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   Computes the stall velocity.
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   Form:
   vStall = VStall( d, altitude )
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   Inputs
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   d              (1,1)  
                         .cLMax      (1,1) Max lift coefficient
                         .wingArea   (1,1) Wing area
                         .massDesign (1,1) mass
   altitude       (1,1)  Altitude (m)

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   Outputs
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   vStall         (1,1)  Stall velocity

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