Abstract
A generic flight vehicle configuration has been designed as a possible candidate for hypersonic flight. Aerodynamic force coefficients over the test model configuration for different angles of attack are measured using a three-component accelerometer force balance system. Experiments are conducted in HST2 shock tunnel facility of IISc at an enthalpy of 2 MJ/kg and nominal Mach number of 6. This data will be useful for validating numerical results obtained by CFD techniques.
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© 2005 Tsinghua University Press and Springer-Verlag Berlin Heidelberg
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Sarwade, A.G. et al. (2005). Aerodynamic characteristics of generic flight vehicle configuration from shock tunnel tests. In: Jiang, Z. (eds) Shock Waves. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-27009-6_18
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DOI: https://doi.org/10.1007/978-3-540-27009-6_18
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Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-540-22497-6
Online ISBN: 978-3-540-27009-6
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