SOKOLOV AIRFOIL (sokolov-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SOKOLOV AIRFOIL (sokolov-il) Reynolds number: 1,000,000 Max Cl/Cd: 146.07 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sokolov-il-1000000.txt Download as CSV file: xf-sokolov-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2900 0.10755 0.10595 -0.0321 1.0000 0.0114
-8.750 -0.2864 0.10473 0.10315 -0.0332 1.0000 0.0115
-8.500 -0.2856 0.10231 0.10076 -0.0330 1.0000 0.0115
-8.250 -0.2750 0.09875 0.09721 -0.0358 0.9981 0.0116
-8.000 -0.2595 0.09465 0.09310 -0.0401 0.9955 0.0116
-7.750 -0.2442 0.09055 0.08901 -0.0443 0.9914 0.0116
-7.500 -0.2334 0.08577 0.08423 -0.0474 0.9857 0.0120
-7.250 -0.2178 0.08307 0.08153 -0.0501 0.9783 0.0123
-7.000 -0.2013 0.08022 0.07866 -0.0532 0.9698 0.0127
-6.750 -0.1875 0.07745 0.07588 -0.0558 0.9577 0.0135
-6.500 -0.1662 0.07305 0.07144 -0.0634 0.9428 0.0155
-6.250 -0.1472 0.06910 0.06745 -0.0682 0.9276 0.0156
-6.000 -0.0320 0.01777 0.01491 -0.1427 0.9162 0.0155
-5.750 0.0012 0.01490 0.01153 -0.1457 0.9002 0.0168
-5.500 0.0263 0.01562 0.01226 -0.1447 0.8787 0.0172
-5.250 -0.0425 0.04828 0.04620 -0.0967 0.8465 0.0147
-4.500 0.1432 0.01313 0.00886 -0.1470 0.8153 0.0222
-4.250 0.1715 0.01312 0.00878 -0.1471 0.8026 0.0230
-4.000 0.1997 0.01312 0.00871 -0.1473 0.7906 0.0242
-3.750 0.2289 0.01284 0.00831 -0.1476 0.7796 0.0257
-3.500 0.2586 0.01240 0.00769 -0.1480 0.7690 0.0269
-3.250 0.2876 0.01232 0.00749 -0.1482 0.7583 0.0277
-3.000 0.3195 0.01084 0.00569 -0.1494 0.7482 0.0293
-2.750 0.3496 0.01013 0.00484 -0.1500 0.7373 0.0302
-2.250 0.4083 0.00949 0.00401 -0.1507 0.7152 0.0325
-2.000 0.4376 0.00922 0.00366 -0.1510 0.7037 0.0337
-1.750 0.4668 0.00897 0.00331 -0.1512 0.6906 0.0345
-1.500 0.4959 0.00876 0.00300 -0.1515 0.6758 0.0351
-1.250 0.5250 0.00858 0.00272 -0.1517 0.6617 0.0356
-1.000 0.5541 0.00843 0.00249 -0.1519 0.6495 0.0362
-0.750 0.5831 0.00833 0.00231 -0.1521 0.6380 0.0368
-0.500 0.6118 0.00828 0.00221 -0.1523 0.6270 0.0377
-0.250 0.6410 0.00816 0.00202 -0.1525 0.6173 0.0388
0.000 0.6701 0.00803 0.00181 -0.1527 0.6077 0.0421
0.250 0.6989 0.00801 0.00174 -0.1529 0.5978 0.0450
0.500 0.7275 0.00799 0.00169 -0.1530 0.5889 0.0482
0.750 0.7563 0.00795 0.00170 -0.1532 0.5798 0.0842
1.000 0.7846 0.00800 0.00176 -0.1533 0.5699 0.1079
1.250 0.8128 0.00805 0.00180 -0.1534 0.5606 0.1153
1.500 0.8412 0.00809 0.00184 -0.1535 0.5533 0.1232
1.750 0.8696 0.00812 0.00187 -0.1536 0.5468 0.1280
2.000 0.8978 0.00816 0.00192 -0.1537 0.5399 0.1367
2.500 0.9554 0.00793 0.00218 -0.1544 0.5263 0.3728
2.750 0.9837 0.00791 0.00231 -0.1546 0.5194 0.4459
3.000 1.0119 0.00791 0.00243 -0.1548 0.5115 0.5099
3.250 1.0358 0.00713 0.00255 -0.1541 0.5043 1.0000
3.500 1.0634 0.00728 0.00264 -0.1541 0.4898 1.0000
3.750 1.0907 0.00749 0.00275 -0.1540 0.4670 1.0000
4.000 1.1180 0.00768 0.00287 -0.1540 0.4450 1.0000
4.250 1.1436 0.00817 0.00310 -0.1537 0.3891 1.0000
4.500 1.1677 0.00889 0.00348 -0.1533 0.3284 1.0000
4.750 1.1935 0.00929 0.00375 -0.1531 0.3025 1.0000
5.000 1.2188 0.00976 0.00405 -0.1528 0.2700 1.0000
5.250 1.2387 0.01105 0.00475 -0.1519 0.1619 1.0000
5.500 1.2624 0.01171 0.00523 -0.1513 0.1257 1.0000
5.750 1.2787 0.01341 0.00629 -0.1497 0.0185 1.0000
6.000 1.3037 0.01379 0.00671 -0.1492 0.0160 1.0000
6.250 1.3280 0.01425 0.00720 -0.1487 0.0142 1.0000
6.500 1.3507 0.01491 0.00795 -0.1477 0.0121 1.0000
6.750 1.3743 0.01539 0.00847 -0.1471 0.0115 1.0000
7.000 1.3975 0.01589 0.00902 -0.1463 0.0109 1.0000
7.250 1.4199 0.01647 0.00964 -0.1454 0.0102 1.0000
7.500 1.4415 0.01709 0.01031 -0.1444 0.0097 1.0000
7.750 1.4620 0.01779 0.01108 -0.1432 0.0091 1.0000
8.000 1.4787 0.01884 0.01220 -0.1414 0.0085 1.0000
8.250 1.4889 0.02042 0.01391 -0.1385 0.0080 1.0000
8.500 1.5099 0.02089 0.01442 -0.1375 0.0077 1.0000
8.750 1.5263 0.02172 0.01531 -0.1356 0.0074 1.0000
9.000 1.5402 0.02268 0.01634 -0.1334 0.0071 1.0000
9.250 1.5519 0.02370 0.01745 -0.1308 0.0069 1.0000
9.500 1.5615 0.02479 0.01862 -0.1279 0.0067 1.0000
9.750 1.5679 0.02588 0.01978 -0.1245 0.0065 1.0000
10.000 1.5744 0.02705 0.02102 -0.1213 0.0063 1.0000
10.250 1.5809 0.02832 0.02237 -0.1183 0.0061 1.0000
10.500 1.5874 0.02968 0.02380 -0.1156 0.0060 1.0000
10.750 1.5933 0.03117 0.02535 -0.1130 0.0058 1.0000
11.000 1.5968 0.03299 0.02725 -0.1103 0.0057 1.0000
11.250 1.5962 0.03552 0.02988 -0.1071 0.0055 1.0000
11.500 1.5944 0.03927 0.03383 -0.1035 0.0053 1.0000
11.750 1.5996 0.04096 0.03565 -0.1015 0.0052 1.0000
12.000 1.6039 0.04289 0.03771 -0.0996 0.0051 1.0000
12.250 1.6070 0.04509 0.04006 -0.0976 0.0050 1.0000
12.500 1.6090 0.04745 0.04257 -0.0959 0.0049 1.0000
12.750 1.6095 0.05005 0.04532 -0.0942 0.0047 1.0000
13.000 1.6077 0.05306 0.04850 -0.0925 0.0046 1.0000
13.250 1.6037 0.05643 0.05205 -0.0909 0.0045 1.0000
13.500 1.5958 0.06039 0.05621 -0.0894 0.0045 1.0000
13.750 1.5857 0.06470 0.06071 -0.0882 0.0045 1.0000
14.000 1.5735 0.06936 0.06558 -0.0874 0.0045 1.0000
14.250 1.5587 0.07447 0.07089 -0.0871 0.0045 1.0000
14.500 1.5424 0.08005 0.07667 -0.0873 0.0045 1.0000
14.750 1.5246 0.08613 0.08296 -0.0882 0.0045 1.0000
15.000 1.5063 0.09256 0.08957 -0.0896 0.0046 1.0000
15.250 1.4872 0.09950 0.09669 -0.0917 0.0046 1.0000
15.500 1.4681 0.10681 0.10419 -0.0945 0.0046 1.0000
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Polar data table (+)
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