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Shock Waves pp 329-334 | Cite as

Ground testing of the HyShot supersonic combustion flight experiment in HEG

  • A. D. Gardner
  • K. Hannemann
  • A. Paull
  • J. Steelant
Conference paper

Abstract

The first phase of the HyShot supersonic combustion ramjet (scramjet) flight exper- iment program of The University of Queensland in Australia was designed to provide benchmark data on supersonic combustion for a flight Mach number of approximately M=8. The second flight of the HyShot program, performed on July 30th 2002, was successful and supersonic com- bustion was observed along the specified trajectory range. The operating range of the High Enthalpy Shock Tunnel Göttingen (HEG) of the German Aerospace Centre (DLR) was recently extended. The facility has now the capability of testing a complete scramjet engine with internal combustion and external aerodynamics at M=7.8 flight conditions in altitudes of about 30 km. A post flight analysis of the HyShot flight experiment was performed using an operational scramjet wind tunnel model with a geometry which is identical to that of the flight configuration.

Keywords

Combustion Chamber Equivalence Ratio Turbulent Heat Flux Flight Altitude Flight Data 
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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References

  1. 1.
    A.D. Gardner, RA. Jacobs, K. Hannemann: ‘End-to-End Modelling and Design of a New Operating Condition for HEG’. In: New Results in Numerical and Experimental Fluid Mechanics IV, 87, (Springer, 2004)Google Scholar
  2. 2.
    K. Hannemann, M. Schnieder, B. Reimann, J. Martinez Schramm: The influence and the delay of driver gas contamination in HEG. In: 21st AIAA Aerodynamic Measurement Technology and Ground Testing Conference, Denver, 19–22 June, 2000, AIAA 2000–2595Google Scholar
  3. 3.
    K. Hannemann: High enthalpy flows in the HEG shock tunnel: experiment and numerical rebuilding. In: 41st AIAA Aerospace Sciences Meeting and Exhibit, Reno, 6–9 January, 2003, AIAA 2003-0978Google Scholar
  4. 4.
    R.H. Korkegi: Comparison of shock-induced two-and three-dimensional incipient turbulent separation. AIAA journal 13(4), 534 (1975)ADSCrossRefGoogle Scholar
  5. 5.
    A. Pauli, H. Alesi, S. Anderson: The HyShot flight program and how it was developed. In: AIAA/A A AF 11th International Space Planes and Hypersonic Systems and Technologies Conference, Orléans, France, 29 September–4 October, 2002, AIAA 2002-4939Google Scholar

Copyright information

© Tsinghua University Press and Springer-Verlag Berlin Heidelberg 2005

Authors and Affiliations

  • A. D. Gardner
    • 1
  • K. Hannemann
    • 1
  • A. Paull
    • 2
  • J. Steelant
    • 3
  1. 1.German Aerospace CenterDLRGöttingenGermany
  2. 2.The University of QueenslandBrisbaneAustralia
  3. 3.European Space & Technology CentreESTECNoordwijkThe Netherlands

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