SOKOLOV AIRFOIL (sokolov-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SOKOLOV AIRFOIL (sokolov-il) Reynolds number: 200,000 Max Cl/Cd: 92.88 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sokolov-il-200000.txt Download as CSV file: xf-sokolov-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2858 0.09736 0.09416 -0.0273 1.0000 0.0329
-7.000 -0.2999 0.09673 0.09363 -0.0235 1.0000 0.0333
-6.750 -0.3142 0.09617 0.09316 -0.0202 0.9994 0.0338
-6.500 -0.2817 0.09142 0.08839 -0.0298 0.9938 0.0361
-6.250 -0.2310 0.08716 0.08408 -0.0495 0.9851 0.0378
-6.000 -0.1897 0.08213 0.07899 -0.0616 0.9791 0.0380
-5.750 -0.1731 0.07520 0.07207 -0.0644 0.9744 0.0390
-5.500 -0.1509 0.07143 0.06829 -0.0651 0.9715 0.0406
-5.250 -0.1192 0.06767 0.06450 -0.0706 0.9662 0.0434
-5.000 -0.0339 0.06151 0.05812 -0.0974 0.9598 0.0503
-4.750 -0.0104 0.05556 0.05217 -0.1004 0.9569 0.0520
-4.500 0.0143 0.05290 0.04950 -0.1016 0.9498 0.0547
-4.250 0.0861 0.04584 0.04218 -0.1206 0.9449 0.0645
-4.000 0.1061 0.04444 0.04082 -0.1191 0.9386 0.0690
-3.750 0.1581 0.03959 0.03575 -0.1295 0.9310 0.0784
-3.500 0.2094 0.03532 0.03120 -0.1383 0.9247 0.0900
-2.500 0.3804 0.01957 0.01351 -0.1562 0.8884 0.0734
-2.250 0.4147 0.01721 0.01068 -0.1575 0.8780 0.0692
-2.000 0.4467 0.01562 0.00864 -0.1579 0.8677 0.0679
-1.750 0.4759 0.01479 0.00757 -0.1578 0.8565 0.0693
-1.500 0.5041 0.01425 0.00684 -0.1575 0.8435 0.0722
-1.250 0.5325 0.01363 0.00605 -0.1572 0.8305 0.0733
-1.000 0.5606 0.01318 0.00546 -0.1569 0.8176 0.0752
-0.750 0.5888 0.01283 0.00510 -0.1568 0.8054 0.0790
-0.500 0.6170 0.01268 0.00488 -0.1565 0.7941 0.0855
-0.250 0.6452 0.01256 0.00472 -0.1564 0.7836 0.0975
0.000 0.6742 0.01224 0.00449 -0.1566 0.7721 0.1362
0.250 0.7027 0.01201 0.00444 -0.1567 0.7614 0.2022
0.500 0.7308 0.01181 0.00456 -0.1569 0.7519 0.3318
0.750 0.7584 0.01171 0.00467 -0.1568 0.7419 0.4527
1.000 0.7825 0.01103 0.00471 -0.1559 0.7313 0.7272
1.250 0.8066 0.01082 0.00457 -0.1547 0.7209 1.0000
1.500 0.8343 0.01096 0.00456 -0.1544 0.7112 1.0000
1.750 0.8619 0.01109 0.00460 -0.1542 0.7004 1.0000
2.000 0.8896 0.01124 0.00467 -0.1541 0.6912 1.0000
2.250 0.9173 0.01141 0.00473 -0.1539 0.6832 1.0000
2.500 0.9448 0.01156 0.00488 -0.1538 0.6737 1.0000
2.750 0.9723 0.01173 0.00498 -0.1537 0.6653 1.0000
3.000 0.9998 0.01190 0.00512 -0.1535 0.6567 1.0000
3.250 1.0273 0.01208 0.00530 -0.1534 0.6485 1.0000
3.500 1.0546 0.01226 0.00546 -0.1532 0.6404 1.0000
3.750 1.0817 0.01244 0.00567 -0.1530 0.6308 1.0000
4.000 1.1088 0.01263 0.00585 -0.1528 0.6220 1.0000
4.250 1.1358 0.01282 0.00606 -0.1526 0.6128 1.0000
4.500 1.1627 0.01302 0.00634 -0.1524 0.6033 1.0000
4.750 1.1893 0.01321 0.00655 -0.1520 0.5927 1.0000
5.000 1.2148 0.01335 0.00671 -0.1514 0.5759 1.0000
5.250 1.2397 0.01349 0.00684 -0.1507 0.5562 1.0000
5.500 1.2645 0.01367 0.00705 -0.1499 0.5350 1.0000
5.750 1.2888 0.01388 0.00726 -0.1491 0.5115 1.0000
6.000 1.3124 0.01413 0.00751 -0.1482 0.4814 1.0000
6.250 1.3335 0.01452 0.00776 -0.1469 0.4237 1.0000
6.500 1.3471 0.01577 0.00842 -0.1446 0.3297 1.0000
6.750 1.3514 0.01827 0.00985 -0.1413 0.1702 1.0000
7.000 1.3525 0.02123 0.01190 -0.1376 0.0471 1.0000
7.250 1.3672 0.02255 0.01321 -0.1354 0.0358 1.0000
7.500 1.3819 0.02379 0.01459 -0.1332 0.0323 1.0000
7.750 1.3961 0.02496 0.01593 -0.1309 0.0305 1.0000
8.000 1.4073 0.02629 0.01739 -0.1282 0.0291 1.0000
8.250 1.4154 0.02773 0.01895 -0.1251 0.0276 1.0000
8.500 1.4183 0.02938 0.02067 -0.1214 0.0261 1.0000
8.750 1.4151 0.03157 0.02292 -0.1169 0.0250 1.0000
9.000 1.4180 0.03381 0.02522 -0.1134 0.0244 1.0000
9.250 1.4287 0.03555 0.02705 -0.1109 0.0241 1.0000
9.500 1.4432 0.03743 0.02903 -0.1089 0.0238 1.0000
9.750 1.4638 0.03956 0.03126 -0.1075 0.0237 1.0000
10.000 1.4951 0.04241 0.03429 -0.1077 0.0238 1.0000
10.250 1.5281 0.04597 0.03809 -0.1085 0.0239 1.0000
10.500 1.5395 0.04825 0.04064 -0.1061 0.0235 1.0000
10.750 1.5484 0.05091 0.04359 -0.1036 0.0232 1.0000
11.000 1.5843 0.05708 0.05001 -0.1052 0.0250 1.0000
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Polar data table (+)
Polar graphs
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