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Aerodynamic Heating Characteristics Over a Protuberance in Hypersonic Flows Using Fast Response Thermo Gauges

  • Published : 2010.09.15

Abstract

Through experimental investigations utilizing hypersonic shock tunnel-coaxial thermocouples as well as blow down hypersonic wind tunnel-temperature sensitive paints, the heat flux and the temperature over a protuberance were measured and analyzed. The experimental data were subsequently compared to heat flux data that was obtained by using blow down hypersonic wind tunnel and heat flux gauges. According to the comparison, both sets of data illustrated correlation with one another. The measured heat flux was large when the height of the protuberance was large. Experimental results show that heat flux measurements taken at higher locations were greater than those taken at lower locations. For high protuberances, a severe jump in the heat flux was observed, ranging in values within 0.6-0.7 of the height of the protuberances. However, when the protuberance was sufficiently short, a rise in the heat flux was rarely observed as the protuberance was totally submerged under the separation region.

Keywords

Protuberance;Hypersonic;Heat flux;Coaxial-thermocouple;Temperature--sensitive-paint

References

  1. Bell, J. H., Schairer, E. T., Hand, L. A., and Mehta, R. D. (2001). Surface pressure measurements using luminescent coatings. Annual Review Fluid Mechanics, 33, 155-206. https://doi.org/10.1146/annurev.fluid.33.1.155
  2. Buttsworth, D. R., Stevens, R., and Stone, C. R. (2005). Eroding ribbon thermocouple: impulse response and transient heat flux analysis. Measurement Science Technology, 16, 1487-1494. https://doi.org/10.1088/0957-0233/16/7/011
  3. Couch, L. M. (1969). Flow-Field Measurements Downstream of Two Protuberances on a Flat Plate Submerged in a Turbulent Boundary Layer at Mach 2.49 and 4.44. NASA TN D-5297. Washington, DC: National Aeronautics and Space Administration.
  4. Hiers R. S. and Loubsky W. J. (1967). Effect of Shock-Wave Impingement on the Heat Transfer on a Cylindrical Leading Edge. NASA TN D-3859. Washington, DC: National Aeronautics and Space Administration.
  5. Hung, F. T. and Clauss, J. M. (1980). Three dimensional protuberance interference heating in high speed flow. 18th AIAA Aerospace Sciences Meeting, Pasadena, CA. AIAA-80-289.
  6. Hung, F. T. and Patel, D. K. (1984). Protuberance interference heating in high speed flow. 19th AIAA, Thermophysics Conference, Snowmass, CO. AIAA-84-39368.
  7. Kaufman, L. G., Kerkegi, R. H., and Morton, L. C. (1973). Shock impingement caused by boundary layer separation ahead of blunt fins. AIAA Journal, 11, 1363-1364. https://doi.org/10.2514/3.50590
  8. Lee, H. J., Lee, B. J. Jeung I. S., Kim, S. L., and Kim, I. (2009). Measurement of aerodynamic heating over the protuberance in hypersonic flow at Mach 7. Journal of the Korean Society for Aeronautical and Space Science, 37, 562-570. https://doi.org/10.5139/JKSAS.2009.37.6.562
  9. Liu, T. and Sullivan, J. P. (2005) Pressure and Temperature Sensitive Paints. New York: Springer.
  10. Nakakita, K., Osafune, T., and Asai, K. (2003). Global heat transfer measurement in a hypersonic shock tunnel using temperature-sensitive-paint. 41th AIAA Aerospace Sciences Meeting, Reno, NV. AIAA-2003-0743.
  11. Ohmi, S., Nagai, H., and Asai, K. (2006). Effect of TSP layer thickness on global heat transfer measurement in hypersonic flow. 44th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV. AIAA-2006-1048.
  12. Sedney, R. (1973). A survey of the effect of small protuberances on boundary layer flows. AIAA Journal, 11, 782-792. https://doi.org/10.2514/3.50520
  13. Sedney, R. (1975). The structure of three-dimensional separated flows in obstacle, boundary-layer interactions. AGARD Conference Proceedings, Vol. 168.
  14. Truitt, R. W. (1965). Hypersonic turbulent boundary layer interference heat transfer in vicinity of protuberance. AIAA Journal, 3, 1745.
  15. Waltrup, P. J., Hall, D. J., and Schetz, J. A. (1968). Flowfield in the vicinity of cylindrical protuberance on a flat plate in supersonic flow. Journal of Spacecraft, 5, 127-128. https://doi.org/10.2514/3.29203
  16. Westkaemper, J. C. (1968). Turbulent boundary-layer separation ahead of cylinders. AIAA Journal, 6, 1352-1355. https://doi.org/10.2514/3.4747
  17. Whitehead, A. H. (1969). Flow-Field and Drag Characteristics of Several Boundary-Layer Tripping Elements in Hypersonic Flow. NASA TN D-5454. Washington, DC: National Aeronautics and Space Administration.

Cited by

  1. Hypersonic Interference Heating on Flat Plate with Short Three-Dimensional Protuberances vol.52, pp.4, 2014, https://doi.org/10.2514/1.J052658
  2. Experimental Investigation of Heat Fluxes in the Vicinity of Protuberances on a Flat Plate at Hypersonic Speeds vol.135, pp.12, 2013, https://doi.org/10.1115/1.4024667

Acknowledgement

Supported by : National Research Foundation of Korea (NRF)