Heat Transfer at the Nose of a High-Speed Missile

  • J. Srulijes
  • F. Seiler
  • P. Hennig
  • P. Gleich
Part of the Notes on Numerical Fluid Mechanics and Multidisciplinary Design book series (NNFM, volume 112)


The heat loads during high-speed missile flight have to be considered in the design process by selecting appropriate geometries, structures and materials. To model these loads, especially at the nose, it is necessary to know the heat flux data in dependence of the time-dependent flow conditions. Therefore, great interest is focused on heat flux data gained from ISL shock tunnel experiments. These were done for Mach number between 3.5 and 10 for flight altitude conditions ranging from sea level up to 60 km. On the nose surface of a blunt and a sharp cone heat fluxes were measured with special, fast-reacting thin film temperature gauges. The results are compared with theoretical calculations based on the classical boundary layer theory for the laminar as well as for the turbulent boundary layer formation at a conical missile nose. Best agreement exists between the heat fluxes measured and the analytical solutions for a sharp cone.


Heat Flux Mach Number Heat Flux Density Flight Altitude Shock Tunnel 
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  1. 1.
    Schlichting, H.: Boundary-Layer Theory. McGraw-Hill, New York (1960)zbMATHGoogle Scholar
  2. 2.
    Seiler, F., Werner, U., Patz, G.: Theoretical and experimental modelling of real Projectile Flight Heating. J. of Sp. and Rockets 38(4), 497–503 (2001)CrossRefGoogle Scholar
  3. 3.
    Srulijes, J., Seiler, F.: Analytically obtained data compared with shock tunnel heat flux measurements at a conical body at M = 6". ISL-report PU 662/2004 (2004)Google Scholar
  4. 4.
  5. 5.
    Oertel, H.: Stoßrohre. Springer, Wien-New York (1966)Google Scholar
  6. 6.
    Oertel, H.: Wärmeübergangsmessungen. In: Kurzzeitphysik. Springer, Wien-New York (1967)Google Scholar
  7. 7.
    Schneider, S.P.: Hypersonic Laminar-Turbulent Transition on Circular Cones and Scramjet Forebodies. Aerospace Sciences 40(1-2), 1–50 (2004)CrossRefGoogle Scholar
  8. 8.
    Seiler, F., Peter, H., Zettler, G., Mathieu, G.: Heat transfer behaviour in gun tubes. In: 22nd International Symposium Innenballistik der Rohrwaffen, BAKWVT Mannheim, Mannheim, ISL-report PU 631/2001 (2001)Google Scholar
  9. 9.
    Seiler, F., Gnemmi, P., Ende, H., Havermann, M., Schwenzer, M.: Study on lateral jet/cross flow interaction in the high energy ISL shock tunnel. In: 23rd Int. Symp. On Shock Waves, Forth-Worth, Texas, USA, ISL-Report PU 628/2001, July 22-27 (2001)Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2010

Authors and Affiliations

  • J. Srulijes
    • 1
  • F. Seiler
    • 1
  • P. Hennig
    • 2
  • P. Gleich
    • 2
  1. 1.French-German Research Institute of Saint-Louis (ISL)Saint-LouisFrance
  2. 2.LFK-Lenkflugkörpersysteme GmbHUnterschleißheimGermany

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