the problem of CL in computing airplane

July 12, 2005, 11:16

when i was computing the CL from actack angle = 5 to 15 degree, i use sst model , when actack angle =5 degree , CL=0.8 but wind tunnel' value is 0.5, why so large difficence ? but when actack angle =15 degree, they are according well. would you tell me why it does so ?

July 12, 2005, 19:39

Hi,

On the CFX Community site there are a number of papers describing studies using CFX of aerofoil modelling. Alternately have a look in your library. Have a look at these papers and see how they do it.

Glenn Horrocks

July 12, 2005, 11:16	the problem of CL in computing airplane	#1
zuozicheng Guest Posts: n/a	when i was computing the CL from actack angle = 5 to 15 degree, i use sst model , when actack angle =5 degree , CL=0.8 but wind tunnel' value is 0.5, why so large difficence ? but when actack angle =15 degree, they are according well. would you tell me why it does so ?

July 12, 2005, 19:39	Re: the problem of CL in computing airplane	#2
Glenn Horrocks Guest Posts: n/a	Hi, On the CFX Community site there are a number of papers describing studies using CFX of aerofoil modelling. Alternately have a look in your library. Have a look at these papers and see how they do it. Glenn Horrocks

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