S1221 w/o flap (s1221-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1221 w/o flap (s1221-il) Reynolds number: 200,000 Max Cl/Cd: 70.04 at α=11.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1221-il-200000.txt Download as CSV file: xf-s1221-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.2748 0.09532 0.09210 -0.0227 1.0000 0.0522
-6.750 -0.2920 0.09232 0.08920 -0.0255 1.0000 0.0543
-6.500 -0.3184 0.08980 0.08681 -0.0266 1.0000 0.0547
-6.250 -0.3138 0.08628 0.08335 -0.0244 1.0000 0.0555
-6.000 -0.2976 0.08466 0.08174 -0.0214 1.0000 0.0567
-5.750 -0.2974 0.08312 0.08027 -0.0192 1.0000 0.0579
-5.500 -0.3002 0.08134 0.07857 -0.0178 1.0000 0.0594
-5.250 -0.2793 0.06885 0.06612 -0.0446 0.9929 0.0656
-5.000 -0.2510 0.07003 0.06731 -0.0369 0.9884 0.0680
-4.750 -0.1977 0.05709 0.05431 -0.0662 0.9773 0.0783
-4.500 -0.1688 0.05665 0.05390 -0.0638 0.9676 0.0804
-4.250 -0.0391 0.02805 0.02334 -0.1204 0.9653 0.0566
-4.000 0.0264 0.02179 0.01599 -0.1283 0.9572 0.0375
-3.500 0.1217 0.01738 0.01107 -0.1356 0.9111 0.0362
-3.250 0.2090 0.01518 0.00858 -0.1467 0.8514 0.0377
-3.000 0.3131 0.01397 0.00671 -0.1621 0.7274 0.0439
-2.750 0.3466 0.01377 0.00611 -0.1631 0.6706 0.0474
-2.500 0.3792 0.01350 0.00554 -0.1641 0.6275 0.0562
-2.250 0.4195 0.01268 0.00519 -0.1674 0.5930 0.2904
-2.000 0.4466 0.01315 0.00543 -0.1669 0.5681 0.3176
-1.750 0.4731 0.01375 0.00592 -0.1662 0.5475 0.3496
-1.500 0.4997 0.01425 0.00631 -0.1655 0.5310 0.3727
-1.250 0.5277 0.01445 0.00634 -0.1653 0.5171 0.3835
-1.000 0.5567 0.01459 0.00630 -0.1653 0.5043 0.3917
-0.750 0.5858 0.01464 0.00623 -0.1653 0.4929 0.3979
-0.500 0.6146 0.01478 0.00622 -0.1653 0.4831 0.4038
-0.250 0.6441 0.01485 0.00616 -0.1655 0.4730 0.4103
0.000 0.6732 0.01496 0.00616 -0.1655 0.4650 0.4156
0.250 0.7022 0.01502 0.00619 -0.1656 0.4569 0.4214
0.750 0.7607 0.01528 0.00631 -0.1658 0.4434 0.4352
1.000 0.7899 0.01542 0.00636 -0.1659 0.4370 0.4433
1.250 0.8190 0.01559 0.00649 -0.1660 0.4313 0.4511
1.500 0.8481 0.01570 0.00662 -0.1661 0.4254 0.4612
1.750 0.8771 0.01584 0.00676 -0.1661 0.4204 0.4715
2.000 0.9064 0.01612 0.00697 -0.1663 0.4160 0.4846
2.250 0.9350 0.01621 0.00718 -0.1663 0.4110 0.4999
2.500 0.9639 0.01634 0.00738 -0.1663 0.4061 0.5175
2.750 0.9931 0.01654 0.00759 -0.1665 0.4020 0.5389
3.000 1.0225 0.01681 0.00792 -0.1667 0.3984 0.5661
3.250 1.0513 0.01692 0.00825 -0.1667 0.3943 0.6017
3.500 1.0796 0.01703 0.00857 -0.1667 0.3901 0.6540
3.750 1.1051 0.01713 0.00888 -0.1658 0.3865 0.7425
4.000 1.1236 0.01725 0.00914 -0.1634 0.3835 0.8494
4.250 1.1396 0.01727 0.00928 -0.1605 0.3806 1.0000
4.500 1.1687 0.01761 0.00965 -0.1608 0.3769 1.0000
4.750 1.1977 0.01796 0.00998 -0.1609 0.3733 1.0000
5.000 1.2266 0.01832 0.01029 -0.1611 0.3698 1.0000
5.250 1.2558 0.01883 0.01070 -0.1613 0.3666 1.0000
5.500 1.2834 0.01925 0.01120 -0.1613 0.3634 1.0000
5.750 1.3107 0.01962 0.01167 -0.1611 0.3597 1.0000
6.000 1.3384 0.01997 0.01205 -0.1610 0.3559 1.0000
6.250 1.3664 0.02035 0.01238 -0.1610 0.3526 1.0000
6.500 1.3947 0.02095 0.01292 -0.1611 0.3493 1.0000
6.750 1.4204 0.02130 0.01345 -0.1607 0.3453 1.0000
7.000 1.4467 0.02165 0.01389 -0.1604 0.3411 1.0000
7.250 1.4738 0.02196 0.01420 -0.1602 0.3372 1.0000
7.500 1.5020 0.02249 0.01462 -0.1603 0.3335 1.0000
7.750 1.5262 0.02285 0.01521 -0.1596 0.3291 1.0000
8.000 1.5516 0.02320 0.01567 -0.1591 0.3246 1.0000
8.250 1.5783 0.02348 0.01595 -0.1588 0.3206 1.0000
8.500 1.6055 0.02402 0.01642 -0.1588 0.3168 1.0000
8.750 1.6282 0.02435 0.01702 -0.1578 0.3116 1.0000
9.000 1.6531 0.02457 0.01730 -0.1573 0.3066 1.0000
9.250 1.6802 0.02482 0.01745 -0.1571 0.3019 1.0000
9.500 1.7016 0.02515 0.01804 -0.1560 0.2960 1.0000
9.750 1.7256 0.02525 0.01821 -0.1552 0.2900 1.0000
10.000 1.7501 0.02548 0.01840 -0.1547 0.2843 1.0000
10.250 1.7707 0.02565 0.01881 -0.1534 0.2772 1.0000
10.500 1.7943 0.02575 0.01888 -0.1526 0.2712 1.0000
10.750 1.8144 0.02607 0.01942 -0.1513 0.2640 1.0000
11.000 1.8357 0.02621 0.01963 -0.1502 0.2572 1.0000
11.250 1.8555 0.02655 0.02014 -0.1489 0.2495 1.0000
11.500 1.8751 0.02677 0.02044 -0.1475 0.2416 1.0000
11.750 1.8932 0.02717 0.02103 -0.1459 0.2320 1.0000
12.000 1.9101 0.02761 0.02154 -0.1443 0.2218 1.0000
12.250 1.9246 0.02819 0.02219 -0.1423 0.2103 1.0000
12.500 1.9363 0.02902 0.02306 -0.1400 0.1975 1.0000
12.750 1.9442 0.03011 0.02421 -0.1372 0.1837 1.0000
13.000 1.9452 0.03148 0.02562 -0.1335 0.1704 1.0000
13.250 1.9428 0.03317 0.02735 -0.1296 0.1579 1.0000
13.500 1.9373 0.03526 0.02948 -0.1258 0.1464 1.0000
13.750 1.9286 0.03778 0.03206 -0.1223 0.1366 1.0000
14.000 1.9140 0.04106 0.03536 -0.1191 0.1291 1.0000
14.250 1.9017 0.04461 0.03905 -0.1172 0.1214 1.0000
14.500 1.8821 0.04947 0.04396 -0.1163 0.1165 1.0000
14.750 1.8678 0.05446 0.04913 -0.1167 0.1106 1.0000
15.000 1.8472 0.06073 0.05547 -0.1180 0.1066 1.0000
15.250 1.8275 0.06725 0.06210 -0.1196 0.1026 1.0000
15.500 1.8104 0.07367 0.06868 -0.1215 0.0984 1.0000
15.750 1.7907 0.08054 0.07561 -0.1236 0.0950 1.0000
16.000 1.7737 0.08693 0.08202 -0.1254 0.0915 1.0000
16.250 1.7601 0.09312 0.08838 -0.1275 0.0881 1.0000
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Polar data table (+)
Polar graphs
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