Re: Aircraft speed and weight at cruise.

Date:         20 Nov 97 02:53:43 
From:         Simon Ellwood <>
Organization: Bodge It & Co. Ltd.
References:   1 2 3
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>The statement "A wing generates a lift value which is proportional to the
>air speed" is completely right.  since:
>    L=1/2*pho*V^2*S*CL_alpha * alpha
>        L is lift, pho is density, V is speed, S is area, CL_alpha is
>        lift curve slope, and alpha is angle of attack
>    L is proportional to air speed is a completely right statement
>    L is also proportional to density, wing area, and lift curve slope

Since when has a "squared" relationship been proportional ?
I'm suprised an aerospace engineer fell into that hole.
Perhaps it's language here.

Simon Ellwood