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Shock Waves pp 203-208 | Cite as

Force and moment measurements on the HOPPER configuration for high enthalpy conditions

  • C. Glößner
  • H. Olivier
Conference paper

Abstract

TH2-D is a high enthalpy hypersonic wind tunnel, for this test campaign driven by an upstream detonation driver [1]. An oxyhydrogen detonation in the high pressure section generates a shock wave in the low pressure section, compressing and heating the synthetic air used as test gas. Varying the filling pressures in both sections and/or diluting the stoichiometric oxyhydrogen with different percentages of helium or argon yields different test conditions. Table 1 shows the test conditions employed corresponding to two points of the HOPPER re-entry trajectory [2]. Figure 1 illustrates reservoir and pitot pressure (p0, pt2) as well as the stagnation point heat flux \( \dot q_{t2} \), as a measure for the stagnation enthalpy. The nozzle flow is protected from water vapour contamination after the testing time by a fast acting center plug valve. The conical nozzle with a half apex angle of 5.8° is followed by the test section with a usable length of about 400 mm and a core flow diameter of 400 mm.
Table 1.

Conditions for the aerothermodynamic testing of the HOPPER-configuration

Fig. 1.

Stagnation point heat flux and reservoir and pitot pressure for conds. D-III and D-IV

Keywords

Pitching Moment Shock Tunnel Pitot Pressure Stagnation Enthalpy Pitching Moment Coefficient 
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

© Tsinghua University Press and Springer-Verlag Berlin Heidelberg 2005

Authors and Affiliations

  • C. Glößner
    • 1
  • H. Olivier
    • 1
  1. 1.Shock Wave LabRWTH Aachen UniversityAachenGermany

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