Seaberg, Ernest C
A reevaluation of existing flight data obtained for a supersonic canard missile configuration of the boost-glide type has been made to determine derivatives not previously evaluated. These derivatives, together with those previously evaluated and published, have been utilized to determine some typical airframe frequency responses based on the three-degree-of-freedom longitudinal equations of motion. For constant flight conditions, it is shown that besides the usual drag-coefficient variation, the velocity derivatives also vary with angle of attack or Mach number. The effect of angle-of-attack variation on the missile frequency responses which include the velocity derivatives in their solution is appreciable only in the low-frequency region of operation (below 10 radians/sec). When the velocity derivatives are neglected, this low-frequency variation with angle of attack is different. Some of these differences are pointed out in the results to indicate the significance of including the velocity derivatives in the solution for the transfer functions.
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