SOKOLOV AIRFOIL (sokolov-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: SOKOLOV AIRFOIL (sokolov-il) Reynolds number: 500,000 Max Cl/Cd: 118.23 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sokolov-il-500000-n5.txt Download as CSV file: xf-sokolov-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SOKOLOV AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2182 0.08857 0.08635 -0.0500 0.9636 0.0068
-7.500 -0.2085 0.08522 0.08299 -0.0524 0.9515 0.0069
-7.250 -0.2005 0.08206 0.07982 -0.0543 0.9369 0.0071
-7.000 -0.1890 0.07850 0.07624 -0.0574 0.9206 0.0073
-6.000 -0.0029 0.01621 0.01203 -0.1505 0.8528 0.0127
-5.750 0.0262 0.01554 0.01114 -0.1512 0.8381 0.0143
-5.500 0.0517 0.01639 0.01202 -0.1502 0.8244 0.0154
-5.250 0.0811 0.01585 0.01125 -0.1508 0.8125 0.0174
-5.000 0.1123 0.01467 0.00966 -0.1520 0.8022 0.0198
-4.750 0.1414 0.01433 0.00917 -0.1525 0.7927 0.0212
-4.500 0.1690 0.01458 0.00940 -0.1525 0.7831 0.0224
-4.250 0.1978 0.01445 0.00915 -0.1528 0.7740 0.0239
-4.000 0.2270 0.01415 0.00867 -0.1532 0.7653 0.0259
-3.750 0.2569 0.01361 0.00792 -0.1537 0.7559 0.0273
-3.500 0.2862 0.01331 0.00743 -0.1541 0.7457 0.0285
-3.250 0.3156 0.01291 0.00683 -0.1545 0.7345 0.0290
-3.000 0.3449 0.01254 0.00627 -0.1548 0.7222 0.0294
-2.750 0.3744 0.01209 0.00565 -0.1552 0.7100 0.0299
-2.500 0.4048 0.01121 0.00456 -0.1559 0.6991 0.0307
-2.250 0.4345 0.01070 0.00392 -0.1564 0.6884 0.0318
-2.000 0.4636 0.01044 0.00355 -0.1567 0.6774 0.0330
-1.750 0.4925 0.01025 0.00328 -0.1569 0.6658 0.0342
-1.500 0.5214 0.01010 0.00305 -0.1572 0.6548 0.0353
-1.250 0.5502 0.00998 0.00286 -0.1574 0.6448 0.0363
-1.000 0.5789 0.00990 0.00268 -0.1575 0.6329 0.0371
-0.750 0.6074 0.00985 0.00253 -0.1577 0.6191 0.0378
-0.500 0.6358 0.00982 0.00241 -0.1578 0.6059 0.0384
-0.250 0.6643 0.00980 0.00233 -0.1579 0.5959 0.0395
0.000 0.6928 0.00979 0.00227 -0.1581 0.5878 0.0405
0.250 0.7212 0.00979 0.00222 -0.1582 0.5795 0.0410
0.500 0.7497 0.00977 0.00215 -0.1583 0.5721 0.0429
0.750 0.7782 0.00976 0.00211 -0.1584 0.5644 0.0487
1.000 0.8066 0.00972 0.00217 -0.1586 0.5569 0.0902
1.250 0.8346 0.00980 0.00223 -0.1586 0.5491 0.1031
1.500 0.8627 0.00984 0.00229 -0.1587 0.5406 0.1113
1.750 0.8905 0.00994 0.00234 -0.1587 0.5315 0.1158
2.000 0.9184 0.00999 0.00242 -0.1588 0.5226 0.1227
2.250 0.9463 0.01005 0.00250 -0.1589 0.5148 0.1336
2.500 0.9749 0.00993 0.00266 -0.1593 0.5075 0.2567
2.750 1.0031 0.00987 0.00287 -0.1595 0.5003 0.3761
3.000 1.0308 0.00993 0.00301 -0.1596 0.4917 0.4172
3.250 1.0585 0.00999 0.00315 -0.1596 0.4827 0.4560
3.500 1.0861 0.01005 0.00332 -0.1597 0.4720 0.5062
3.750 1.1082 0.00938 0.00344 -0.1586 0.4601 1.0000
4.000 1.1350 0.00960 0.00360 -0.1584 0.4383 1.0000
4.250 1.1584 0.01027 0.00391 -0.1579 0.3691 1.0000
4.500 1.1824 0.01089 0.00430 -0.1574 0.3293 1.0000
4.750 1.2071 0.01139 0.00466 -0.1570 0.3022 1.0000
5.000 1.2316 0.01189 0.00503 -0.1566 0.2729 1.0000
5.250 1.2499 0.01322 0.00576 -0.1555 0.1661 1.0000
5.500 1.2729 0.01386 0.00631 -0.1548 0.1410 1.0000
5.750 1.2864 0.01569 0.00746 -0.1529 0.0250 1.0000
6.000 1.3096 0.01623 0.00799 -0.1521 0.0152 1.0000
6.250 1.3328 0.01673 0.00854 -0.1514 0.0128 1.0000
6.500 1.3548 0.01736 0.00925 -0.1504 0.0105 1.0000
6.750 1.3769 0.01791 0.00990 -0.1495 0.0094 1.0000
7.000 1.3986 0.01848 0.01053 -0.1485 0.0085 1.0000
7.250 1.4192 0.01914 0.01125 -0.1473 0.0078 1.0000
7.500 1.4385 0.01987 0.01205 -0.1460 0.0072 1.0000
7.750 1.4541 0.02092 0.01319 -0.1441 0.0066 1.0000
8.000 1.4701 0.02185 0.01421 -0.1422 0.0063 1.0000
8.250 1.4869 0.02262 0.01509 -0.1404 0.0058 1.0000
8.500 1.5020 0.02345 0.01599 -0.1385 0.0054 1.0000
8.750 1.5139 0.02443 0.01705 -0.1360 0.0051 1.0000
9.000 1.5234 0.02545 0.01815 -0.1331 0.0049 1.0000
9.250 1.5298 0.02655 0.01933 -0.1298 0.0047 1.0000
9.500 1.5352 0.02784 0.02069 -0.1266 0.0045 1.0000
9.750 1.5374 0.02947 0.02242 -0.1232 0.0044 1.0000
10.000 1.5352 0.03161 0.02467 -0.1195 0.0042 1.0000
10.250 1.5397 0.03332 0.02651 -0.1169 0.0042 1.0000
10.500 1.5433 0.03523 0.02854 -0.1144 0.0041 1.0000
10.750 1.5460 0.03731 0.03076 -0.1120 0.0040 1.0000
11.000 1.5483 0.03955 0.03314 -0.1097 0.0039 1.0000
11.250 1.5504 0.04191 0.03563 -0.1076 0.0038 1.0000
11.500 1.5531 0.04427 0.03818 -0.1056 0.0036 1.0000
11.750 1.5559 0.04667 0.04071 -0.1039 0.0035 1.0000
12.000 1.5586 0.04908 0.04326 -0.1024 0.0033 1.0000
12.250 1.5605 0.05162 0.04594 -0.1010 0.0032 1.0000
12.500 1.5624 0.05419 0.04864 -0.0999 0.0031 1.0000
12.750 1.5637 0.05684 0.05141 -0.0990 0.0030 1.0000
13.000 1.5632 0.05978 0.05448 -0.0981 0.0029 1.0000
13.250 1.5612 0.06298 0.05782 -0.0973 0.0029 1.0000
13.500 1.5578 0.06646 0.06143 -0.0966 0.0028 1.0000
13.750 1.5535 0.07013 0.06525 -0.0962 0.0028 1.0000
14.000 1.5472 0.07420 0.06948 -0.0959 0.0028 1.0000
14.250 1.5392 0.07866 0.07410 -0.0959 0.0027 1.0000
14.500 1.5285 0.08367 0.07930 -0.0961 0.0027 1.0000
14.750 1.5153 0.08923 0.08506 -0.0966 0.0026 1.0000
15.000 1.5027 0.09496 0.09099 -0.0977 0.0026 1.0000
15.250 1.4902 0.10091 0.09715 -0.0992 0.0026 1.0000
15.500 1.4764 0.10732 0.10376 -0.1012 0.0026 1.0000
15.750 1.4617 0.11414 0.11078 -0.1038 0.0026 1.0000
16.000 1.4465 0.12137 0.11821 -0.1069 0.0026 1.0000
16.250 1.4312 0.12902 0.12605 -0.1106 0.0026 1.0000
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Polar data table (+)
Polar graphs
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