Shock Tube Experiments on Heat Transfer at Generic Re-entry Bodies

  • J. Srulijes
  • R. Hruschka
  • F. Seiler
  • B. Sauerwein
  • M. Bastide-Luquet
  • K. J. Dahlem
Conference paper

Introduction

Since the beginning of space exploration, there has been a lot of research conducted on heat generation at high flight Mach numbers in the upper atmosphere. Currently areas of special interest are: aerodynamics/thermodynamics and flight mechanics of slender re-entry vehicles. Especially problems concerning heat phenomena, i.e. behaviour of ablative materials and their influence on the signature and flight trajectory are open questions. Accurate information on surface heating of slender vehicles during the re-entry phase in the upper atmosphere at hypersonic speeds is crucial for the validation of the computing codes. These are applied for calculating the aerothermodynamics and related problems numerically, which have considerable influence on the bodies’ navigation and control simulation. The ISL high-energy shock tunnels are ideal tools to provide for the generic re-entry body under investigation at high re-entry Mach numbers (M10, M12, M14) and several flight altitudes, ranging from 50 to 70 km, heat transfer values which are used to prove the numerics applied: Bird’s DS2V software [1].

Keywords

Mach Number Shock Tube Nozzle Exit Direct Simulation Monte Carlo Vibrational Temperature 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

Preview

Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.

References

  1. 1.
    Bird, G.A.: Molecular Gas Dynamics and the Direct Simulation of Gas Flows. Clarendon Press, Oxford (1994)Google Scholar
  2. 2.
    Oertel, H.: Wärmeübergangsmessungen. In: Kurzzeitphysik. Springer, Wien (1967)Google Scholar
  3. 3.
    O’Byrne, S., Danehy, P.M., Houwing, A.F.P.: Investigation of hypersonic nozzle flow uniformity using NO fluorescence. Shock Waves 15(2), 81–87 (2006)CrossRefGoogle Scholar
  4. 4.
    McIntosh, M.K.: Computer program for the numerical calculation of frozen and equilibrium conditions in shock tunnels. Tech. rep., Australian National University (1968)Google Scholar
  5. 5.
    Borgnakke, C., Larsen, P.S.: Statistical collision model for Monte Carlo simulation of polyatomic gas mixture. Journal of Computational Physics 18(4), 405–420 (1975)CrossRefGoogle Scholar
  6. 6.
    Stoßwellenlabor RWTH Aachen, Templergraben 55, D-52056 AachenGoogle Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2012

Authors and Affiliations

  • J. Srulijes
    • 1
  • R. Hruschka
    • 1
  • F. Seiler
    • 1
  • B. Sauerwein
    • 1
  • M. Bastide-Luquet
    • 1
  • K. J. Dahlem
    • 2
  1. 1.French-German Research Institute of Saint-Louis (ISL)Saint-LouisFrance
  2. 2.MBDA/LFK-Lenkflugkörpersysteme GmbHSchrobenhausenGermany

Personalised recommendations