Path: ACPro/ACPerformance
% Computes drag coefficient increment due to the undercarriage.
Type DragUndercarriage for a demo.
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Form:
deltaCD = DragUndercarriage( m, s, f )
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Inputs
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m (1,1) Mass (m)
s (1,1) Reference area (m^2)
f (1,1) If entered the flaps are down
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Outputs
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deltaCD (1,1) Change in drag coefficient
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Reference: Mair, W. A. and D. L. Birdsall, "Aircraft Performance,"
Cambridge, p. 124.
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