Aerodynamic force measurements over missile configurations in IISc shock tunnel at M∞ =3.85 and 9.15
Three most commonly used missile configurations are tested in a shock tunnel, and a new set of aerodynamic data is obtained at M∞ = 3.85 and 9.15 by using an accelerometer balance system. The agreement between theory and experiment is generally good for all the cases. Noticeable decreases in measured CLand Cmvalues are obtained at M∞=9.15, compared to those at M∞ = 3.85. The dependence of CDon M∞ seems to be insignificant.
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