SOKOLOV AIRFOIL (sokolov-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: SOKOLOV AIRFOIL (sokolov-il) Reynolds number: 500,000 Max Cl/Cd: 124.67 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sokolov-il-500000.txt Download as CSV file: xf-sokolov-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-2.750 0.3467 0.01326 0.00769 -0.1502 0.8010 0.0410
-2.500 0.3772 0.01235 0.00653 -0.1508 0.7891 0.0415
-2.250 0.4066 0.01180 0.00582 -0.1511 0.7778 0.0433
-2.000 0.4364 0.01119 0.00502 -0.1514 0.7669 0.0439
-1.750 0.4658 0.01072 0.00442 -0.1517 0.7562 0.0446
-1.500 0.4952 0.01034 0.00393 -0.1519 0.7454 0.0454
-1.250 0.5244 0.01004 0.00353 -0.1521 0.7343 0.0461
-1.000 0.5533 0.00982 0.00323 -0.1523 0.7231 0.0476
-0.750 0.5822 0.00965 0.00296 -0.1524 0.7112 0.0489
-0.500 0.6110 0.00950 0.00272 -0.1525 0.6978 0.0500
-0.250 0.6400 0.00934 0.00247 -0.1526 0.6846 0.0523
0.000 0.6689 0.00923 0.00231 -0.1528 0.6731 0.0568
0.500 0.7260 0.00916 0.00229 -0.1530 0.6532 0.1097
0.750 0.7544 0.00916 0.00229 -0.1531 0.6430 0.1311
1.000 0.7827 0.00917 0.00231 -0.1532 0.6336 0.1450
1.250 0.8109 0.00919 0.00234 -0.1533 0.6246 0.1675
1.500 0.8397 0.00901 0.00247 -0.1537 0.6151 0.2951
1.750 0.8680 0.00894 0.00263 -0.1539 0.6060 0.4130
2.000 0.8961 0.00886 0.00276 -0.1541 0.5975 0.5175
2.750 0.9746 0.00830 0.00296 -0.1529 0.5746 1.0000
4.500 1.1664 0.00937 0.00387 -0.1523 0.4976 1.0000
4.750 1.1931 0.00957 0.00403 -0.1521 0.4790 1.0000
5.000 1.2191 0.00984 0.00422 -0.1519 0.4454 1.0000
5.250 1.2413 0.01060 0.00458 -0.1511 0.3681 1.0000
5.500 1.2637 0.01140 0.00509 -0.1504 0.3182 1.0000
5.750 1.2859 0.01221 0.00563 -0.1497 0.2678 1.0000
6.000 1.3002 0.01407 0.00672 -0.1479 0.1387 1.0000
6.250 1.3121 0.01614 0.00806 -0.1457 0.0244 1.0000
6.500 1.3348 0.01675 0.00874 -0.1448 0.0209 1.0000
6.750 1.3560 0.01751 0.00959 -0.1436 0.0184 1.0000
7.000 1.3760 0.01837 0.01056 -0.1422 0.0170 1.0000
7.250 1.3964 0.01910 0.01136 -0.1410 0.0159 1.0000
7.500 1.4150 0.01998 0.01233 -0.1394 0.0150 1.0000
7.750 1.4317 0.02096 0.01340 -0.1376 0.0143 1.0000
8.000 1.4464 0.02207 0.01460 -0.1355 0.0137 1.0000
8.250 1.4579 0.02336 0.01597 -0.1328 0.0132 1.0000
8.500 1.4648 0.02490 0.01761 -0.1295 0.0127 1.0000
8.750 1.4674 0.02674 0.01953 -0.1255 0.0124 1.0000
9.000 1.4659 0.02906 0.02195 -0.1209 0.0121 1.0000
9.250 1.4759 0.03030 0.02329 -0.1182 0.0117 1.0000
9.500 1.4872 0.03136 0.02445 -0.1158 0.0113 1.0000
9.750 1.4974 0.03290 0.02611 -0.1134 0.0111 1.0000
10.000 1.5084 0.03460 0.02792 -0.1111 0.0109 1.0000
10.250 1.5205 0.03646 0.02990 -0.1089 0.0107 1.0000
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Polar data table (+)
Polar graphs
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