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Experimental Investigation and Numerical Simulation on a Missile Radome at Mach 6

  • Carl Dankert
  • Hannes Otto
Part of the Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM) book series (NNFM, volume 96)

Abstract

The aerodynamic loads for a missile radome cruising near ground level are investigated. The investigation consists of experiments at Mach 6 performed in the High Enthalpy Shock Tunnel Göttingen (HEG) and CFD calculations using the TAU code of DLR. The first approach duplicated an hypersonic flight at 11 km altitude for some milliseconds with the appropriate Mach number, Re number, flow velocity, pressure and heat load. The experimental results for the heat transfer on the radome fit to the CFD data including the transition from laminar to turbulent.

Keywords

Heat Transfer Mach Number Heat Transfer Rate Shock Tube Wall Pressure 
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.

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Copyright information

© Springer-Verlag Berlin Heidelberg 2007

Authors and Affiliations

  • Carl Dankert
    • 1
  • Hannes Otto
    • 2
  1. 1.Institute of Aerodynamics and Flow TechnologyGerman Aerospace Center DLRGöttingenGermany
  2. 2.Institute of Aerodynamics and Flow TechnologyGerman Aerospace Center DLRBraunschweigGermany

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