SOKOLOV AIRFOIL (sokolov-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SOKOLOV AIRFOIL (sokolov-il) Reynolds number: 50,000 Max Cl/Cd: 45.15 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sokolov-il-50000-n5.txt Download as CSV file: xf-sokolov-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2803 0.11133 0.10488 -0.0328 1.0000 0.0771
-7.500 -0.2910 0.11099 0.10470 -0.0317 1.0000 0.0777
-7.250 -0.2994 0.11045 0.10431 -0.0317 1.0000 0.0780
-7.000 -0.2879 0.10488 0.09876 -0.0282 1.0000 0.0813
-6.750 -0.2911 0.10318 0.09717 -0.0266 1.0000 0.0847
-6.500 -0.2985 0.10232 0.09643 -0.0260 1.0000 0.0876
-6.250 -0.3067 0.10213 0.09637 -0.0272 1.0000 0.0891
-6.000 -0.3097 0.10171 0.09605 -0.0306 1.0000 0.0897
-5.750 -0.3041 0.09647 0.09086 -0.0252 0.9983 0.0926
-5.500 -0.2765 0.09230 0.08664 -0.0314 0.9904 0.0983
-5.000 -0.2140 0.08343 0.07765 -0.0476 0.9733 0.1055
-4.750 -0.1576 0.07962 0.07364 -0.0660 0.9639 0.1161
-4.500 -0.1472 0.07496 0.06904 -0.0625 0.9564 0.1196
-4.250 -0.1121 0.07064 0.06463 -0.0692 0.9489 0.1226
-4.000 -0.0699 0.06601 0.05985 -0.0783 0.9408 0.1224
-3.500 0.0619 0.05131 0.04435 -0.1093 0.9283 0.0768
-3.250 0.1318 0.04490 0.03732 -0.1236 0.9246 0.0779
-3.000 0.1645 0.04278 0.03513 -0.1264 0.9159 0.0823
-2.750 0.2303 0.03745 0.02901 -0.1375 0.9120 0.0800
-2.500 0.2815 0.03420 0.02513 -0.1439 0.9066 0.0802
-2.250 0.3245 0.03198 0.02239 -0.1479 0.8992 0.0817
-2.000 0.3692 0.03028 0.02007 -0.1517 0.8936 0.0887
-1.750 0.4042 0.02918 0.01874 -0.1536 0.8849 0.0940
-1.500 0.4431 0.02792 0.01705 -0.1559 0.8781 0.0966
-1.250 0.4793 0.02695 0.01569 -0.1574 0.8704 0.1002
-1.000 0.5137 0.02620 0.01464 -0.1585 0.8625 0.1048
-0.750 0.5491 0.02552 0.01371 -0.1597 0.8555 0.1131
-0.500 0.5809 0.02500 0.01307 -0.1604 0.8469 0.1263
-0.250 0.6167 0.02434 0.01250 -0.1619 0.8406 0.1648
0.000 0.6466 0.02396 0.01244 -0.1626 0.8314 0.2452
0.250 0.6803 0.02336 0.01244 -0.1636 0.8255 0.4345
0.500 0.6972 0.02240 0.01243 -0.1612 0.8152 0.9266
0.750 0.7283 0.02264 0.01232 -0.1617 0.8075 1.0000
1.000 0.7577 0.02293 0.01237 -0.1619 0.7992 1.0000
1.250 0.7855 0.02331 0.01255 -0.1619 0.7907 1.0000
1.500 0.8155 0.02355 0.01263 -0.1621 0.7833 1.0000
1.750 0.8413 0.02398 0.01295 -0.1618 0.7735 1.0000
2.000 0.8707 0.02415 0.01299 -0.1617 0.7647 1.0000
2.250 0.8982 0.02433 0.01311 -0.1612 0.7539 1.0000
2.500 0.9235 0.02459 0.01331 -0.1605 0.7416 1.0000
2.750 0.9494 0.02484 0.01353 -0.1598 0.7302 1.0000
3.000 0.9776 0.02501 0.01369 -0.1594 0.7212 1.0000
3.250 1.0026 0.02544 0.01415 -0.1589 0.7114 1.0000
3.500 1.0276 0.02589 0.01465 -0.1584 0.7020 1.0000
3.750 1.0559 0.02610 0.01490 -0.1581 0.6943 1.0000
4.000 1.0789 0.02668 0.01563 -0.1574 0.6840 1.0000
4.250 1.1044 0.02706 0.01610 -0.1568 0.6746 1.0000
4.500 1.1316 0.02728 0.01641 -0.1563 0.6655 1.0000
4.750 1.1544 0.02781 0.01713 -0.1554 0.6542 1.0000
5.000 1.1784 0.02819 0.01766 -0.1545 0.6427 1.0000
5.250 1.2034 0.02845 0.01807 -0.1535 0.6309 1.0000
5.500 1.2289 0.02864 0.01841 -0.1525 0.6188 1.0000
5.750 1.2542 0.02886 0.01887 -0.1516 0.6068 1.0000
6.000 1.2764 0.02938 0.01962 -0.1504 0.5940 1.0000
6.250 1.2987 0.02989 0.02039 -0.1493 0.5813 1.0000
6.500 1.3214 0.03033 0.02109 -0.1481 0.5678 1.0000
6.750 1.3438 0.03074 0.02178 -0.1467 0.5535 1.0000
7.000 1.3619 0.03046 0.02170 -0.1437 0.5235 1.0000
7.250 1.3722 0.03039 0.02165 -0.1396 0.4795 1.0000
7.500 1.3856 0.03088 0.02234 -0.1368 0.4465 1.0000
7.750 1.3899 0.03154 0.02280 -0.1323 0.3800 1.0000
8.000 1.3846 0.03331 0.02378 -0.1271 0.2935 1.0000
8.250 1.3717 0.03615 0.02591 -0.1222 0.1841 1.0000
8.500 1.3565 0.03950 0.02872 -0.1176 0.1332 1.0000
8.750 1.3444 0.04310 0.03186 -0.1141 0.0735 1.0000
9.000 1.3369 0.04647 0.03509 -0.1113 0.0584 1.0000
9.250 1.3321 0.04973 0.03838 -0.1090 0.0509 1.0000
9.500 1.3284 0.05299 0.04177 -0.1072 0.0458 1.0000
9.750 1.3229 0.05656 0.04541 -0.1056 0.0428 1.0000
10.000 1.3212 0.05981 0.04891 -0.1042 0.0407 1.0000
10.250 1.3190 0.06316 0.05248 -0.1029 0.0390 1.0000
10.500 1.3170 0.06654 0.05613 -0.1016 0.0375 1.0000
10.750 1.3149 0.06994 0.05966 -0.1005 0.0359 1.0000
11.000 1.3122 0.07340 0.06320 -0.0993 0.0344 1.0000
11.250 1.3168 0.07605 0.06608 -0.0978 0.0327 1.0000
11.500 1.3230 0.07851 0.06878 -0.0961 0.0310 1.0000
11.750 1.3336 0.08052 0.07099 -0.0939 0.0297 1.0000
12.000 1.3505 0.08206 0.07275 -0.0913 0.0287 1.0000
12.250 1.3674 0.08406 0.07496 -0.0889 0.0279 1.0000
12.500 1.3803 0.08682 0.07790 -0.0872 0.0270 1.0000
12.750 1.3880 0.09048 0.08175 -0.0859 0.0263 1.0000
13.000 1.3830 0.09493 0.08659 -0.0858 0.0260 1.0000
13.250 1.3754 0.09978 0.09178 -0.0862 0.0257 1.0000
13.500 1.3657 0.10499 0.09732 -0.0871 0.0255 1.0000
13.750 1.3542 0.11057 0.10321 -0.0886 0.0254 1.0000
14.000 1.3414 0.11654 0.10946 -0.0908 0.0254 1.0000
14.250 1.3282 0.12290 0.11608 -0.0936 0.0254 1.0000
14.500 1.3144 0.12978 0.12318 -0.0972 0.0255 1.0000
14.750 1.3007 0.13708 0.13069 -0.1014 0.0256 1.0000
15.000 1.2873 0.14485 0.13864 -0.1063 0.0257 1.0000
15.250 1.2752 0.15294 0.14688 -0.1116 0.0259 1.0000
15.500 1.2646 0.16131 0.15536 -0.1172 0.0261 1.0000
15.750 1.2556 0.16986 0.16401 -0.1229 0.0263 1.0000
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Polar data table (+)
Polar graphs
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