NACA 63(2)-615 (naca632615-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63(2)-615 (naca632615-il) Reynolds number: 50,000 Max Cl/Cd: 24.85 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca632615-il-50000-n5.txt Download as CSV file: xf-naca632615-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(2)-615
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3813 0.10310 0.09570 -0.0584 1.0000 0.0667
-11.000 -0.3908 0.09805 0.09074 -0.0603 1.0000 0.0670
-10.750 -0.4043 0.09229 0.08508 -0.0625 1.0000 0.0668
-10.500 -0.4263 0.08537 0.07826 -0.0656 1.0000 0.0663
-10.000 -0.5695 0.07011 0.06303 -0.0697 1.0000 0.0603
-9.750 -0.6001 0.06834 0.06129 -0.0664 1.0000 0.0602
-9.500 -0.6258 0.06617 0.05907 -0.0635 1.0000 0.0601
-9.250 -0.6480 0.06371 0.05651 -0.0610 1.0000 0.0601
-9.000 -0.6419 0.05923 0.05171 -0.0646 0.9917 0.0613
-8.750 -0.6198 0.05651 0.04889 -0.0674 0.9845 0.0634
-8.500 -0.6043 0.05286 0.04486 -0.0702 0.9756 0.0653
-8.250 -0.5872 0.04918 0.04069 -0.0726 0.9672 0.0669
-8.000 -0.5636 0.04570 0.03657 -0.0755 0.9603 0.0696
-7.750 -0.5419 0.04328 0.03383 -0.0765 0.9522 0.0723
-7.500 -0.5111 0.04124 0.03160 -0.0785 0.9466 0.0753
-7.250 -0.4871 0.03948 0.02955 -0.0790 0.9388 0.0792
-7.000 -0.4559 0.03766 0.02737 -0.0805 0.9329 0.0835
-6.750 -0.4274 0.03634 0.02603 -0.0811 0.9267 0.0876
-6.500 -0.3998 0.03521 0.02467 -0.0814 0.9196 0.0935
-6.250 -0.3660 0.03401 0.02344 -0.0826 0.9149 0.0994
-6.000 -0.3429 0.03319 0.02252 -0.0821 0.9069 0.1062
-5.750 -0.3136 0.03222 0.02154 -0.0828 0.9009 0.1153
-5.500 -0.2821 0.03123 0.02049 -0.0840 0.8956 0.1272
-5.250 -0.2617 0.03038 0.01967 -0.0836 0.8869 0.1424
-5.000 -0.2292 0.02907 0.01853 -0.0858 0.8819 0.1733
-4.750 -0.2084 0.02771 0.01766 -0.0864 0.8739 0.2328
-4.500 -0.1833 0.02670 0.01762 -0.0869 0.8675 0.3805
-4.250 -0.1528 0.02693 0.01801 -0.0866 0.8623 0.4795
-4.000 -0.1348 0.02742 0.01848 -0.0844 0.8533 0.5275
-3.750 -0.1047 0.02798 0.01891 -0.0837 0.8480 0.5734
-3.500 -0.0896 0.02870 0.01961 -0.0803 0.8394 0.6007
-3.250 -0.0655 0.02918 0.01997 -0.0785 0.8331 0.6277
-3.000 -0.0398 0.02955 0.02022 -0.0768 0.8280 0.6482
-2.750 -0.0245 0.02986 0.02044 -0.0744 0.8189 0.6647
-2.250 0.0234 0.03006 0.02034 -0.0727 0.8061 0.6921
-2.000 0.0477 0.03009 0.02026 -0.0720 0.7997 0.7030
-1.750 0.0817 0.02994 0.01993 -0.0731 0.7956 0.7151
-1.500 0.0943 0.03021 0.02014 -0.0709 0.7862 0.7246
-1.250 0.1237 0.03014 0.01995 -0.0712 0.7810 0.7348
-1.000 0.1507 0.03016 0.01985 -0.0714 0.7753 0.7455
-0.750 0.1677 0.03037 0.02001 -0.0699 0.7672 0.7542
-0.500 0.2009 0.03027 0.01979 -0.0711 0.7629 0.7648
-0.250 0.2159 0.03056 0.02006 -0.0693 0.7548 0.7736
0.000 0.2420 0.03064 0.02006 -0.0694 0.7487 0.7836
0.250 0.2734 0.03054 0.01990 -0.0698 0.7449 0.7933
0.500 0.2845 0.03104 0.02039 -0.0680 0.7356 0.8033
0.750 0.3137 0.03107 0.02036 -0.0685 0.7305 0.8142
1.000 0.3447 0.03093 0.02019 -0.0686 0.7272 0.8239
1.250 0.3512 0.03164 0.02093 -0.0663 0.7168 0.8354
1.500 0.3815 0.03162 0.02088 -0.0668 0.7126 0.8472
1.750 0.3931 0.03213 0.02143 -0.0648 0.7044 0.8596
2.000 0.4146 0.03233 0.02165 -0.0640 0.6984 0.8724
2.250 0.4455 0.03221 0.02154 -0.0643 0.6947 0.8858
2.500 0.4502 0.03303 0.02243 -0.0619 0.6848 0.9031
2.750 0.4801 0.03306 0.02248 -0.0623 0.6801 0.9202
3.250 0.5338 0.03401 0.02358 -0.0644 0.6660 0.9696
3.500 0.5747 0.03398 0.02357 -0.0670 0.6620 1.0000
3.750 0.5878 0.03527 0.02488 -0.0672 0.6520 1.0000
4.000 0.6231 0.03554 0.02517 -0.0690 0.6471 1.0000
4.250 0.6658 0.03543 0.02510 -0.0714 0.6439 1.0000
4.500 0.6717 0.03718 0.02688 -0.0707 0.6321 1.0000
4.750 0.7115 0.03710 0.02687 -0.0725 0.6284 1.0000
5.000 0.7189 0.03887 0.02868 -0.0719 0.6170 1.0000
5.250 0.7563 0.03881 0.02871 -0.0731 0.6127 1.0000
5.500 0.7649 0.04056 0.03051 -0.0725 0.6016 1.0000
5.750 0.8005 0.04047 0.03051 -0.0734 0.5967 1.0000
6.250 0.8453 0.04194 0.03218 -0.0733 0.5802 1.0000
6.750 0.8928 0.04297 0.03343 -0.0729 0.5633 1.0000
7.000 0.9001 0.04465 0.03523 -0.0718 0.5506 1.0000
7.250 0.9452 0.04331 0.03405 -0.0722 0.5459 1.0000
7.500 0.9508 0.04497 0.03582 -0.0709 0.5322 1.0000
8.000 1.0108 0.04413 0.03532 -0.0699 0.5134 1.0000
8.250 1.0203 0.04526 0.03659 -0.0685 0.4992 1.0000
8.500 1.0350 0.04587 0.03735 -0.0672 0.4850 1.0000
8.750 1.0545 0.04592 0.03758 -0.0659 0.4707 1.0000
9.000 1.0752 0.04571 0.03752 -0.0645 0.4550 1.0000
9.250 1.0941 0.04557 0.03753 -0.0630 0.4373 1.0000
9.500 1.1163 0.04492 0.03701 -0.0614 0.4171 1.0000
9.750 1.1199 0.04631 0.03850 -0.0598 0.3932 1.0000
10.000 1.1328 0.04666 0.03888 -0.0581 0.3648 1.0000
10.250 1.1415 0.04757 0.03974 -0.0565 0.3322 1.0000
10.500 1.1483 0.04879 0.04083 -0.0550 0.2962 1.0000
10.750 1.1509 0.05064 0.04242 -0.0535 0.2602 1.0000
11.000 1.1489 0.05324 0.04479 -0.0524 0.2286 1.0000
11.250 1.1450 0.05628 0.04765 -0.0516 0.2011 1.0000
11.500 1.1408 0.05952 0.05072 -0.0510 0.1781 1.0000
11.750 1.1373 0.06287 0.05396 -0.0506 0.1584 1.0000
12.000 1.1349 0.06621 0.05720 -0.0504 0.1424 1.0000
12.250 1.1344 0.06947 0.06039 -0.0502 0.1289 1.0000
12.500 1.1354 0.07261 0.06350 -0.0501 0.1177 1.0000
12.750 1.1379 0.07559 0.06639 -0.0499 0.1090 1.0000
13.000 1.1434 0.07836 0.06925 -0.0498 0.1005 1.0000
13.250 1.1498 0.08101 0.07192 -0.0496 0.0938 1.0000
13.500 1.1577 0.08354 0.07454 -0.0494 0.0878 1.0000
13.750 1.1673 0.08588 0.07690 -0.0492 0.0828 1.0000
14.000 1.1754 0.08861 0.07985 -0.0492 0.0779 1.0000
14.250 1.1870 0.09064 0.08184 -0.0489 0.0739 1.0000
14.500 1.1944 0.09372 0.08519 -0.0490 0.0705 1.0000
14.750 1.1987 0.09714 0.08885 -0.0496 0.0673 1.0000
15.000 1.2063 0.09989 0.09166 -0.0499 0.0645 1.0000
15.250 1.2126 0.10309 0.09499 -0.0504 0.0622 1.0000
15.500 1.2052 0.10855 0.10083 -0.0524 0.0607 1.0000
15.750 1.1959 0.11439 0.10697 -0.0548 0.0593 1.0000
16.000 1.1847 0.12073 0.11357 -0.0578 0.0582 1.0000
16.250 1.1710 0.12776 0.12084 -0.0615 0.0573 1.0000
16.500 1.1524 0.13627 0.12959 -0.0665 0.0568 1.0000
16.750 1.1157 0.14995 0.14356 -0.0753 0.0574 1.0000
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Polar data table (+)
Polar graphs
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