SOKOLOV AIRFOIL (sokolov-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SOKOLOV AIRFOIL (sokolov-il) Reynolds number: 200,000 Max Cl/Cd: 91.97 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sokolov-il-200000-n5.txt Download as CSV file: xf-sokolov-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2783 0.11256 0.10915 -0.0361 1.0000 0.0198
-8.500 -0.2773 0.11000 0.10664 -0.0358 1.0000 0.0198
-8.250 -0.2781 0.10761 0.10428 -0.0349 1.0000 0.0198
-8.000 -0.2751 0.10495 0.10167 -0.0355 0.9982 0.0198
-7.750 -0.1322 0.07830 0.07513 -0.0543 0.9701 0.0190
-7.500 -0.1212 0.07412 0.07095 -0.0566 0.9642 0.0183
-7.250 -0.2254 0.09151 0.08822 -0.0450 0.9831 0.0191
-7.000 -0.2079 0.08744 0.08415 -0.0486 0.9768 0.0180
-6.750 -0.1896 0.08338 0.08009 -0.0534 0.9678 0.0174
-6.500 -0.1699 0.07924 0.07594 -0.0586 0.9583 0.0170
-6.250 -0.1475 0.07494 0.07162 -0.0646 0.9491 0.0169
-6.000 -0.1237 0.07062 0.06728 -0.0710 0.9385 0.0173
-5.750 -0.0961 0.06567 0.06229 -0.0792 0.9258 0.0187
-5.500 -0.0644 0.06005 0.05660 -0.0885 0.9131 0.0192
-5.250 -0.0275 0.05385 0.05031 -0.0986 0.9011 0.0197
-5.000 0.0104 0.04835 0.04469 -0.1079 0.8900 0.0208
-4.750 0.0341 0.04778 0.04407 -0.1086 0.8786 0.0230
-4.500 0.0789 0.04249 0.03859 -0.1184 0.8682 0.0251
-4.250 0.1739 0.02605 0.02116 -0.1454 0.8625 0.0303
-4.000 0.2083 0.02374 0.01855 -0.1486 0.8519 0.0322
-3.750 0.2390 0.02271 0.01730 -0.1500 0.8405 0.0352
-3.500 0.2776 0.01968 0.01358 -0.1534 0.8300 0.0378
-3.250 0.3112 0.01800 0.01136 -0.1550 0.8196 0.0394
-3.000 0.3420 0.01725 0.01020 -0.1556 0.8095 0.0409
-2.750 0.3728 0.01625 0.00886 -0.1563 0.7994 0.0411
-2.500 0.4036 0.01507 0.00737 -0.1571 0.7899 0.0418
-2.250 0.4333 0.01422 0.00631 -0.1576 0.7808 0.0430
-2.000 0.4626 0.01368 0.00565 -0.1579 0.7707 0.0444
-1.750 0.4915 0.01330 0.00514 -0.1581 0.7607 0.0459
-1.500 0.5202 0.01301 0.00473 -0.1582 0.7502 0.0473
-1.250 0.5487 0.01278 0.00440 -0.1583 0.7390 0.0490
-1.000 0.5772 0.01262 0.00414 -0.1584 0.7275 0.0519
-0.750 0.6056 0.01249 0.00391 -0.1584 0.7164 0.0535
-0.500 0.6341 0.01237 0.00370 -0.1585 0.7064 0.0546
-0.250 0.6627 0.01226 0.00352 -0.1586 0.6964 0.0573
0.000 0.6912 0.01218 0.00342 -0.1587 0.6867 0.0625
0.250 0.7194 0.01214 0.00344 -0.1587 0.6776 0.0925
0.500 0.7475 0.01217 0.00343 -0.1587 0.6681 0.1153
0.750 0.7754 0.01217 0.00342 -0.1587 0.6582 0.1296
1.000 0.8030 0.01216 0.00344 -0.1587 0.6474 0.1506
1.250 0.8310 0.01203 0.00354 -0.1589 0.6361 0.2473
1.500 0.8587 0.01186 0.00377 -0.1591 0.6251 0.4190
1.750 0.8860 0.01182 0.00386 -0.1590 0.6151 0.4936
2.000 0.9117 0.01148 0.00395 -0.1585 0.6058 0.6969
2.250 0.9347 0.01121 0.00392 -0.1572 0.5973 1.0000
2.500 0.9622 0.01138 0.00403 -0.1571 0.5902 1.0000
2.750 0.9897 0.01155 0.00417 -0.1571 0.5821 1.0000
3.000 1.0170 0.01173 0.00431 -0.1570 0.5738 1.0000
3.250 1.0441 0.01191 0.00447 -0.1568 0.5648 1.0000
3.500 1.0713 0.01210 0.00465 -0.1567 0.5561 1.0000
3.750 1.0981 0.01231 0.00485 -0.1565 0.5476 1.0000
4.000 1.1251 0.01249 0.00508 -0.1564 0.5386 1.0000
4.250 1.1519 0.01270 0.00531 -0.1562 0.5304 1.0000
4.500 1.1786 0.01291 0.00558 -0.1560 0.5213 1.0000
4.750 1.2052 0.01312 0.00586 -0.1557 0.5120 1.0000
5.000 1.2306 0.01338 0.00611 -0.1553 0.4930 1.0000
5.250 1.2545 0.01370 0.00636 -0.1546 0.4597 1.0000
5.500 1.2760 0.01424 0.00669 -0.1535 0.3990 1.0000
5.750 1.2921 0.01539 0.00733 -0.1517 0.3242 1.0000
6.000 1.3113 0.01631 0.00803 -0.1505 0.2787 1.0000
6.500 1.3325 0.02007 0.01049 -0.1459 0.0686 1.0000
6.750 1.3430 0.02181 0.01192 -0.1433 0.0225 1.0000
7.000 1.3599 0.02283 0.01307 -0.1415 0.0175 1.0000
7.250 1.3771 0.02376 0.01416 -0.1397 0.0160 1.0000
7.500 1.3932 0.02472 0.01531 -0.1378 0.0150 1.0000
7.750 1.4072 0.02579 0.01654 -0.1356 0.0139 1.0000
8.000 1.4190 0.02693 0.01781 -0.1332 0.0126 1.0000
8.250 1.4271 0.02823 0.01924 -0.1302 0.0117 1.0000
8.500 1.4295 0.02973 0.02087 -0.1264 0.0112 1.0000
8.750 1.4297 0.03153 0.02280 -0.1226 0.0108 1.0000
9.000 1.4283 0.03366 0.02509 -0.1189 0.0105 1.0000
9.250 1.4256 0.03613 0.02767 -0.1154 0.0101 1.0000
9.500 1.4264 0.03857 0.03019 -0.1123 0.0099 1.0000
9.750 1.4337 0.04041 0.03216 -0.1101 0.0097 1.0000
10.000 1.4421 0.04217 0.03405 -0.1082 0.0093 1.0000
10.250 1.4504 0.04398 0.03600 -0.1063 0.0088 1.0000
10.500 1.4580 0.04592 0.03806 -0.1045 0.0083 1.0000
10.750 1.4654 0.04804 0.04032 -0.1027 0.0079 1.0000
11.000 1.4729 0.05030 0.04272 -0.1008 0.0077 1.0000
11.250 1.4799 0.05266 0.04524 -0.0990 0.0075 1.0000
11.500 1.4861 0.05516 0.04790 -0.0973 0.0074 1.0000
11.750 1.4905 0.05788 0.05080 -0.0956 0.0072 1.0000
12.000 1.4929 0.06081 0.05392 -0.0940 0.0071 1.0000
12.250 1.4933 0.06397 0.05735 -0.0925 0.0070 1.0000
12.500 1.4916 0.06741 0.06100 -0.0912 0.0069 1.0000
12.750 1.4876 0.07113 0.06494 -0.0900 0.0069 1.0000
13.000 1.4814 0.07514 0.06918 -0.0891 0.0068 1.0000
13.250 1.4731 0.07946 0.07373 -0.0885 0.0068 1.0000
13.500 1.4628 0.08408 0.07858 -0.0883 0.0068 1.0000
13.750 1.4509 0.08901 0.08375 -0.0885 0.0068 1.0000
14.000 1.4379 0.09426 0.08923 -0.0893 0.0068 1.0000
14.250 1.4242 0.09985 0.09506 -0.0906 0.0068 1.0000
14.500 1.4097 0.10583 0.10127 -0.0924 0.0068 1.0000
14.750 1.3952 0.11216 0.10781 -0.0949 0.0068 1.0000
15.000 1.3803 0.11894 0.11480 -0.0980 0.0068 1.0000
15.250 1.3652 0.12623 0.12232 -0.1019 0.0069 1.0000
15.500 1.3496 0.13415 0.13044 -0.1065 0.0069 1.0000
15.750 1.3327 0.14313 0.13964 -0.1123 0.0070 1.0000
16.000 1.3085 0.15554 0.15234 -0.1210 0.0072 1.0000
16.250 1.2855 0.16924 0.16627 -0.1307 0.0074 1.0000
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