<table cellspacing="0" cellpadding="6" border="0" align="center" id="post5022434" class="tborder" style="width: 1028px; height: 121px;"> <tbody> <tr valign="top"> <td class="alt1" id="td_post_5022434" style="border-right: 1px solid rgb(0, 0, 99);"> <div id="post_message_5022434">Hello,

I've been repeating some basics and I'm stuck. As far as I remember, the maximum AOA allowance for a given wing, has been defined with its chord length. That goes for either highly swept wings like Mirage delta, or straight ones like the Spitfire's, so it isn't directly related to high-sweep leading edge vortex or aspect ratio.
IIRC, it had something to do with movement of center of pressure (cp) along the chord line. So, again IIRC, the stall occurs (in 2D sense) when the cp departs the wing's area. Longer chorded wings have this travel space larger than short chorded, hence larger AoA limit for them.
Can anyone verify that? and if I'm all wrong, please post a link or answer with correct explanation.
Thx.</div> <! / message ></td> </tr> <tr> <td class="alt2" style="border-style: none solid solid; border-color: -moz-use-text-color rgb(0, 0, 99) rgb(0, 0, 99); border-width: 0px 1px 1px;"> <! start pprune code 'bft' > <! end pprune code 'bft' ></td> <td align="right" class="alt1" style="border-style: none solid solid none; border-color: -moz-use-text-color rgb(0, 0, 99) rgb(0, 0, 99) -moz-use-text-color; border-width: 0px 1px 1px 0px;"><! controls > </td> </tr> </tbody></table>