S1221 w/ 4 deg flap (s1221-flap-il)
S1221 w/ 4 deg flap - Selig S1221 airfoil with 4 deg flap
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(s1221-flap-il) S1221 w/ 4 deg flap Selig S1221 airfoil with 4 deg flap Max thickness 12.1% at 21.8% chord. Max camber 5.3% at 52.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S1221 w/ 4 deg flap 0.99927 -0.00338 0.99761 -0.00254 0.99306 0.00001 0.98626 0.00377 0.97730 0.00799 0.96571 0.01227 0.95129 0.01679 0.94627 0.01824 0.87364 0.03696 0.83704 0.04523 0.82224 0.04831 0.80740 0.05112 0.79250 0.05360 0.77754 0.05572 0.72514 0.06224 0.65074 0.07145 0.64181 0.07259 0.60456 0.07717 0.56677 0.08157 0.52865 0.08577 0.49051 0.08975 0.45264 0.09349 0.41537 0.09693 0.37902 0.09992 0.34385 0.10232 0.31005 0.10396 0.27776 0.10469 0.24715 0.10447 0.21836 0.10298 0.19125 0.10011 0.16569 0.09601 0.14166 0.09077 0.11918 0.08461 0.09838 0.07771 0.07937 0.07022 0.06223 0.06222 0.04705 0.05386 0.03388 0.04528 0.02281 0.03663 0.01391 0.02808 0.00733 0.01969 0.00297 0.01152 0.00065 0.00384 0.00037 -0.00287 0.00271 -0.00774 0.00859 -0.01117 0.01809 -0.01422 0.03068 -0.01687 0.04619 -0.01909 0.06442 -0.02087 0.08523 -0.02216 0.10841 -0.02290 0.13379 -0.02304 0.16116 -0.02248 0.19026 -0.02101 0.22124 -0.01813 0.25456 -0.01393 0.29025 -0.00894 0.32811 -0.00346 0.36788 0.00227 0.40929 0.00801 0.45202 0.01360 0.49574 0.01880 0.54006 0.02346 0.58459 0.02742 0.62895 0.03058 0.65126 0.03183 0.72628 0.03528 0.77128 0.03648 0.78630 0.03650 0.80131 0.03610 0.81631 0.03527 0.83128 0.03399 0.87548 0.02860 0.94938 0.01434 0.96794 0.00915 0.98244 0.00397 0.99211 -0.00014 0.99753 -0.00259 0.99925 -0.00338 |
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Polars for S1221 w/ 4 deg flap (s1221-flap-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s1221-flap-il | 50,000 | 9 | 31 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 50,000 | 5 | 39.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 100,000 | 9 | 48.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 100,000 | 5 | 56.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 200,000 | 9 | 69.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 200,000 | 5 | 76.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 500,000 | 9 | 104.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 500,000 | 5 | 106.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 1,000,000 | 9 | 133.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 1,000,000 | 5 | 129.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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