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   Computes lift and drag coefficients for a vehicle using simple formulas. 
   You will have to call this routine for the wing, fuselage and tail
   separately using different characteristic lengths. The wing and tail use
   the mean chord and the fuselage uses the length. cL is the optimal.
   Altitude and velocity must be the same length.
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   Form:
   y = LiftAndDrag( d, altitude, velocity )
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   Inputs
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   d              (1,1)  Aircraft parameters
                         .length      (1,1) Representative length (e.g. mean chord) (m)
                         .oswaldEff   (1,1) Oswald efficiency factor (0.9 to 1.0)
                         .aspectRatio (1,1) Aspect ratio for wing
                         .thickness   (1,1) Ratio of length to thickness
                         .s           (1,1) Area
   altitude       (1,n)  Altitude (m)
   velocity       (1,n)  Velocity at altitude (m/sec)

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   Outputs
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   y              (1,1)  Output data structure
                         .reynoldsNumber (1,n)
                         .skinFriction   (1,n)
                         .formDrag       (1,n)
                         .kInduced       (1,n)
                         .parasiticDrag  (1,n)
                         .cD0            (1,n)
                         .cL             (1,n) Optimal lift coefficient.
                         .lift           (1,n) Lift
                         .drag           (1,n) Drag
                         .loading        (1,n) Wing loading

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