NACA 64(2)-415 (naca642415-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(2)-415 (naca642415-il) Reynolds number: 50,000 Max Cl/Cd: 25.86 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca642415-il-50000-n5.txt Download as CSV file: xf-naca642415-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(2)-415
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4597 0.10524 0.09757 -0.0519 1.0000 0.0649
-11.750 -0.4685 0.09871 0.09109 -0.0552 1.0000 0.0645
-11.500 -0.4840 0.09116 0.08357 -0.0596 1.0000 0.0639
-11.250 -0.5093 0.08321 0.07564 -0.0645 1.0000 0.0633
-11.000 -0.5391 0.07622 0.06863 -0.0686 1.0000 0.0625
-10.750 -0.5681 0.07078 0.06313 -0.0708 1.0000 0.0619
-10.500 -0.5959 0.06674 0.05903 -0.0709 1.0000 0.0617
-10.250 -0.6239 0.06384 0.05608 -0.0689 1.0000 0.0614
-10.000 -0.6486 0.06148 0.05367 -0.0657 1.0000 0.0614
-9.750 -0.6689 0.05928 0.05136 -0.0623 1.0000 0.0615
-9.500 -0.6866 0.05727 0.04922 -0.0587 1.0000 0.0618
-9.250 -0.7012 0.05531 0.04709 -0.0550 1.0000 0.0624
-9.000 -0.7122 0.05333 0.04490 -0.0516 1.0000 0.0631
-8.750 -0.7194 0.05127 0.04258 -0.0485 1.0000 0.0639
-8.500 -0.7201 0.04896 0.03992 -0.0464 0.9990 0.0650
-8.250 -0.6956 0.04570 0.03604 -0.0485 0.9906 0.0664
-8.000 -0.6660 0.04304 0.03313 -0.0506 0.9838 0.0680
-7.750 -0.6367 0.04116 0.03111 -0.0523 0.9761 0.0709
-7.500 -0.6061 0.03933 0.02901 -0.0538 0.9689 0.0746
-7.250 -0.5728 0.03756 0.02684 -0.0552 0.9622 0.0778
-7.000 -0.5404 0.03609 0.02539 -0.0563 0.9557 0.0815
-6.750 -0.5076 0.03495 0.02414 -0.0575 0.9488 0.0873
-6.500 -0.4723 0.03383 0.02290 -0.0586 0.9433 0.0929
-6.250 -0.4451 0.03289 0.02194 -0.0589 0.9349 0.1001
-6.000 -0.4114 0.03179 0.02081 -0.0605 0.9293 0.1100
-5.750 -0.3906 0.03089 0.01987 -0.0601 0.9197 0.1210
-5.500 -0.3613 0.02957 0.01867 -0.0617 0.9134 0.1408
-5.250 -0.3444 0.02833 0.01763 -0.0613 0.9034 0.1702
-5.000 -0.3229 0.02614 0.01631 -0.0628 0.8967 0.2744
-4.750 -0.3118 0.02583 0.01711 -0.0593 0.8869 0.4607
-4.500 -0.2826 0.02634 0.01753 -0.0587 0.8805 0.5438
-4.250 -0.2639 0.02704 0.01813 -0.0560 0.8713 0.5852
-4.000 -0.2380 0.02787 0.01885 -0.0540 0.8648 0.6243
-3.750 -0.2189 0.02901 0.01994 -0.0499 0.8570 0.6541
-3.500 -0.1968 0.02976 0.02059 -0.0470 0.8498 0.6788
-3.250 -0.1654 0.03007 0.02072 -0.0463 0.8452 0.6963
-3.000 -0.1511 0.03012 0.02063 -0.0442 0.8354 0.7079
-2.750 -0.1205 0.03004 0.02037 -0.0444 0.8302 0.7162
-2.500 -0.1014 0.02991 0.02009 -0.0437 0.8221 0.7259
-2.250 -0.0758 0.02986 0.01989 -0.0433 0.8157 0.7328
-2.000 -0.0437 0.02964 0.01950 -0.0443 0.8114 0.7411
-1.750 -0.0301 0.02971 0.01950 -0.0425 0.8021 0.7484
-1.500 -0.0015 0.02959 0.01925 -0.0429 0.7969 0.7555
-1.250 0.0221 0.02952 0.01906 -0.0429 0.7910 0.7631
-1.000 0.0412 0.02961 0.01910 -0.0419 0.7836 0.7693
-0.750 0.0709 0.02947 0.01883 -0.0428 0.7791 0.7771
-0.500 0.0888 0.02962 0.01894 -0.0416 0.7720 0.7834
-0.250 0.1110 0.02969 0.01896 -0.0413 0.7658 0.7909
0.000 0.1408 0.02964 0.01883 -0.0420 0.7619 0.7978
0.250 0.1554 0.02995 0.01913 -0.0406 0.7547 0.8054
0.500 0.1780 0.03008 0.01923 -0.0404 0.7488 0.8137
0.750 0.2073 0.03008 0.01920 -0.0407 0.7451 0.8210
1.000 0.2203 0.03051 0.01963 -0.0393 0.7377 0.8302
1.250 0.2413 0.03076 0.01989 -0.0387 0.7323 0.8388
1.500 0.2702 0.03081 0.01994 -0.0391 0.7287 0.8477
1.750 0.2822 0.03134 0.02050 -0.0376 0.7215 0.8587
2.000 0.3022 0.03166 0.02086 -0.0368 0.7158 0.8687
2.250 0.3310 0.03177 0.02100 -0.0372 0.7123 0.8794
2.500 0.3434 0.03239 0.02168 -0.0359 0.7053 0.8928
2.750 0.3644 0.03278 0.02213 -0.0355 0.6993 0.9063
3.000 0.3979 0.03288 0.02230 -0.0367 0.6957 0.9190
3.250 0.4163 0.03360 0.02312 -0.0367 0.6883 0.9365
3.500 0.4497 0.03405 0.02366 -0.0388 0.6824 0.9526
3.750 0.4964 0.03414 0.02386 -0.0424 0.6789 0.9673
4.000 0.5131 0.03519 0.02500 -0.0433 0.6698 1.0000
4.250 0.5382 0.03556 0.02542 -0.0438 0.6643 1.0000
4.500 0.5758 0.03558 0.02551 -0.0456 0.6610 1.0000
4.750 0.5751 0.03719 0.02716 -0.0440 0.6495 1.0000
5.000 0.6126 0.03720 0.02726 -0.0454 0.6456 1.0000
5.250 0.6185 0.03872 0.02883 -0.0445 0.6345 1.0000
5.500 0.6554 0.03866 0.02890 -0.0456 0.6297 1.0000
5.750 0.6649 0.04001 0.03032 -0.0447 0.6183 1.0000
6.000 0.7047 0.03957 0.03004 -0.0456 0.6131 1.0000
6.250 0.7154 0.04076 0.03132 -0.0446 0.6005 1.0000
6.500 0.7631 0.03953 0.03030 -0.0455 0.5955 1.0000
6.750 0.7749 0.04040 0.03129 -0.0441 0.5817 1.0000
7.000 0.7935 0.04075 0.03178 -0.0430 0.5683 1.0000
7.250 0.8205 0.04023 0.03145 -0.0420 0.5547 1.0000
7.500 0.8513 0.03910 0.03050 -0.0407 0.5390 1.0000
7.750 0.8794 0.03789 0.02947 -0.0391 0.5201 1.0000
8.000 0.9140 0.03588 0.02763 -0.0373 0.4976 1.0000
8.250 0.9130 0.03703 0.02891 -0.0348 0.4709 1.0000
8.500 0.9188 0.03769 0.02968 -0.0326 0.4380 1.0000
8.750 0.9251 0.03847 0.03052 -0.0307 0.3948 1.0000
9.000 0.9529 0.03685 0.02831 -0.0277 0.3105 1.0000
9.500 0.9458 0.04147 0.03194 -0.0238 0.2042 1.0000
9.750 0.9410 0.04434 0.03451 -0.0225 0.1726 1.0000
10.000 0.9395 0.04708 0.03705 -0.0216 0.1489 1.0000
10.250 0.9404 0.04970 0.03951 -0.0207 0.1312 1.0000
10.500 0.9442 0.05211 0.04184 -0.0200 0.1176 1.0000
10.750 0.9506 0.05434 0.04400 -0.0192 0.1068 1.0000
11.000 0.9586 0.05644 0.04597 -0.0185 0.0985 1.0000
11.250 0.9718 0.05816 0.04783 -0.0178 0.0902 1.0000
11.500 0.9862 0.05983 0.04946 -0.0170 0.0840 1.0000
11.750 1.0044 0.06131 0.05110 -0.0162 0.0780 1.0000
12.000 1.0253 0.06263 0.05238 -0.0154 0.0730 1.0000
12.250 1.0482 0.06415 0.05418 -0.0147 0.0685 1.0000
12.500 1.0676 0.06585 0.05594 -0.0142 0.0649 1.0000
12.750 1.0862 0.06795 0.05819 -0.0138 0.0619 1.0000
13.000 1.0969 0.07083 0.06140 -0.0135 0.0596 1.0000
13.250 1.1047 0.07393 0.06477 -0.0134 0.0578 1.0000
13.500 1.1094 0.07713 0.06816 -0.0135 0.0563 1.0000
13.750 1.1154 0.08015 0.07129 -0.0136 0.0547 1.0000
14.000 1.1160 0.08389 0.07517 -0.0140 0.0536 1.0000
14.250 1.1017 0.08909 0.08073 -0.0152 0.0531 1.0000
14.500 1.0845 0.09487 0.08684 -0.0170 0.0527 1.0000
14.750 1.0649 0.10130 0.09357 -0.0196 0.0525 1.0000
15.000 1.0421 0.10866 0.10120 -0.0232 0.0525 1.0000
15.250 1.0169 0.11708 0.10985 -0.0278 0.0527 1.0000
15.500 0.9900 0.12676 0.11971 -0.0337 0.0530 1.0000
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Polar data table (+)
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