I hope there are some people around here with some experience in Xrotor than me. (Xrotor is:"XROTOR is an interactive program for the design and analysis of ducted and free-tip propellers and windmills." Found: here documentation is at the end of the site) For the Blade Section Properties, I need following:
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1) Zero-lift alpha (deg): 0.00 7) Minimum Cd : 0.0070
2) d(Cl)/d(alpha) : 6.280 8) Cl at minimum Cd : 0.150
3) d(Cl)/d(alpha)@stall : 0.100 9) d(Cd)/d(Cl**2) : 0.0040
4) Maximum Cl : 2.00 10) Reference Re number : 2000000.
5) Minimum Cl : -1.50 11) Re scaling exponent : -0.2000
6) Cl increment to stall: 0.200 12) Cm : -0.100
13) Mcrit : 0.620
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Now does anyone know how 3) d(Cl)/d(alpha)@stall and 6) Cl increment to stall is defined?
If I had to guess 3) is just the slop after Maximum Cl. But 6) which is also mentioned in the doc as "delta CL for the stall transition region" gives me some headache.
Any help is appreciated.
Cheers