S1221 w/o flap (s1221-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1221 w/o flap (s1221-il) Reynolds number: 100,000 Max Cl/Cd: 54.52 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1221-il-100000-n5.txt Download as CSV file: xf-s1221-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S1221 w/o flap
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2885 0.10652 0.10177 -0.0262 1.0000 0.0644
-7.500 -0.2945 0.10365 0.09899 -0.0280 1.0000 0.0648
-7.250 -0.2965 0.10067 0.09608 -0.0287 1.0000 0.0649
-6.750 -0.2947 0.08719 0.08263 -0.0285 1.0000 0.0323
-6.500 -0.2941 0.08497 0.08049 -0.0275 1.0000 0.0319
-6.250 -0.2976 0.08262 0.07823 -0.0265 1.0000 0.0314
-6.000 -0.3049 0.08002 0.07574 -0.0255 1.0000 0.0308
-5.500 -0.3034 0.05888 0.05461 -0.0490 0.9921 0.0270
-5.250 -0.2443 0.04318 0.03829 -0.0820 0.9814 0.0263
-5.000 -0.1811 0.03480 0.02904 -0.1001 0.9727 0.0260
-4.750 -0.1266 0.03020 0.02376 -0.1095 0.9616 0.0261
-4.500 -0.0784 0.02707 0.02009 -0.1154 0.9466 0.0266
-4.000 0.0046 0.02341 0.01600 -0.1220 0.8992 0.0298
-3.750 0.0553 0.02164 0.01396 -0.1263 0.8621 0.0313
-3.500 0.1343 0.01975 0.01175 -0.1359 0.8075 0.0331
-3.250 0.2084 0.01867 0.01018 -0.1450 0.7370 0.0364
-3.000 0.2541 0.01815 0.00923 -0.1488 0.6885 0.0414
-2.750 0.2938 0.01763 0.00841 -0.1515 0.6505 0.0501
-2.500 0.3358 0.01674 0.00739 -0.1549 0.6167 0.0832
-2.250 0.3754 0.01624 0.00732 -0.1581 0.5879 0.2735
-2.000 0.4057 0.01690 0.00785 -0.1582 0.5646 0.3293
-1.750 0.4347 0.01728 0.00805 -0.1580 0.5455 0.3529
-1.500 0.4648 0.01740 0.00792 -0.1582 0.5297 0.3644
-1.250 0.4945 0.01749 0.00779 -0.1583 0.5160 0.3729
-1.000 0.5241 0.01755 0.00763 -0.1585 0.5034 0.3800
-0.750 0.5532 0.01760 0.00755 -0.1585 0.4918 0.3863
-0.500 0.5829 0.01769 0.00742 -0.1587 0.4817 0.3929
-0.250 0.6118 0.01776 0.00739 -0.1587 0.4719 0.3986
0.000 0.6409 0.01787 0.00738 -0.1588 0.4638 0.4055
0.250 0.6703 0.01798 0.00736 -0.1589 0.4558 0.4125
0.500 0.6989 0.01812 0.00741 -0.1589 0.4491 0.4188
0.750 0.7281 0.01824 0.00747 -0.1590 0.4416 0.4271
1.000 0.7566 0.01839 0.00756 -0.1589 0.4351 0.4353
1.250 0.7857 0.01856 0.00767 -0.1590 0.4288 0.4456
1.500 0.8142 0.01871 0.00783 -0.1590 0.4226 0.4551
1.750 0.8428 0.01892 0.00797 -0.1590 0.4178 0.4661
2.000 0.8715 0.01913 0.00817 -0.1590 0.4127 0.4794
2.250 0.8998 0.01932 0.00840 -0.1589 0.4073 0.4942
2.500 0.9279 0.01953 0.00861 -0.1588 0.4025 0.5116
2.750 0.9561 0.01977 0.00885 -0.1588 0.3983 0.5316
3.000 0.9841 0.01998 0.00918 -0.1586 0.3935 0.5551
3.250 1.0119 0.02020 0.00951 -0.1585 0.3892 0.5840
3.500 1.0390 0.02042 0.00981 -0.1582 0.3853 0.6219
3.750 1.0645 0.02063 0.01015 -0.1574 0.3818 0.6747
4.000 1.0870 0.02077 0.01056 -0.1560 0.3775 0.7511
4.250 1.1052 0.02086 0.01083 -0.1536 0.3739 0.8396
4.500 1.1247 0.02096 0.01099 -0.1516 0.3707 1.0000
4.750 1.1539 0.02140 0.01133 -0.1519 0.3675 1.0000
5.000 1.1822 0.02186 0.01179 -0.1520 0.3639 1.0000
5.250 1.2100 0.02231 0.01232 -0.1521 0.3597 1.0000
5.500 1.2378 0.02278 0.01280 -0.1521 0.3561 1.0000
5.750 1.2656 0.02325 0.01326 -0.1521 0.3530 1.0000
6.000 1.2937 0.02373 0.01370 -0.1521 0.3501 1.0000
6.250 1.3200 0.02427 0.01437 -0.1519 0.3462 1.0000
6.500 1.3463 0.02480 0.01501 -0.1517 0.3422 1.0000
6.750 1.3728 0.02531 0.01559 -0.1515 0.3387 1.0000
7.000 1.3998 0.02579 0.01606 -0.1513 0.3354 1.0000
7.250 1.4261 0.02633 0.01664 -0.1511 0.3320 1.0000
7.500 1.4503 0.02695 0.01749 -0.1506 0.3276 1.0000
7.750 1.4754 0.02747 0.01812 -0.1502 0.3233 1.0000
8.000 1.5014 0.02793 0.01859 -0.1499 0.3196 1.0000
8.250 1.5265 0.02847 0.01921 -0.1494 0.3157 1.0000
8.500 1.5489 0.02912 0.02010 -0.1487 0.3104 1.0000
8.750 1.5730 0.02959 0.02067 -0.1481 0.3058 1.0000
9.000 1.5987 0.02997 0.02104 -0.1477 0.3019 1.0000
9.250 1.6194 0.03073 0.02208 -0.1467 0.2965 1.0000
9.500 1.6415 0.03129 0.02281 -0.1459 0.2913 1.0000
9.750 1.6658 0.03163 0.02317 -0.1453 0.2867 1.0000
10.000 1.6850 0.03236 0.02416 -0.1441 0.2807 1.0000
10.250 1.7054 0.03286 0.02482 -0.1430 0.2744 1.0000
10.500 1.7267 0.03321 0.02522 -0.1420 0.2687 1.0000
10.750 1.7430 0.03395 0.02628 -0.1404 0.2609 1.0000
11.000 1.7629 0.03422 0.02657 -0.1391 0.2546 1.0000
11.250 1.7765 0.03512 0.02780 -0.1373 0.2458 1.0000
11.500 1.7921 0.03565 0.02844 -0.1356 0.2380 1.0000
11.750 1.8043 0.03650 0.02952 -0.1335 0.2287 1.0000
12.000 1.8147 0.03745 0.03065 -0.1313 0.2194 1.0000
12.250 1.8225 0.03838 0.03166 -0.1288 0.2108 1.0000
12.500 1.8238 0.03977 0.03324 -0.1256 0.2014 1.0000
12.750 1.8229 0.04135 0.03495 -0.1224 0.1928 1.0000
13.000 1.8184 0.04329 0.03697 -0.1193 0.1843 1.0000
13.250 1.8109 0.04586 0.03972 -0.1166 0.1757 1.0000
13.500 1.7991 0.04903 0.04299 -0.1145 0.1688 1.0000
13.750 1.7831 0.05323 0.04736 -0.1136 0.1617 1.0000
14.250 1.7380 0.06542 0.05985 -0.1157 0.1512 1.0000
14.500 1.7099 0.07339 0.06796 -0.1185 0.1466 1.0000
14.750 1.6821 0.08162 0.07629 -0.1215 0.1422 1.0000
15.000 1.6533 0.09045 0.08530 -0.1250 0.1375 1.0000
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Polar data table (+)
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