S1223 (s1223-il)
S1223 - Selig S1223 high lift low Reynolds number airfoil
| Details | Dat file | Parser | |
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(s1223-il) S1223 Selig S1223 high lift low Reynolds number airfoil Max thickness 12.1% at 19.8% chord. Max camber 8.1% at 49% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S1223 1.00000 0.00000 0.99838 0.00126 0.99417 0.00494 0.98825 0.01037 0.98075 0.01646 0.97111 0.02250 0.95884 0.02853 0.94389 0.03476 0.92639 0.04116 0.90641 0.04768 0.88406 0.05427 0.85947 0.06089 0.83277 0.06749 0.80412 0.07402 0.77369 0.08044 0.74166 0.08671 0.70823 0.09277 0.67360 0.09859 0.63798 0.10412 0.60158 0.10935 0.56465 0.11425 0.52744 0.11881 0.49025 0.12303 0.45340 0.12683 0.41721 0.13011 0.38193 0.13271 0.34777 0.13447 0.31488 0.13526 0.28347 0.13505 0.25370 0.13346 0.22541 0.13037 0.19846 0.12594 0.17286 0.12026 0.14863 0.11355 0.12591 0.10598 0.10482 0.09770 0.08545 0.08879 0.06789 0.07940 0.05223 0.06965 0.03855 0.05968 0.02694 0.04966 0.01755 0.03961 0.01028 0.02954 0.00495 0.01969 0.00155 0.01033 0.00005 0.00178 0.00044 -0.00561 0.00264 -0.01120 0.00789 -0.01427 0.01718 -0.01550 0.03006 -0.01584 0.04627 -0.01532 0.06561 -0.01404 0.08787 -0.01202 0.11282 -0.00925 0.14020 -0.00563 0.17006 -0.00075 0.20278 0.00535 0.23840 0.01213 0.27673 0.01928 0.31750 0.02652 0.36044 0.03358 0.40519 0.04021 0.45139 0.04618 0.49860 0.05129 0.54639 0.05534 0.59428 0.05820 0.64176 0.05976 0.68832 0.05994 0.73344 0.05872 0.77660 0.05612 0.81729 0.05219 0.85500 0.04706 0.88928 0.04088 0.91966 0.03387 0.94573 0.02624 0.96693 0.01822 0.98255 0.01060 0.99268 0.00468 0.99825 0.00115 1.00000 0.00000 |
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Polars for S1223 (s1223-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s1223-il | 50,000 | 9 | 33.1 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223-il | 50,000 | 5 | 42.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223-il | 100,000 | 9 | 54.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223-il | 100,000 | 5 | 59.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223-il | 200,000 | 9 | 73.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223-il | 200,000 | 5 | 75.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223-il | 500,000 | 9 | 98.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223-il | 500,000 | 5 | 97.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223-il | 1,000,000 | 9 | 121.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223-il | 1,000,000 | 5 | 120 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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