Snaps

[RUDDERCABL at aol.com]

In a message dated 4/14/2004 7:26:42 PM Eastern Standard Time, jbudd at QNET.COM 
writes:

A wing is stalled when the lift curve slope changes sign, meaning 
that a further increase in angle of attack (AOA) results in a 
reduction in lift, due to increased separation of the airflow 
disrupting the pressure distribution over the top of the wing.  The 
AOA (also refered to as "alpha" in the flight test world) at which 
the lift curve slope changes from positive to negative is where the 
maximum lift coefficient (CL-max) of the wing (or vehicle) is reached 
and is typically found to occur around 18 to 30 degrees alpha.  It's 
a function of a whole lot of things like aspect ratio, planform, 
control surface deflection, Reynolds #, Mach#, etc.  It is NOT a 
function of airspeed.

But I digress...
WOW Buddman! That was great! Can you give it to me in redneck?

Your redneck pal
Robert
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