S1221 w/o flap (s1221-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1221 w/o flap (s1221-il) Reynolds number: 50,000 Max Cl/Cd: 36.59 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1221-il-50000-n5.txt Download as CSV file: xf-s1221-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2794 0.10797 0.10112 -0.0266 1.0000 0.0633
-7.250 -0.2720 0.10183 0.09515 -0.0268 1.0000 0.0603
-6.750 -0.2872 0.09408 0.08763 -0.0298 1.0000 0.0545
-6.500 -0.2876 0.09134 0.08500 -0.0292 1.0000 0.0542
-6.250 -0.2884 0.08879 0.08257 -0.0284 1.0000 0.0537
-6.000 -0.2914 0.08598 0.07988 -0.0281 1.0000 0.0532
-5.750 -0.2920 0.08292 0.07695 -0.0285 1.0000 0.0526
-5.500 -0.2927 0.07956 0.07371 -0.0295 1.0000 0.0518
-5.250 -0.2934 0.07563 0.06990 -0.0316 1.0000 0.0511
-5.000 -0.2924 0.07085 0.06524 -0.0353 1.0000 0.0500
-4.750 -0.2645 0.05160 0.04533 -0.0679 1.0000 0.0461
-4.500 -0.2304 0.04566 0.03898 -0.0776 1.0000 0.0459
-4.250 -0.1756 0.03977 0.03239 -0.0894 0.9963 0.0460
-4.000 -0.1144 0.03550 0.02761 -0.0992 0.9856 0.0469
-3.750 -0.0616 0.03263 0.02444 -0.1056 0.9689 0.0487
-3.500 -0.0117 0.03032 0.02178 -0.1107 0.9474 0.0525
-3.250 0.0352 0.02832 0.01954 -0.1146 0.9219 0.0565
-3.000 0.0801 0.02664 0.01775 -0.1177 0.8909 0.0608
-2.750 0.1312 0.02495 0.01592 -0.1221 0.8564 0.0692
-2.500 0.1994 0.02290 0.01375 -0.1301 0.8183 0.0931
-2.250 0.2836 0.02176 0.01319 -0.1415 0.7713 0.3098
-2.000 0.3244 0.02314 0.01430 -0.1420 0.7268 0.3799
-1.750 0.3578 0.02352 0.01428 -0.1419 0.6916 0.4044
-1.500 0.3908 0.02359 0.01393 -0.1425 0.6620 0.4191
-1.250 0.4244 0.02360 0.01350 -0.1435 0.6373 0.4315
-1.000 0.4558 0.02362 0.01320 -0.1440 0.6155 0.4419
-0.750 0.4872 0.02363 0.01292 -0.1446 0.5971 0.4506
-0.500 0.5196 0.02367 0.01265 -0.1454 0.5808 0.4603
-0.250 0.5503 0.02374 0.01249 -0.1458 0.5665 0.4686
0.000 0.5833 0.02384 0.01229 -0.1468 0.5535 0.4782
0.250 0.6135 0.02395 0.01228 -0.1472 0.5412 0.4869
0.500 0.6457 0.02411 0.01223 -0.1480 0.5306 0.4979
0.750 0.6765 0.02427 0.01225 -0.1484 0.5208 0.5085
1.000 0.7070 0.02445 0.01236 -0.1489 0.5111 0.5196
1.250 0.7379 0.02465 0.01243 -0.1494 0.5029 0.5333
1.500 0.7676 0.02489 0.01267 -0.1497 0.4945 0.5484
1.750 0.7972 0.02514 0.01287 -0.1500 0.4874 0.5650
2.000 0.8258 0.02541 0.01317 -0.1500 0.4804 0.5836
2.250 0.8535 0.02569 0.01352 -0.1499 0.4733 0.6060
2.500 0.8812 0.02596 0.01380 -0.1496 0.4678 0.6335
2.750 0.9057 0.02629 0.01434 -0.1489 0.4612 0.6664
3.000 0.9287 0.02656 0.01478 -0.1476 0.4557 0.7118
3.250 0.9489 0.02674 0.01504 -0.1457 0.4513 0.7783
3.500 0.9602 0.02678 0.01530 -0.1420 0.4464 0.9027
3.750 0.9917 0.02740 0.01588 -0.1431 0.4403 1.0000
4.000 1.0230 0.02806 0.01638 -0.1440 0.4355 1.0000
4.250 1.0522 0.02882 0.01708 -0.1445 0.4307 1.0000
4.500 1.0794 0.02966 0.01800 -0.1448 0.4252 1.0000
4.750 1.1075 0.03039 0.01869 -0.1450 0.4204 1.0000
5.000 1.1368 0.03107 0.01925 -0.1453 0.4165 1.0000
5.250 1.1607 0.03213 0.02047 -0.1451 0.4112 1.0000
5.500 1.1861 0.03307 0.02152 -0.1451 0.4064 1.0000
5.750 1.2130 0.03386 0.02230 -0.1450 0.4023 1.0000
6.000 1.2398 0.03470 0.02313 -0.1450 0.3985 1.0000
6.250 1.2604 0.03604 0.02474 -0.1445 0.3931 1.0000
6.500 1.2839 0.03712 0.02593 -0.1442 0.3887 1.0000
6.750 1.3101 0.03795 0.02678 -0.1440 0.3848 1.0000
7.000 1.3327 0.03912 0.02806 -0.1436 0.3806 1.0000
7.250 1.3499 0.04073 0.02997 -0.1427 0.3751 1.0000
7.500 1.3723 0.04186 0.03122 -0.1422 0.3706 1.0000
7.750 1.3990 0.04258 0.03194 -0.1420 0.3670 1.0000
8.000 1.4109 0.04464 0.03435 -0.1408 0.3611 1.0000
8.250 1.4273 0.04625 0.03617 -0.1398 0.3558 1.0000
8.500 1.4524 0.04698 0.03696 -0.1394 0.3516 1.0000
8.750 1.4650 0.04891 0.03912 -0.1381 0.3463 1.0000
9.000 1.4723 0.05124 0.04176 -0.1366 0.3402 1.0000
9.250 1.4969 0.05185 0.04244 -0.1360 0.3356 1.0000
9.500 1.5035 0.05418 0.04501 -0.1344 0.3300 1.0000
9.750 1.5007 0.05722 0.04834 -0.1323 0.3234 1.0000
10.000 1.5304 0.05716 0.04835 -0.1318 0.3189 1.0000
10.250 1.5024 0.06242 0.05396 -0.1286 0.3122 1.0000
10.500 1.4846 0.06640 0.05813 -0.1260 0.3061 1.0000
10.750 1.5449 0.06346 0.05522 -0.1265 0.3019 1.0000
11.000 1.3546 0.08847 0.08045 -0.1282 0.2886 1.0000
11.250 1.3987 0.08495 0.07707 -0.1249 0.2865 1.0000
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Polar data table (+)
Polar graphs
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