Abstract
A new six-component accelerometer force balance is developed and used in the HST2 shock tunnel of Indian Institute of Science. Aerodynamic forces and moments for a hypersonic slender body measured using this balance system at a free stream Mach number of 5.75 and Reynolds number of 1.5 million and stagnation enthalpy of 1.5 and 2 MJ/kg are presented. These measured values compare well with the theoretical values estimated using modified Newtonian theory.
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References
N.M. Reddy: Development of a three componenet balance for use in s shock tunnel. High Enthalpy Aerodynamics, Report No 85 HEA2 (1985)
Niranjan Sahoo, D.R. Mahapatra, G. Jagadesh, S. Gopalakrishnan and K.P.J. Reddy: An accelerometer aubalance system for measurement of aerodynamic force co-efficients over blunt bodies in hypersonic shock tunnel. Measurement Science and Technology 14, 260 (2003)
R.W. Truitt: Hypersonic aerodynamics. (Ronald, New York, 1959)
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© 2005 Tsinghua University Press and Springer-Verlag Berlin Heidelberg
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Saravanan, S., Jagadeesh, G., Reddy, K.P.J. (2005). A new 6-component accelerometer force balance for short duration ground testing facilities. In: Jiang, Z. (eds) Shock Waves. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-27009-6_53
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DOI: https://doi.org/10.1007/978-3-540-27009-6_53
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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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