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Robert,
<br>You're a Hoot!
<br>BTW, I think you're doing a fantastic job as District VP!
<p>RUDDERCABL@aol.com wrote:
<blockquote TYPE=CITE> In a message dated 4/14/2004 7:26:42 PM Eastern
Standard Time, jbudd@QNET.COM writes:
<blockquote style="PADDING-LEFT: 5px; MARGIN-LEFT: 5px; BORDER-LEFT: blue 2px solid">
<br><font face="Arial">A wing is stalled when the lift curve slope changes
sign, meaning</font>
<br><font face="Arial">that a further increase in angle of attack (AOA)
results in a</font>
<br><font face="Arial">reduction in lift, due to increased separation of
the airflow</font>
<br><font face="Arial">disrupting the pressure distribution over the top
of the wing. The</font>
<br><font face="Arial">AOA (also refered to as "alpha" in the flight test
world) at which</font>
<br><font face="Arial">the lift curve slope changes from positive to negative
is where the</font>
<br><font face="Arial">maximum lift coefficient (CL-max) of the wing (or
vehicle) is reached</font>
<br><font face="Arial">and is typically found to occur around 18 to 30
degrees alpha. It's</font>
<br><font face="Arial">a function of a whole lot of things like aspect
ratio, planform,</font>
<br><font face="Arial">control surface deflection, Reynolds #, Mach#, etc.
It is NOT a</font>
<br><font face="Arial">function of airspeed.</font>
<p><font face="Arial">But I digress...</font></blockquote>
WOW Buddman! That was great! Can you give it to me in redneck? Your
redneck palRobert</blockquote>
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