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Measuring the Effect of Nose Bluntness on Drag of a Cone in a Hypervelocity Shock Tunnel Facility

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Shock Waves @ Marseille I

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Abstract

Presented in this paper are results obtained from an investigation into the effects of nose bluntness on slender cone drag in the hypersonic (M > 5) and hypervelocity (flight speed & 5 km/s) regime. Experiments were performed in a free-piston driver shock tunnel facility. Drag measurements were made using the de convolution force balance (Sanderson and Simmons 1991) for measuring drag in hypervelocity impulse facilities where test times may be of the order of 1 ms. Experiments were performed on a 5° semi-vertex angle cone with varying degrees of nose bluntness. Results are presented here for drag measurements made in air as test gas at stagnation enthalpies of 3.3 and 14.4 MJ/kg.

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References

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Author information

Authors and Affiliations

  1. University of Queensland, 4072, St. Lucia, Queensland, Australia

    L. M. Porter, A. Paull & D. J. Mee

Authors
  1. L. M. Porter
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  2. A. Paull
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  3. D. J. Mee
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Editor information

Editors and Affiliations

  1. Centre Saint-Jérôme, Université de Provence, Case 321, F-13397, Marseille Cedex 20, France

    Raymond Brun  & Lucien Z. Dumitrescu  & 

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© 1995 Springer-Verlag Berlin Heidelberg

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Porter, L.M., Paull, A., Mee, D.J. (1995). Measuring the Effect of Nose Bluntness on Drag of a Cone in a Hypervelocity Shock Tunnel Facility. In: Brun, R., Dumitrescu, L.Z. (eds) Shock Waves @ Marseille I. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-78829-1_7

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  • DOI: https://doi.org/10.1007/978-3-642-78829-1_7

  • Publisher Name: Springer, Berlin, Heidelberg

  • Print ISBN: 978-3-642-78831-4

  • Online ISBN: 978-3-642-78829-1

  • eBook Packages: Springer Book Archive

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