Air Taiwan
Topic Author
Posts: 1498
Joined: Fri Dec 03, 1999 3:06 pm

Need Help With CL For Concord

Tue Apr 16, 2002 9:34 pm

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
 
Minuteman
Posts: 260
Joined: Sat Aug 05, 2000 1:01 am

RE: Need Help With CL For Concord

Wed Apr 17, 2002 10:08 am

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
Topic Author
Posts: 1498
Joined: Fri Dec 03, 1999 3:06 pm

RE: Need Help With CL For Concord

Sun Apr 21, 2002 8:50 pm

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

cheers!

Jimmy

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