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<DIV>In a message dated 4/14/2004 6:33:46 PM Central Daylight Time, jbudd@QNET.COM writes:</DIV>
<BLOCKQUOTE style="PADDING-LEFT: 5px; MARGIN-LEFT: 5px; BORDER-LEFT: blue 2px solid"><FONT face=Arial>Not quite.<BR><BR>A wing is stalled when the lift curve slope changes sign, meaning <BR>that a further increase in angle of attack (AOA) results in a <BR>reduction in lift, due to increased separation of the airflow <BR>disrupting the pressure distribution over the top of the wing. The <BR>AOA (also refered to as "alpha" in the flight test world) at which <BR>the lift curve slope changes from positive to negative is where the <BR>maximum lift coefficient (CL-max) of the wing (or vehicle) is reached <BR>and is typically found to occur around 18 to 30 degrees alpha. It's <BR>a function of a whole lot of things like aspect ratio, planform, <BR>control surface deflection, Reynolds #, Mach#, etc. It is NOT a <BR>function of airspeed.<BR><BR>But I digress...<BR><BR>Jerry</FONT></BLOCKQUOTE></DIV>
<DIV>is it getting warm in here or it just me?</DIV>
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<DIV>D</DIV></BODY></HTML>