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.
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References
B. Bottin: ”Aerothermodynamic Model of an Inductively-Coupled Plasma Wind Tun-nel”, Dissertation, Université de Liège, 1999
H.K. Ciezki et al.: ”The DLR Research and Technology Project ”Hochagiler Flugkörper” (Missile of High Agility)”. Proceedings of the Innovative Missile Systems Symposium, RTO-MP-AVT-135, Paper 17, May 15–19 2006, Amsterdam, NL, pp 17–21, 17–17.
G. Eitelberg, T.J. Mclntyre, W.H. Beck:”The High Enthalpy Shock Tunnel in Göttingen”, AIAA paper, 92–3942, 1992. AIAA 17th Aerospace Ground Testing Con-ference.
T. Gerhold, O. Friedrichs, J. Evans, M. Galle: ”Calculation of Complex Three-Dimensional Configurations Employing the DLR-Tau-Code”, AIAA 97–0167, 1997
G. Koppenwallner: ”Fundamentals of Hypersonics: Aerodynamics and Heat Transfer”. In: Short Course Notes entitled Hypersonic Aerodynamics, Rhode Saint Genese, Bel-gium, 1984. Von Karman Institute for Fluid Dynamics.
A. Mack, V. Hannemann: ”Validation of the unstructured DLR-TAU-Code for Hyper-sonic Hows”, AIAA 2002–3111, 2002
C. Park: ”Review of Chemical-Kinetic Problems of Future NASA Missions”, I: Earth Entries. Journal of Thermophysics and Heat Transfer, No. 3, 385–398, 1993.
F. Seiler, J. Srulijes, M. Havermann, P. Hennig, P. Gleich:”Heat transfer measurements at the nose of a high speed Mach 6 missile.”, RTO AVT-135/RSY-020 Symposium on Innovative Missile Systems, 15–19 May 2006, Amsterdam, The Naval Barracs.
D.C. Wilcox: ”Turbulence Modeling for CFD”, DCW Industries, Inc., 1993.
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© 2007 Springer-Verlag Berlin Heidelberg
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Dankert, C., Otto, H. (2007). Experimental Investigation and Numerical Simulation on a Missile Radome at Mach 6. In: Tropea, C., Jakirlic, S., Heinemann, HJ., Henke, R., Hönlinger, H. (eds) New Results in Numerical and Experimental Fluid Mechanics VI. Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM), vol 96. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-74460-3_39
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DOI: https://doi.org/10.1007/978-3-540-74460-3_39
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-540-74458-0
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