S1223 RTL (s1223rtl-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1223 RTL (s1223rtl-il) Reynolds number: 100,000 Max Cl/Cd: 43.28 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1223rtl-il-100000.txt Download as CSV file: xf-s1223rtl-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S1223 RTL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.250 -0.0573 0.11230 0.10845 -0.0444 0.9532 0.0711
-6.000 -0.0453 0.10994 0.10611 -0.0491 0.9428 0.0742
-5.750 -0.0544 0.11023 0.10645 -0.0537 0.9304 0.0751
-5.500 -0.0061 0.10209 0.09832 -0.0556 0.9216 0.0774
-5.250 0.0200 0.09812 0.09437 -0.0586 0.9102 0.0822
-5.000 0.0214 0.09666 0.09295 -0.0619 0.8955 0.0854
-4.750 0.0520 0.09111 0.08743 -0.0656 0.8842 0.0888
-4.500 0.0818 0.08673 0.08307 -0.0682 0.8687 0.0942
-4.250 0.0942 0.08430 0.08068 -0.0819 0.8432 0.0994
-4.000 0.1156 0.07879 0.07519 -0.0744 0.8208 0.1019
-3.750 0.1352 0.07518 0.07155 -0.0736 0.7733 0.1063
-3.500 0.2180 0.06700 0.06274 -0.0908 0.6658 0.1179
-3.250 0.2809 0.06232 0.05716 -0.1070 0.5814 0.1309
-3.000 0.3085 0.06017 0.05462 -0.1068 0.5514 0.1373
-2.750 0.3501 0.05694 0.05111 -0.1164 0.5332 0.1492
-2.500 0.3974 0.05410 0.04797 -0.1254 0.5188 0.1658
-2.250 0.7359 0.02786 0.01884 -0.2219 0.4922 0.0855
-2.000 0.8060 0.02608 0.01630 -0.2314 0.4820 0.0885
-1.750 0.8525 0.02527 0.01523 -0.2352 0.4742 0.0928
-1.500 0.8968 0.02475 0.01446 -0.2385 0.4667 0.1025
-1.250 0.9428 0.02457 0.01407 -0.2421 0.4601 0.1175
-1.000 0.9825 0.02427 0.01393 -0.2445 0.4538 0.1507
-0.750 1.0250 0.02466 0.01478 -0.2472 0.4477 0.3299
-0.500 1.0531 0.02561 0.01561 -0.2467 0.4432 0.3821
-0.250 1.0806 0.02656 0.01651 -0.2461 0.4392 0.4206
0.000 1.1027 0.02711 0.01717 -0.2443 0.4353 0.4501
0.250 1.1313 0.02756 0.01757 -0.2443 0.4308 0.4753
0.500 1.1620 0.02797 0.01787 -0.2448 0.4264 0.4940
0.750 1.1952 0.02849 0.01821 -0.2458 0.4224 0.5124
1.000 1.2275 0.02914 0.01875 -0.2468 0.4189 0.5300
1.250 1.2549 0.02953 0.01922 -0.2467 0.4156 0.5473
1.500 1.2837 0.03001 0.01972 -0.2469 0.4122 0.5654
1.750 1.3129 0.03053 0.02024 -0.2472 0.4088 0.5857
2.000 1.3416 0.03106 0.02075 -0.2474 0.4055 0.6060
2.250 1.3716 0.03169 0.02131 -0.2479 0.4023 0.6279
2.500 1.4018 0.03263 0.02219 -0.2485 0.3993 0.6528
2.750 1.4247 0.03317 0.02288 -0.2476 0.3964 0.6772
3.000 1.4476 0.03380 0.02367 -0.2467 0.3937 0.7034
3.250 1.4711 0.03448 0.02446 -0.2460 0.3909 0.7345
3.500 1.4939 0.03511 0.02521 -0.2451 0.3884 0.7726
4.000 1.5348 0.03618 0.02646 -0.2425 0.3835 1.0000
4.250 1.5682 0.03748 0.02755 -0.2441 0.3808 1.0000
4.500 1.5914 0.03884 0.02895 -0.2438 0.3783 1.0000
4.750 1.6100 0.04007 0.03033 -0.2424 0.3758 1.0000
5.000 1.6285 0.04143 0.03184 -0.2411 0.3734 1.0000
5.250 1.6471 0.04283 0.03334 -0.2399 0.3711 1.0000
5.500 1.6662 0.04421 0.03479 -0.2387 0.3688 1.0000
5.750 1.6874 0.04545 0.03605 -0.2379 0.3664 1.0000
6.000 1.7119 0.04657 0.03712 -0.2375 0.3641 1.0000
6.250 1.7369 0.04786 0.03837 -0.2374 0.3619 1.0000
6.500 1.7588 0.04992 0.04041 -0.2370 0.3599 1.0000
6.750 1.7588 0.05212 0.04297 -0.2329 0.3581 1.0000
7.000 1.7568 0.05475 0.04592 -0.2288 0.3562 1.0000
7.250 1.7510 0.05776 0.04922 -0.2245 0.3543 1.0000
7.500 1.7399 0.06107 0.05284 -0.2196 0.3522 1.0000
7.750 1.7237 0.06464 0.05666 -0.2143 0.3500 1.0000
8.000 1.6942 0.06885 0.06113 -0.2076 0.3482 1.0000
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Polar data table (+)
Polar graphs
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