CLARK-Y 11.7% smoothed (clarkysm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK-Y 11.7% smoothed (clarkysm-il) Reynolds number: 50,000 Max Cl/Cd: 35.34 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkysm-il-50000-n5.txt Download as CSV file: xf-clarkysm-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK-Y 11.7% smoothed
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3642 0.11556 0.10804 -0.0438 1.0000 0.0678
-10.250 -0.3642 0.11206 0.10461 -0.0442 1.0000 0.0676
-10.000 -0.3647 0.10871 0.10132 -0.0445 1.0000 0.0675
-9.750 -0.3659 0.10534 0.09803 -0.0446 1.0000 0.0673
-9.500 -0.3674 0.10211 0.09486 -0.0445 1.0000 0.0669
-9.250 -0.3703 0.09892 0.09174 -0.0443 1.0000 0.0664
-9.000 -0.3754 0.09575 0.08867 -0.0441 1.0000 0.0659
-8.750 -0.3834 0.09261 0.08562 -0.0437 1.0000 0.0654
-8.500 -0.3950 0.08953 0.08266 -0.0432 1.0000 0.0649
-8.250 -0.4104 0.08667 0.07992 -0.0422 1.0000 0.0644
-8.000 -0.4305 0.08388 0.07726 -0.0409 1.0000 0.0639
-7.750 -0.4483 0.08045 0.07394 -0.0404 1.0000 0.0634
-7.500 -0.4648 0.07670 0.07023 -0.0401 1.0000 0.0630
-7.250 -0.4798 0.07272 0.06626 -0.0397 1.0000 0.0629
-7.000 -0.4926 0.06858 0.06206 -0.0393 1.0000 0.0631
-6.750 -0.5022 0.06438 0.05773 -0.0388 1.0000 0.0634
-6.500 -0.5088 0.06005 0.05319 -0.0384 1.0000 0.0643
-6.250 -0.5098 0.05544 0.04823 -0.0385 0.9993 0.0653
-6.000 -0.4908 0.04936 0.04143 -0.0422 0.9923 0.0669
-5.750 -0.4683 0.04496 0.03639 -0.0444 0.9857 0.0686
-5.500 -0.4413 0.04335 0.03472 -0.0458 0.9795 0.0720
-5.250 -0.4143 0.04060 0.03146 -0.0473 0.9731 0.0762
-5.000 -0.3874 0.03759 0.02760 -0.0482 0.9668 0.0800
-4.750 -0.3587 0.03625 0.02625 -0.0493 0.9604 0.0848
-4.500 -0.3282 0.03455 0.02412 -0.0503 0.9546 0.0904
-4.250 -0.2999 0.03320 0.02253 -0.0509 0.9476 0.0968
-4.000 -0.2649 0.03201 0.02106 -0.0525 0.9424 0.1047
-3.750 -0.2391 0.03108 0.02001 -0.0525 0.9345 0.1125
-3.500 -0.2043 0.03016 0.01882 -0.0538 0.9288 0.1232
-3.250 -0.1762 0.02948 0.01813 -0.0541 0.9213 0.1342
-3.000 -0.1425 0.02881 0.01739 -0.0553 0.9149 0.1482
-2.750 -0.1090 0.02824 0.01675 -0.0565 0.9084 0.1656
-2.500 -0.0785 0.02774 0.01625 -0.0572 0.9007 0.1873
-2.250 -0.0425 0.02718 0.01579 -0.0588 0.8949 0.2201
-2.000 -0.0170 0.02672 0.01549 -0.0587 0.8859 0.2634
-1.750 0.0196 0.02601 0.01515 -0.0605 0.8805 0.3415
-1.500 0.0397 0.02544 0.01506 -0.0592 0.8706 0.4414
-1.250 0.0734 0.02426 0.01508 -0.0590 0.8658 0.7028
-1.000 0.1810 0.02406 0.01483 -0.0738 0.8655 1.0000
-0.500 0.2364 0.02426 0.01451 -0.0739 0.8459 1.0000
-0.250 0.2662 0.02432 0.01437 -0.0742 0.8361 1.0000
0.000 0.2916 0.02444 0.01431 -0.0737 0.8253 1.0000
0.500 0.3536 0.02446 0.01401 -0.0744 0.8056 1.0000
0.750 0.3803 0.02451 0.01393 -0.0740 0.7943 1.0000
1.000 0.4199 0.02426 0.01356 -0.0755 0.7862 1.0000
1.500 0.4671 0.02441 0.01353 -0.0733 0.7604 1.0000
1.750 0.4956 0.02437 0.01341 -0.0729 0.7488 1.0000
2.000 0.5308 0.02416 0.01312 -0.0735 0.7391 1.0000
2.250 0.5532 0.02427 0.01319 -0.0722 0.7255 1.0000
2.500 0.5772 0.02435 0.01323 -0.0711 0.7122 1.0000
2.750 0.6028 0.02440 0.01324 -0.0703 0.6993 1.0000
3.000 0.6304 0.02439 0.01320 -0.0697 0.6867 1.0000
3.250 0.6605 0.02430 0.01307 -0.0695 0.6746 1.0000
3.500 0.6864 0.02434 0.01310 -0.0687 0.6608 1.0000
3.750 0.7098 0.02449 0.01324 -0.0675 0.6461 1.0000
4.000 0.7336 0.02463 0.01337 -0.0664 0.6313 1.0000
4.250 0.7576 0.02478 0.01351 -0.0653 0.6163 1.0000
4.500 0.7816 0.02496 0.01371 -0.0643 0.6013 1.0000
4.750 0.8054 0.02517 0.01391 -0.0632 0.5861 1.0000
5.000 0.8290 0.02541 0.01415 -0.0622 0.5709 1.0000
5.250 0.8524 0.02569 0.01445 -0.0611 0.5558 1.0000
5.500 0.8756 0.02601 0.01478 -0.0601 0.5411 1.0000
5.750 0.8987 0.02638 0.01515 -0.0590 0.5267 1.0000
6.000 0.9219 0.02677 0.01556 -0.0581 0.5127 1.0000
6.250 0.9458 0.02718 0.01600 -0.0572 0.4995 1.0000
6.500 0.9710 0.02757 0.01640 -0.0566 0.4870 1.0000
6.750 0.9911 0.02816 0.01706 -0.0553 0.4740 1.0000
7.000 1.0110 0.02880 0.01780 -0.0540 0.4617 1.0000
7.250 1.0325 0.02940 0.01846 -0.0530 0.4501 1.0000
7.500 1.0565 0.02992 0.01901 -0.0522 0.4389 1.0000
7.750 1.0761 0.03045 0.01959 -0.0508 0.4256 1.0000
8.000 1.0916 0.03095 0.02013 -0.0487 0.4099 1.0000
8.250 1.1041 0.03146 0.02063 -0.0461 0.3931 1.0000
8.500 1.1137 0.03205 0.02126 -0.0432 0.3764 1.0000
8.750 1.1242 0.03269 0.02192 -0.0406 0.3609 1.0000
9.000 1.1364 0.03334 0.02263 -0.0383 0.3471 1.0000
9.250 1.1430 0.03417 0.02357 -0.0353 0.3336 1.0000
9.500 1.1491 0.03505 0.02454 -0.0323 0.3200 1.0000
9.750 1.1545 0.03599 0.02556 -0.0294 0.3060 1.0000
10.000 1.1591 0.03702 0.02667 -0.0266 0.2918 1.0000
10.250 1.1624 0.03816 0.02792 -0.0238 0.2772 1.0000
10.500 1.1639 0.03946 0.02929 -0.0212 0.2619 1.0000
10.750 1.1642 0.04094 0.03084 -0.0186 0.2461 1.0000
11.000 1.1637 0.04259 0.03256 -0.0163 0.2300 1.0000
11.250 1.1624 0.04444 0.03445 -0.0142 0.2140 1.0000
11.500 1.1608 0.04647 0.03649 -0.0124 0.1987 1.0000
11.750 1.1595 0.04867 0.03870 -0.0109 0.1849 1.0000
12.000 1.1589 0.05100 0.04106 -0.0096 0.1730 1.0000
12.250 1.1588 0.05338 0.04344 -0.0085 0.1631 1.0000
12.500 1.1592 0.05574 0.04574 -0.0075 0.1546 1.0000
12.750 1.1590 0.05847 0.04858 -0.0067 0.1463 1.0000
13.000 1.1615 0.06082 0.05086 -0.0060 0.1399 1.0000
13.250 1.1620 0.06373 0.05396 -0.0055 0.1337 1.0000
13.500 1.1664 0.06601 0.05620 -0.0049 0.1283 1.0000
13.750 1.1654 0.06922 0.05960 -0.0047 0.1234 1.0000
14.000 1.1656 0.07229 0.06283 -0.0046 0.1187 1.0000
14.250 1.1766 0.07397 0.06441 -0.0038 0.1141 1.0000
14.500 1.1678 0.07847 0.06924 -0.0045 0.1109 1.0000
14.750 1.1603 0.08288 0.07388 -0.0053 0.1076 1.0000
15.000 1.1600 0.08624 0.07734 -0.0056 0.1042 1.0000
15.250 1.1674 0.08858 0.07967 -0.0054 0.1005 1.0000
15.500 1.1463 0.09542 0.08684 -0.0079 0.0990 1.0000
15.750 1.1195 0.10372 0.09543 -0.0116 0.0977 1.0000
16.000 1.0804 0.11516 0.10714 -0.0176 0.0972 1.0000
16.250 0.9983 0.13861 0.13071 -0.0312 0.0977 1.0000
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Polar data table (+)
Polar graphs
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