the problem of CL in computing airplane
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 ?
Re: the problem of CL in computing airplane
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.
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