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Boundary Layer Transition Measurements on Sharp and Blunt Cones in the T4 Stalker Tube

  • David J. MeeEmail author
  • Sreekanth Raghunath
Conference paper

Abstract

The process via which a hypersonic boundary layer transitions from laminar to turbulent flow is important in determining the length of transitional flow regions which is important information for designers of hypersonic vehicles. The effects of bluntness of the leading edge of the hypersonic body on the unsteady processes in the transitional region have not received much attention in the literature. This paper compares the unsteady processes in the transitional region for a slender cone with both a sharp and a blunted tip at hypersonic flow conditions in the T4 Stalker Tube. Fewer, more isolated turbulent spots were observed for the blunted than for the sharp cone when tested at similar or higher Reynolds number conditions.

References

  1. 1.
    S.P. Schneider, Hypersonic laminar-turbulent transition on circular cones and scramjet Forebodies. Prog. Aerosp. Sci. 40(1–2), 1–50 (2004)CrossRefGoogle Scholar
  2. 2.
    K.Y. Lau, Hypersonic boundary-layer transition: Application to high-speed vehicle design. J. Spacecr. Rocket. 45(2), 176–183 (2008)CrossRefGoogle Scholar
  3. 3.
    S. Frauholz, B.U. Reinartz, S. Müller, M. Behr, Transition prediction for scramjets using γ-Reθt model coupled to two turbulence models. J. Propuls. Power 31(5), 1404–1422 (2015)CrossRefGoogle Scholar
  4. 4.
    R.J. Stalker, R.G. Morgan, Free piston shock tunnel T4 – Initial operation and preliminary calibration, CR 181721, NASA, 1988Google Scholar
  5. 5.
    Jacobs, P. A., Morgan, R. G., Stalker, R. J., and Mee, D. J., Use of argon-helium driver-gas mixtures in the T4 shock tunnel, shock waves @ Marseille, Proceedings of the 19th International Symposium on Shock Waves, ed. by R. Brun and L. Dumitrescu, Springer, Berlin, 1993, pp. 263–268Google Scholar
  6. 6.
    L.M. Porter, High enthalpy, hypersonic drag measurements on blunt cones in an impulse facility, Ph.D. thesis, The University of Queensland, 1996Google Scholar
  7. 7.
    D.L. Schultz, T.V. Jones, Heat transfer measurements in short duration hypersonic facilities, AGARDograph 165, AGARD, 1973Google Scholar
  8. 8.
    K.A. Skinner, Mass spectrometry in shock tunnel experiments of hypersonic combustion, Ph.D. thesis, The University of Queensland, 1994Google Scholar
  9. 9.
    G.I. Taylor, J.W. Maccoll, The air pressure on a cone moving at high speed – II. Proc. R. Soc. Lond. A Math. Phys. Sci. 139(A838), 278–311 (1932)zbMATHGoogle Scholar
  10. 10.
    G. Simeonides, Generalized reference enthalpy formulations and simulation of viscous effects in hypersonic flow. Shock Waves 8(3), 161–172 (1998)CrossRefGoogle Scholar
  11. 11.
    E.R. Van Driest, Turbulent boundary layers in compressible fluids. J. Aeronaut. Sci. 18, 145–160 (1951)MathSciNetCrossRefGoogle Scholar
  12. 12.
    F.M. White, Viscous Fluid Flow (McGraw-Hill, New York, 1991)Google Scholar
  13. 13.
    D.J. Mee, Boundary-layer transition measurements in hypervelocity flows in a shock tunnel. AIAA J. 40(8), 1542–1548 (2002)CrossRefGoogle Scholar
  14. 14.
    J.S. Jewell, N.J. Parziale, I.A. Leyva, J.E. Shepherd, Effects of shock-tube cleanliness on hypersonic boundary layer transition at high enthalpy. AIAA J. 55(1), 332–338 (2017)CrossRefGoogle Scholar
  15. 15.
    D.J. Mee, C.P. Goyne, Turbulent spots in boundary layers in a free-piston shock-tunnel flow. Shock Waves 6, 337–343 (1996)CrossRefGoogle Scholar
  16. 16.
    S. Raghunath, D.J. Mee, R. Narasimha, Estimating turbulent spot initiation rates from transition lengths in hypersonic boundary layers. AIAA J., 2017, to appearGoogle Scholar

Copyright information

© Springer International Publishing AG, part of Springer Nature 2019

Authors and Affiliations

  1. 1.Centre for Hypersonics, School of Mechanical and Mining EngineeringThe University of QueenslandBrisbaneAustralia

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