CLARK W AIRFOIL (clarkw-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK W AIRFOIL (clarkw-il) Reynolds number: 50,000 Max Cl/Cd: 36.46 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkw-il-50000-n5.txt Download as CSV file: xf-clarkw-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK W 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3760 0.10213 0.09454 -0.0404 1.0000 0.0826
-9.000 -0.3812 0.09879 0.09128 -0.0406 1.0000 0.0810
-8.750 -0.3908 0.09532 0.08792 -0.0408 1.0000 0.0794
-8.250 -0.4490 0.08618 0.07907 -0.0432 1.0000 0.0750
-8.000 -0.4563 0.08320 0.07615 -0.0422 1.0000 0.0747
-7.750 -0.4647 0.08000 0.07300 -0.0415 1.0000 0.0743
-7.500 -0.4733 0.07651 0.06953 -0.0411 1.0000 0.0739
-7.250 -0.4811 0.07265 0.06566 -0.0409 1.0000 0.0735
-7.000 -0.4880 0.06826 0.06120 -0.0412 1.0000 0.0732
-6.750 -0.4937 0.06328 0.05607 -0.0418 1.0000 0.0733
-6.500 -0.4967 0.05806 0.05057 -0.0426 1.0000 0.0738
-6.250 -0.4951 0.05300 0.04509 -0.0433 1.0000 0.0744
-6.000 -0.4882 0.04849 0.04006 -0.0435 1.0000 0.0751
-5.750 -0.4761 0.04540 0.03666 -0.0431 1.0000 0.0757
-5.500 -0.4614 0.04289 0.03387 -0.0426 1.0000 0.0763
-5.250 -0.4335 0.04033 0.03096 -0.0444 0.9962 0.0775
-5.000 -0.4021 0.03800 0.02825 -0.0465 0.9914 0.0791
-4.750 -0.3697 0.03607 0.02593 -0.0485 0.9864 0.0819
-4.500 -0.3363 0.03420 0.02354 -0.0504 0.9817 0.0859
-4.250 -0.3037 0.03275 0.02181 -0.0519 0.9763 0.0894
-4.000 -0.2688 0.03164 0.02053 -0.0538 0.9716 0.0933
-3.750 -0.2371 0.03052 0.01914 -0.0548 0.9655 0.0983
-3.500 -0.2012 0.02960 0.01812 -0.0567 0.9605 0.1057
-3.250 -0.1694 0.02887 0.01724 -0.0578 0.9541 0.1177
-3.000 -0.1342 0.02820 0.01657 -0.0595 0.9482 0.1348
-2.750 -0.0993 0.02769 0.01604 -0.0610 0.9421 0.1608
-2.500 -0.0674 0.02746 0.01593 -0.0623 0.9344 0.1959
-2.250 -0.0324 0.02746 0.01606 -0.0641 0.9276 0.2407
-2.000 -0.0021 0.02729 0.01593 -0.0647 0.9188 0.2742
-1.750 0.0352 0.02708 0.01570 -0.0665 0.9120 0.3103
-1.500 0.0655 0.02688 0.01551 -0.0670 0.9024 0.3436
-1.250 0.1000 0.02660 0.01526 -0.0683 0.8942 0.3801
-1.000 0.1330 0.02624 0.01500 -0.0693 0.8852 0.4192
-0.750 0.1635 0.02581 0.01475 -0.0697 0.8758 0.4633
-0.500 0.1970 0.02502 0.01444 -0.0706 0.8680 0.5402
-0.250 0.2569 0.02404 0.01441 -0.0755 0.8610 1.0000
0.000 0.2942 0.02404 0.01414 -0.0770 0.8519 1.0000
0.250 0.3213 0.02415 0.01406 -0.0768 0.8400 1.0000
0.500 0.3546 0.02415 0.01387 -0.0774 0.8301 1.0000
0.750 0.3875 0.02412 0.01369 -0.0780 0.8199 1.0000
1.000 0.4135 0.02420 0.01366 -0.0774 0.8072 1.0000
1.250 0.4431 0.02420 0.01356 -0.0773 0.7958 1.0000
1.500 0.4782 0.02404 0.01330 -0.0780 0.7861 1.0000
2.000 0.5288 0.02417 0.01331 -0.0763 0.7590 1.0000
2.250 0.5568 0.02415 0.01325 -0.0758 0.7462 1.0000
2.500 0.5877 0.02403 0.01309 -0.0757 0.7342 1.0000
2.750 0.6167 0.02396 0.01298 -0.0752 0.7210 1.0000
3.000 0.6419 0.02402 0.01303 -0.0743 0.7060 1.0000
3.250 0.6675 0.02407 0.01306 -0.0734 0.6909 1.0000
3.500 0.6934 0.02413 0.01310 -0.0725 0.6757 1.0000
3.750 0.7195 0.02420 0.01317 -0.0717 0.6602 1.0000
4.000 0.7455 0.02429 0.01325 -0.0709 0.6446 1.0000
4.250 0.7713 0.02442 0.01337 -0.0700 0.6287 1.0000
4.500 0.7969 0.02458 0.01354 -0.0692 0.6130 1.0000
4.750 0.8223 0.02479 0.01374 -0.0684 0.5972 1.0000
5.000 0.8473 0.02504 0.01399 -0.0675 0.5816 1.0000
5.250 0.8721 0.02534 0.01431 -0.0667 0.5663 1.0000
5.500 0.8967 0.02567 0.01465 -0.0658 0.5513 1.0000
5.750 0.9214 0.02604 0.01503 -0.0650 0.5371 1.0000
6.000 0.9463 0.02642 0.01545 -0.0643 0.5231 1.0000
6.250 0.9720 0.02681 0.01584 -0.0636 0.5098 1.0000
6.500 0.9940 0.02736 0.01647 -0.0626 0.4959 1.0000
6.750 1.0157 0.02794 0.01714 -0.0615 0.4821 1.0000
7.000 1.0373 0.02850 0.01776 -0.0604 0.4680 1.0000
7.250 1.0578 0.02901 0.01831 -0.0590 0.4523 1.0000
7.750 1.0954 0.03010 0.01950 -0.0557 0.4198 1.0000
8.000 1.1136 0.03072 0.02019 -0.0541 0.4046 1.0000
8.250 1.1313 0.03138 0.02093 -0.0525 0.3898 1.0000
8.500 1.1474 0.03206 0.02172 -0.0506 0.3745 1.0000
8.750 1.1607 0.03275 0.02250 -0.0484 0.3578 1.0000
9.000 1.1709 0.03348 0.02330 -0.0458 0.3399 1.0000
9.250 1.1785 0.03425 0.02412 -0.0429 0.3211 1.0000
9.500 1.1833 0.03506 0.02496 -0.0397 0.3025 1.0000
9.750 1.1863 0.03602 0.02592 -0.0364 0.2840 1.0000
10.000 1.1872 0.03726 0.02729 -0.0333 0.2642 1.0000
10.250 1.1882 0.03864 0.02872 -0.0305 0.2442 1.0000
10.500 1.1884 0.04019 0.03026 -0.0279 0.2245 1.0000
10.750 1.1878 0.04201 0.03205 -0.0256 0.2052 1.0000
11.000 1.1866 0.04408 0.03414 -0.0235 0.1864 1.0000
11.250 1.1848 0.04637 0.03640 -0.0217 0.1701 1.0000
11.500 1.1824 0.04887 0.03886 -0.0202 0.1562 1.0000
11.750 1.1799 0.05154 0.04151 -0.0188 0.1446 1.0000
12.000 1.1772 0.05430 0.04417 -0.0176 0.1353 1.0000
12.250 1.1764 0.05713 0.04709 -0.0166 0.1259 1.0000
12.500 1.1755 0.05997 0.04994 -0.0157 0.1186 1.0000
12.750 1.1753 0.06286 0.05290 -0.0150 0.1115 1.0000
13.000 1.1767 0.06561 0.05566 -0.0142 0.1059 1.0000
13.250 1.1771 0.06868 0.05892 -0.0138 0.1003 1.0000
13.500 1.1797 0.07130 0.06151 -0.0132 0.0956 1.0000
13.750 1.1788 0.07470 0.06515 -0.0130 0.0914 1.0000
14.000 1.1770 0.07824 0.06890 -0.0130 0.0876 1.0000
14.250 1.1788 0.08114 0.07185 -0.0128 0.0840 1.0000
14.500 1.1786 0.08454 0.07535 -0.0129 0.0810 1.0000
14.750 1.1684 0.08961 0.08074 -0.0141 0.0786 1.0000
15.000 1.1587 0.09475 0.08612 -0.0155 0.0765 1.0000
15.250 1.1502 0.09979 0.09133 -0.0171 0.0746 1.0000
15.500 1.1489 0.10352 0.09513 -0.0179 0.0723 1.0000
15.750 1.1442 0.10803 0.09971 -0.0193 0.0705 1.0000
16.000 1.1188 0.11694 0.10892 -0.0239 0.0700 1.0000
16.250 1.0874 0.12793 0.12017 -0.0302 0.0699 1.0000
16.500 1.0465 0.14257 0.13501 -0.0390 0.0702 1.0000
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