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 Need Help With CL For Concord
 Air Taiwan From Australia, joined Dec 1999, 1519 posts, RR: 4Posted Tue Apr 16 2002 14:34:55 UTC (12 years 11 months 2 weeks 4 days 21 hours ago) and read 2997 times:

 Hi everyone, I'm doing this project for uni (Aircraft Engineering) and we had to work out the Coefficient of Lift for the concord and some other aircraft. The figure I got for concord was 0.207 Is it too low?? Cuz even a cessna 172 has a CL of 0.369!! Can anyone help me?? Thank you very much!! Jimmy
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 Minuteman From United States of America, joined Aug 2000, 271 posts, RR: 0 Reply 1, posted Wed Apr 17 2002 03:08:00 UTC (12 years 11 months 2 weeks 4 days 8 hours ago) and read 2948 times:

 That seems reasonable that Concorde would have a lower CL than a Cessna (as long as its incompressible flow, i.e. takeoff/landing speeds). I believe a small CL is the reason for the relatively high speeds and angles of attack used by the plane. Consider a general equation for lift: L=(dynamic pressure, q)(CL)(AOA, alpha)(wing planform area, S) In most cases, S is a fixed value. Things that change this value can be Fowler flaps or variable geometry wings. For this case, we're also going to fix L, the lifting force. That leaves us with CL, alpha, and q. If CL, a constant, is small, then we have to increase alpha and/or q. On approach, Concorde will fly around 150% of the typical values of AOA and airspeed for a subsonic transport. This leads me to assume that the ship has a relatively small CL. Also, to develop lift with a delta wing (vortex lift), some AOA is always necessary. Otherwise, you'll likely have equal pressures on the top and bottom of the wing as there's not much camber to cause circulation. Hope that helps. (OK experts, I gave you the target, fire away.)
 Air Taiwan From Australia, joined Dec 1999, 1519 posts, RR: 4 Reply 2, posted Sun Apr 21 2002 13:50:44 UTC (12 years 11 months 1 week 6 days 22 hours ago) and read 2903 times:

 Thank you very much for the reply, Minuteman! Appreciated it! cheers! Jimmy
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