were carried out with air as the test gas to obtain the surface convective heating rate and surface pressure distribution on blunt and sharp cone models flying at hypersonic speeds. Tests were performed in a hypersonic shock tunnel at two different angles of attack: ${0}^\circ$ and ${5}^\circ$ with angles of rotation $\phi = {0}^\circ, {90}^\circ$, and ${180}^\circ$. The experiments were conducted at a stagnation enthalpy of 1.4MJ/kg, flow Mach number of 6.56 and free stream Reynolds number based on the model length of $9.1 \times {10}^{5}$. The effective test time of the shock tunnel is 3ms. The results obtained for cone model with a bluntness ratio of 0.2 were compared with sharp cone models for $\alpha ={0}^\circ$. The measured stagnation heat transfer value matched well with the theoretical value predicted by the Fay and Riddell correlation and with the CFD results.

Keywords

hypersonic flow over the cone modelheat transfer in hypersonic flowheat transfer in hypersonic flowshock waves in hypersonic flow
Type
Research Article
Information
The Aeronautical Journal , Volume 123 , Issue 1269 , November 2019 , pp. 1857 - 1880
Copyright
© Royal Aeronautical Society 2019 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

Footnotes

*

Research Scholar, Department of Aerospace Engineering, Madras institute of Technology, Anna University, Chennai, India

†

Professor, Department of Aerospace Engineering, Madras institute of Technology, Anna University, Chennai, India.

‡

Scientist, Directorate of Aerodynamics, Defence Research and Development Laboratory, Hyderabad, India.

References

REFERENCES

Niranjan, S., Saravanan, S., Jagadeesh, G. and Reddy, K.P.J. Simultaneous measurement of aerodynamic and heat transfer data for large angle blunt cones in hypersonic shock tunnel, Sadhana, October 2006, 31, (5), pp 557–581. doi: 10.1007/BF02715914.Google Scholar
Saravanan, S., Jagadeesh, G. and Reddy, K.P.J. Convective heat-transfer rate distributions over a missile shaped body flying at hypersonic speeds, Experimental Thermal and Fluid Science, April 2009, 33, (4), pp 782–790. doi: 10.1016/j.expthermflusci.2009.02.005.CrossRefGoogle Scholar
Raju, I.S. and Craft, W.J. Analysis and sizing of mars aero brake structure, J of Spacecraft and Rocket, January-February 1993, 30, (1), pp 102–110. doi: 10.2514/3.25476.CrossRefGoogle Scholar
Mohammed Ibrahim, S. and Reddy, K.P.J. Heat transfer measurements over large angle blunt cones entering Martian atmosphere, J of Spacecraft and Rockets, May-June 2013, 50, (3), pp 719–722. doi: 10.2514/1.A32454.CrossRefGoogle Scholar
Jian-Xia, L., Zhong-Xi, H., Xiao-Qian, C. and Jun-Tao, Z. Experimental and numerical study on the aero-heating characteristics of blunted wave rider, Applied Thermal Engineering, March 2013, 51, (2), pp 301–314. doi: 10.1016/j.applthermaleng.2012.09.026.Google Scholar
Stewart, D.A. and Chen, Y.K. Hypersonic convective heat transfer over 140-deg blunt cones in different gases, J of Spacecraft and Rockets, September-October 1994, 31, (5), pp 735–743. doi: 10.2514/3.26506.CrossRefGoogle Scholar
Srinivasan, K., Desikan, S.L.N., Saravanan, R., Kumar, A. and Maurya, P.K. Fore-body and base heat flux measurements on a typical crew module in short duration impulse facilities, Applied Thermal Engineering, June 2016, 103, pp 842–854. doi: 10.1016/j.applthermaleng.2016.04.111.CrossRefGoogle Scholar
Miller, C.G. Comparison of Thin-film Resistance Heat-transfer Gages with Thin skin Transient Calorimeter Gages in Conventional Hypersonic wind Tunnels, NASA Technical Memorandum 83197, December 1981.Google Scholar
Wannenwetsch, G.D., Ticatch, L.A., Kidd, C.T. and Arterbury, R.L. Measurements of wing-leading edge heating rates on wind tunnel models using the thin-film technique, AIAA 20th Thermo physics Conference, June 1985, pp 1–12. doi: 10.2514/6.1985-972.CrossRefGoogle Scholar
Kidd, C.T. Recent developments in high heat-flux measurements at the AEDC, Proceedings of the 36th International Instrumentation Symposium, May 1990, pp 477–492.Google Scholar
Kidd, C.T. High heat-flux measurements and experimental calibrations/ characterizations, in: Jag, J. Singh, Richard, R. Antcliff (Eds), NASA CP-3161, NASA, Washington, DC, 1992, pp 31–50.Google Scholar
Sanderson, S.R. and Sturtevant, B. Transient heat flux measurement using a surface junction thermocouple, Review of Scientific Instruments, July 2002, 73, (7), pp 2781–2787. doi: 10.1063/1.1484255.CrossRefGoogle Scholar
Hubner, J.P., Carroll, B.F. and Schanze, K.S. Heat transfer measurements in hypersonic flow using luminescent coating techniques, J of Thermophysics and Heat Transfer, October–December 2002, 16, (4), pp 516–522. doi: 10.2514/2.6726.CrossRefGoogle Scholar
Asai, K., Kunimasu, T. and Iijima, Y. Visualization of the quiet test region in a supersonic wind tunnel using luminescent paint, 17th International Congress on Instrumentation in Aerospace Simulation Facilities, 29 September–2 October, 1997, pp 84–94. doi: 10.1109/iciasf.1997.644667.CrossRefGoogle Scholar
De Luca, L., Cardone, G., Carlomagno, G.M., Aymer de la Chevalerie, D. and de Roquefort, Alziary, T. Flow visualization and heat transfer measurement in a hypersonic wind tunnel, Experimental Heat Transfer, 1992, 5, (1), pp 65–78.CrossRefGoogle Scholar
Micol, J.R. Aerothermodynamics measurement and prediction for a modified orbiter at Mach 6 and 10 in air. J of Spacecraft and Rockets, 1995, 32, (5), pp 737–748. doi: 10.2514/3.26678.CrossRefGoogle Scholar
Kumar, R. Design, Fabrication and Novel Calibration Techniques for Heat Transfer Gauges during Short Duration Transient Measurement, Thesis, Guwahati, 2014.Google Scholar
Kuribayashi, T., Ohtani, K., Takayama, K., Menezes, V., Sun, M. and Saito, T. Heat flux measurement over a cone in a shock tube flow, Shock Waves, May 2007, 16, (5), pp 275–285. doi: 10.1007/s00193-006-0068-4.CrossRefGoogle Scholar
Irimpan, K.J., Mannil, N., Arya, H. and Menezes, V. Performance evaluation of coaxial thermocouple against platinum thin film gauge for heat flux measurement in shock tunnel. Measurement, 2015, 61, pp 291–298. doi: 10.1016/j.measurement.2014.10.056.CrossRefGoogle Scholar
Menezes, V., Saravanan, S., Jagadeesh, G. and Reddy, K.P.J. Experimental investigations of hypersonic flow over highly blunted cones with aerospikes, AIAA Journal, October 2003, 41, (10), pp 1955–1968. doi: 10.2514/2.1885.CrossRefGoogle Scholar
Shanmugam, V., Rampratap, S.P. and Prasad, R.J. Calibration of recently commissioned hypersonic shock tunnel, National Conference on Wind Tunnel Testing (NCWT-02), 12–14 March 2009, Bangalore.Google Scholar
Kinnear, K.M. and Lu, F.K. Design, calibration and testing of transient thin film heat transfer gauge, 20th AIAA Advanced Measurement and Ground Testing Technology Conference, Fluid Dynamics and Co-located Conferences, June 1998. doi: 10.2514/6.1998-2504.CrossRefGoogle Scholar
Heiser, H.W. and Pratt, D.T. Hypersonic air breathing propulsion, AIAA Education series, Washington, DC, 1994.CrossRefGoogle Scholar
Cook, W.J. and Felderman, E.J. Reduction of data from thin film heat transfer gauge a concise numerical technique, AIAA Journal, March 1966, 49 (3), pp 561–562. doi: 10.2514/3.3486.CrossRefGoogle Scholar
Kendall, D.N., Dixon, W.P. and Schulte, E.H. Semiconductor surface thermocouple for determining heat-transfer rates, IEEE Transactions on Aerospace and Electronic Systems, July 1967, AES-3, (4), pp 596–603.CrossRefGoogle Scholar
Hollis, B.R. User’s manual for the One-Dimensional Hypersonic Experimental Aero-Thermodynamic (1DHEAT) data reduction code, NASA Contractor Report 4691, August 1995.Google Scholar
Inouye, M. Shock standoff distance for equilibrium flow around hemisphere obtained from numerical calculation. AIAA Journal, 1965, 3, (1), pp 172–173.CrossRefGoogle Scholar
https://imagej.net/Fiji/Downloads.Google Scholar
Lees, L. Laminar heat transfer over blunt-nosed bodies at hypersonic flight speeds, J of Jet Propulsion, April 1956, 26, (4), pp 259–269.CrossRefGoogle Scholar
Fay, F.R. and Riddell, J.A. Theory of stagnation point heat transfer in dissociated air, J of Aeronautical Sciences, 1958, 25, (2), pp 73–85.Google Scholar
Saiprakash, M., Senthilkumar, C., Balu, G., Shanmugam, V., Rampratap, S.P. and Kadamsunil, G. Convective heat transfer rate and surface pressure distribution over a cone model at hypersonic speeds, Proceeding of Institution of Mechanical Engineers Part G. Journal of Aerospace Engineering, October 2018. doi: 10.1177/0954410018804691.CrossRefGoogle Scholar
Stewart, D.A. and Chen, Y.K. Hypersonic convective heat transfer over 140-deg blunt cones in different gases, J of Spacecraft and Rockets, September-October 1994, 31, (5), pp 735–743. doi: 10.2514/3.26506.Google Scholar
Gino, M. and Bleich, G. Three dimensional flow around blunt bodies, AIAA Journal, 1967, 5, (9), pp 1557–1562.Google Scholar
Supplementary material: File

Saiprakash et al. supplementary material

Saiprakash et al. supplementary material

Download Saiprakash et al. supplementary material(File)
File 216.8 KB