SOKOLOV AIRFOIL (sokolov-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: SOKOLOV AIRFOIL (sokolov-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.71 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sokolov-il-1000000-n5.txt Download as CSV file: xf-sokolov-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2687 0.10129 0.09965 -0.0406 0.9644 0.0040
-8.750 -0.2631 0.09766 0.09601 -0.0422 0.9534 0.0040
-8.500 -0.2588 0.09383 0.09217 -0.0437 0.9408 0.0040
-7.500 -0.1777 0.01685 0.01347 -0.1469 0.8445 0.0057
-7.250 -0.1460 0.01467 0.01083 -0.1494 0.8294 0.0059
-7.000 -0.1157 0.01350 0.00936 -0.1506 0.8167 0.0062
-6.750 -0.0852 0.01237 0.00796 -0.1519 0.8056 0.0071
-6.500 -0.0554 0.01163 0.00702 -0.1527 0.7955 0.0080
-6.250 -0.0257 0.01108 0.00628 -0.1533 0.7862 0.0088
-6.000 0.0039 0.01062 0.00568 -0.1538 0.7780 0.0100
-5.750 0.0333 0.01026 0.00525 -0.1542 0.7693 0.0121
-5.500 0.0623 0.01010 0.00503 -0.1545 0.7613 0.0145
-5.000 0.1189 0.01036 0.00527 -0.1544 0.7438 0.0190
-4.750 0.1473 0.01043 0.00527 -0.1545 0.7336 0.0197
-4.500 0.1758 0.01048 0.00525 -0.1545 0.7222 0.0200
-4.250 0.2055 0.01002 0.00464 -0.1551 0.7096 0.0215
-4.000 0.2340 0.01006 0.00462 -0.1552 0.6970 0.0225
-3.750 0.2627 0.01005 0.00455 -0.1553 0.6848 0.0234
-3.500 0.2916 0.00995 0.00435 -0.1556 0.6722 0.0243
-3.250 0.3206 0.00981 0.00409 -0.1558 0.6589 0.0252
-3.000 0.3498 0.00957 0.00374 -0.1561 0.6475 0.0259
-2.500 0.4084 0.00914 0.00308 -0.1568 0.6248 0.0274
-2.250 0.4374 0.00902 0.00288 -0.1570 0.6147 0.0282
-2.000 0.4661 0.00897 0.00276 -0.1572 0.6035 0.0289
-1.750 0.4947 0.00896 0.00266 -0.1573 0.5883 0.0293
-1.500 0.5232 0.00897 0.00258 -0.1575 0.5742 0.0295
-1.250 0.5522 0.00887 0.00241 -0.1577 0.5643 0.0301
-1.000 0.5814 0.00870 0.00218 -0.1581 0.5577 0.0309
-0.750 0.6104 0.00862 0.00203 -0.1583 0.5511 0.0316
-0.500 0.6392 0.00856 0.00194 -0.1585 0.5447 0.0321
-0.250 0.6679 0.00853 0.00186 -0.1587 0.5377 0.0327
0.000 0.6965 0.00852 0.00181 -0.1588 0.5311 0.0332
0.250 0.7251 0.00851 0.00177 -0.1590 0.5233 0.0342
0.500 0.7536 0.00853 0.00176 -0.1591 0.5154 0.0357
0.750 0.7820 0.00855 0.00175 -0.1592 0.5075 0.0369
1.000 0.8104 0.00858 0.00176 -0.1594 0.5008 0.0394
1.250 0.8388 0.00861 0.00178 -0.1595 0.4918 0.0479
1.500 0.8672 0.00861 0.00185 -0.1597 0.4823 0.0915
1.750 0.8952 0.00869 0.00192 -0.1598 0.4710 0.0993
2.000 0.9231 0.00879 0.00199 -0.1598 0.4599 0.1019
2.250 0.9510 0.00887 0.00206 -0.1599 0.4473 0.1056
2.500 0.9787 0.00900 0.00215 -0.1599 0.4296 0.1099
2.750 1.0057 0.00924 0.00228 -0.1599 0.3980 0.1127
3.250 1.0588 0.00986 0.00267 -0.1597 0.3377 0.1266
3.750 1.1124 0.01028 0.00317 -0.1599 0.2929 0.2739
4.000 1.1396 0.01040 0.00341 -0.1600 0.2791 0.3660
4.250 1.1662 0.01063 0.00366 -0.1599 0.2591 0.4194
4.500 1.1886 0.01149 0.00420 -0.1594 0.1738 0.4705
4.750 1.2145 0.01154 0.00471 -0.1595 0.1502 0.7667
5.000 1.2354 0.01152 0.00495 -0.1581 0.1336 1.0000
5.250 1.2530 0.01302 0.00585 -0.1567 0.0241 1.0000
5.500 1.2778 0.01342 0.00623 -0.1563 0.0141 1.0000
5.750 1.3028 0.01379 0.00660 -0.1559 0.0107 1.0000
6.000 1.3278 0.01411 0.00695 -0.1555 0.0093 1.0000
6.250 1.3524 0.01447 0.00732 -0.1550 0.0081 1.0000
6.500 1.3763 0.01490 0.00778 -0.1544 0.0070 1.0000
6.750 1.3998 0.01536 0.00828 -0.1537 0.0063 1.0000
7.000 1.4234 0.01578 0.00873 -0.1531 0.0059 1.0000
7.250 1.4465 0.01621 0.00918 -0.1524 0.0053 1.0000
7.500 1.4691 0.01667 0.00966 -0.1517 0.0048 1.0000
7.750 1.4895 0.01736 0.01039 -0.1505 0.0042 1.0000
8.000 1.5111 0.01787 0.01097 -0.1495 0.0041 1.0000
8.250 1.5317 0.01845 0.01160 -0.1484 0.0039 1.0000
8.500 1.5514 0.01907 0.01228 -0.1472 0.0036 1.0000
8.750 1.5702 0.01972 0.01299 -0.1458 0.0034 1.0000
9.000 1.5881 0.02040 0.01373 -0.1443 0.0032 1.0000
9.250 1.6051 0.02110 0.01447 -0.1426 0.0031 1.0000
9.500 1.6201 0.02186 0.01528 -0.1406 0.0029 1.0000
9.750 1.6316 0.02278 0.01627 -0.1380 0.0028 1.0000
10.000 1.6345 0.02410 0.01770 -0.1340 0.0026 1.0000
10.250 1.6432 0.02499 0.01867 -0.1310 0.0026 1.0000
10.500 1.6512 0.02602 0.01981 -0.1282 0.0025 1.0000
10.750 1.6588 0.02715 0.02104 -0.1254 0.0024 1.0000
11.000 1.6652 0.02845 0.02243 -0.1228 0.0023 1.0000
11.250 1.6706 0.02991 0.02398 -0.1202 0.0022 1.0000
11.500 1.6748 0.03156 0.02574 -0.1176 0.0022 1.0000
11.750 1.6784 0.03335 0.02764 -0.1153 0.0021 1.0000
12.000 1.6812 0.03531 0.02970 -0.1131 0.0020 1.0000
12.250 1.6836 0.03743 0.03194 -0.1112 0.0020 1.0000
12.500 1.6860 0.03964 0.03425 -0.1095 0.0019 1.0000
12.750 1.6883 0.04192 0.03663 -0.1080 0.0019 1.0000
13.000 1.6893 0.04443 0.03925 -0.1066 0.0019 1.0000
13.250 1.6894 0.04711 0.04204 -0.1053 0.0018 1.0000
13.500 1.6890 0.04990 0.04494 -0.1042 0.0018 1.0000
13.750 1.6885 0.05277 0.04791 -0.1032 0.0018 1.0000
14.000 1.6861 0.05595 0.05123 -0.1024 0.0017 1.0000
14.250 1.6836 0.05923 0.05463 -0.1017 0.0017 1.0000
14.500 1.6796 0.06279 0.05830 -0.1012 0.0017 1.0000
14.750 1.6749 0.06658 0.06221 -0.1009 0.0016 1.0000
15.000 1.6684 0.07072 0.06648 -0.1008 0.0016 1.0000
15.250 1.6605 0.07514 0.07103 -0.1009 0.0016 1.0000
15.500 1.6513 0.07989 0.07592 -0.1012 0.0016 1.0000
15.750 1.6396 0.08514 0.08133 -0.1017 0.0015 1.0000
16.000 1.6253 0.09098 0.08733 -0.1026 0.0015 1.0000
16.250 1.6097 0.09712 0.09364 -0.1037 0.0015 1.0000
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Polar data table (+)
Polar graphs
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