NACA 63(2)-615 (naca632615-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63(2)-615 (naca632615-il) Reynolds number: 100,000 Max Cl/Cd: 55.59 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca632615-il-100000-n5.txt Download as CSV file: xf-naca632615-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4633 0.08418 0.07881 -0.0694 1.0000 0.0368
-11.750 -0.4953 0.07516 0.06976 -0.0749 1.0000 0.0365
-11.500 -0.5250 0.06837 0.06293 -0.0788 1.0000 0.0362
-11.250 -0.5573 0.06292 0.05741 -0.0810 1.0000 0.0361
-11.000 -0.5844 0.05950 0.05395 -0.0806 1.0000 0.0359
-10.750 -0.6149 0.05741 0.05186 -0.0777 1.0000 0.0358
-10.500 -0.6373 0.05374 0.04798 -0.0792 0.9913 0.0358
-10.250 -0.6395 0.04810 0.04178 -0.0849 0.9765 0.0364
-10.000 -0.6329 0.04359 0.03667 -0.0881 0.9651 0.0370
-9.750 -0.6077 0.04132 0.03429 -0.0906 0.9594 0.0381
-9.500 -0.5861 0.03950 0.03232 -0.0921 0.9509 0.0395
-9.250 -0.5588 0.03701 0.02945 -0.0948 0.9459 0.0415
-9.000 -0.5391 0.03463 0.02658 -0.0955 0.9368 0.0432
-8.750 -0.5095 0.03262 0.02439 -0.0974 0.9319 0.0448
-8.500 -0.4838 0.03139 0.02307 -0.0982 0.9246 0.0469
-8.250 -0.4555 0.02997 0.02141 -0.0992 0.9182 0.0495
-8.000 -0.4229 0.02840 0.01956 -0.1007 0.9140 0.0518
-7.750 -0.3998 0.02738 0.01859 -0.1006 0.9054 0.0541
-7.500 -0.3695 0.02635 0.01744 -0.1016 0.8998 0.0574
-7.250 -0.3416 0.02540 0.01629 -0.1019 0.8934 0.0604
-7.000 -0.3167 0.02446 0.01543 -0.1020 0.8858 0.0636
-6.750 -0.2861 0.02360 0.01450 -0.1029 0.8808 0.0679
-6.500 -0.2642 0.02293 0.01376 -0.1022 0.8721 0.0716
-6.250 -0.2368 0.02216 0.01300 -0.1027 0.8660 0.0769
-6.000 -0.2116 0.02156 0.01231 -0.1026 0.8588 0.0827
-5.750 -0.1869 0.02085 0.01162 -0.1027 0.8515 0.0906
-5.500 -0.1574 0.02011 0.01087 -0.1035 0.8465 0.1031
-5.250 -0.1352 0.01952 0.01034 -0.1031 0.8377 0.1210
-5.000 -0.1074 0.01866 0.00965 -0.1039 0.8318 0.1625
-4.750 -0.0820 0.01768 0.00909 -0.1046 0.8251 0.2486
-4.500 -0.0567 0.01694 0.00889 -0.1050 0.8180 0.3679
-4.250 -0.0270 0.01673 0.00885 -0.1053 0.8129 0.4450
-4.000 -0.0015 0.01678 0.00893 -0.1048 0.8053 0.4899
-3.750 0.0264 0.01686 0.00899 -0.1045 0.7991 0.5255
-3.500 0.0559 0.01697 0.00901 -0.1044 0.7941 0.5561
-3.250 0.0799 0.01718 0.00922 -0.1034 0.7863 0.5764
-3.000 0.1079 0.01728 0.00924 -0.1030 0.7807 0.5943
-2.750 0.1349 0.01739 0.00928 -0.1026 0.7746 0.6100
-2.500 0.1606 0.01749 0.00932 -0.1020 0.7677 0.6221
-2.250 0.1893 0.01748 0.00922 -0.1019 0.7626 0.6310
-2.000 0.2163 0.01751 0.00917 -0.1018 0.7560 0.6407
-1.750 0.2427 0.01754 0.00915 -0.1014 0.7496 0.6481
-1.500 0.2726 0.01750 0.00900 -0.1016 0.7449 0.6567
-1.250 0.2981 0.01757 0.00905 -0.1013 0.7378 0.6641
-1.000 0.3253 0.01758 0.00902 -0.1011 0.7318 0.6714
-0.750 0.3561 0.01753 0.00886 -0.1016 0.7274 0.6795
-0.500 0.3797 0.01766 0.00901 -0.1009 0.7201 0.6858
-0.250 0.4087 0.01766 0.00895 -0.1012 0.7144 0.6941
0.000 0.4373 0.01765 0.00890 -0.1011 0.7099 0.7004
0.250 0.4615 0.01779 0.00907 -0.1006 0.7027 0.7079
0.500 0.4898 0.01782 0.00907 -0.1007 0.6973 0.7153
0.750 0.5175 0.01785 0.00907 -0.1005 0.6926 0.7222
1.000 0.5431 0.01800 0.00925 -0.1004 0.6855 0.7307
1.250 0.5694 0.01805 0.00932 -0.1000 0.6803 0.7372
1.500 0.5983 0.01811 0.00935 -0.1002 0.6755 0.7456
1.750 0.6213 0.01829 0.00960 -0.0994 0.6685 0.7527
2.000 0.6493 0.01835 0.00968 -0.0994 0.6634 0.7610
2.250 0.6762 0.01844 0.00978 -0.0992 0.6584 0.7687
2.500 0.6998 0.01864 0.01006 -0.0986 0.6515 0.7773
2.750 0.7270 0.01871 0.01016 -0.0984 0.6464 0.7854
3.000 0.7532 0.01884 0.01033 -0.0981 0.6410 0.7943
3.250 0.7762 0.01904 0.01062 -0.0974 0.6342 0.8029
3.500 0.8041 0.01910 0.01071 -0.0973 0.6291 0.8125
3.750 0.8268 0.01928 0.01099 -0.0964 0.6228 0.8214
4.000 0.8513 0.01946 0.01125 -0.0959 0.6162 0.8319
4.250 0.8779 0.01947 0.01129 -0.0954 0.6113 0.8416
4.500 0.8976 0.01974 0.01171 -0.0941 0.6038 0.8525
4.750 0.9222 0.01983 0.01187 -0.0934 0.5976 0.8644
5.000 0.9451 0.01992 0.01206 -0.0924 0.5914 0.8767
5.250 0.9641 0.02008 0.01235 -0.0908 0.5835 0.8906
5.500 0.9896 0.01999 0.01230 -0.0900 0.5771 0.9059
5.750 1.0059 0.02016 0.01265 -0.0881 0.5673 0.9266
6.000 1.0322 0.02008 0.01264 -0.0877 0.5586 0.9536
6.250 1.0615 0.02017 0.01282 -0.0883 0.5476 1.0000
6.500 1.0875 0.02042 0.01318 -0.0884 0.5359 1.0000
6.750 1.1143 0.02057 0.01338 -0.0885 0.5235 1.0000
7.000 1.1398 0.02073 0.01358 -0.0884 0.5095 1.0000
7.250 1.1628 0.02096 0.01386 -0.0878 0.4938 1.0000
7.500 1.1818 0.02126 0.01423 -0.0866 0.4742 1.0000
7.750 1.1988 0.02157 0.01452 -0.0850 0.4502 1.0000
8.000 1.2120 0.02205 0.01498 -0.0830 0.4224 1.0000
8.250 1.2219 0.02264 0.01550 -0.0805 0.3919 1.0000
8.500 1.2294 0.02344 0.01618 -0.0778 0.3584 1.0000
8.750 1.2334 0.02453 0.01708 -0.0749 0.3226 1.0000
9.000 1.2343 0.02593 0.01829 -0.0720 0.2863 1.0000
9.250 1.2333 0.02763 0.01980 -0.0693 0.2513 1.0000
9.500 1.2310 0.02958 0.02158 -0.0668 0.2192 1.0000
9.750 1.2288 0.03170 0.02356 -0.0647 0.1904 1.0000
10.000 1.2267 0.03398 0.02570 -0.0628 0.1649 1.0000
10.250 1.2258 0.03630 0.02792 -0.0613 0.1420 1.0000
10.500 1.2246 0.03876 0.03029 -0.0599 0.1234 1.0000
10.750 1.2246 0.04122 0.03270 -0.0588 0.1072 1.0000
11.000 1.2248 0.04376 0.03520 -0.0578 0.0951 1.0000
11.250 1.2253 0.04635 0.03779 -0.0570 0.0856 1.0000
11.500 1.2275 0.04885 0.04033 -0.0563 0.0781 1.0000
11.750 1.2276 0.05162 0.04308 -0.0557 0.0725 1.0000
12.000 1.2312 0.05410 0.04566 -0.0552 0.0671 1.0000
12.250 1.2317 0.05698 0.04854 -0.0549 0.0634 1.0000
12.500 1.2363 0.05947 0.05113 -0.0545 0.0595 1.0000
12.750 1.2396 0.06216 0.05389 -0.0544 0.0561 1.0000
13.000 1.2418 0.06502 0.05677 -0.0543 0.0534 1.0000
13.250 1.2477 0.06753 0.05942 -0.0542 0.0504 1.0000
13.500 1.2516 0.07031 0.06226 -0.0543 0.0479 1.0000
13.750 1.2546 0.07322 0.06516 -0.0544 0.0458 1.0000
14.000 1.2613 0.07577 0.06789 -0.0544 0.0436 1.0000
14.250 1.2665 0.07852 0.07075 -0.0546 0.0416 1.0000
14.500 1.2707 0.08140 0.07369 -0.0549 0.0400 1.0000
14.750 1.2765 0.08409 0.07639 -0.0550 0.0386 1.0000
15.000 1.2826 0.08690 0.07942 -0.0553 0.0371 1.0000
15.250 1.2872 0.08992 0.08259 -0.0557 0.0356 1.0000
15.500 1.2910 0.09304 0.08582 -0.0563 0.0344 1.0000
15.750 1.2952 0.09607 0.08889 -0.0570 0.0334 1.0000
16.000 1.3003 0.09901 0.09189 -0.0575 0.0324 1.0000
16.250 1.3011 0.10286 0.09602 -0.0585 0.0316 1.0000
16.500 1.3014 0.10682 0.10021 -0.0597 0.0308 1.0000
16.750 1.3003 0.11103 0.10462 -0.0612 0.0302 1.0000
17.000 1.2979 0.11552 0.10932 -0.0630 0.0296 1.0000
17.250 1.2944 0.12024 0.11422 -0.0650 0.0292 1.0000
17.500 1.2897 0.12525 0.11942 -0.0675 0.0288 1.0000
17.750 1.2839 0.13057 0.12491 -0.0703 0.0284 1.0000
18.000 1.2768 0.13624 0.13077 -0.0735 0.0282 1.0000
18.250 1.2685 0.14229 0.13698 -0.0771 0.0279 1.0000
18.500 1.2577 0.14910 0.14398 -0.0814 0.0277 1.0000
18.750 1.2422 0.15729 0.15238 -0.0870 0.0276 1.0000
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Polar data table (+)
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