NACA 65(2)-415 (naca652415-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(2)-415 (naca652415-il) Reynolds number: 50,000 Max Cl/Cd: 24.04 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca652415-il-50000-n5.txt Download as CSV file: xf-naca652415-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5105 0.08500 0.07761 -0.0734 1.0000 0.0574
-11.000 -0.5307 0.08081 0.07343 -0.0741 1.0000 0.0572
-10.750 -0.5524 0.07737 0.07001 -0.0735 1.0000 0.0571
-10.500 -0.5760 0.07472 0.06739 -0.0716 1.0000 0.0569
-10.250 -0.6022 0.07287 0.06559 -0.0681 1.0000 0.0566
-10.000 -0.6325 0.07164 0.06440 -0.0632 1.0000 0.0565
-9.750 -0.6592 0.07020 0.06295 -0.0585 1.0000 0.0563
-9.500 -0.6843 0.06845 0.06112 -0.0541 1.0000 0.0563
-9.250 -0.7009 0.06594 0.05845 -0.0513 0.9983 0.0562
-9.000 -0.6997 0.06153 0.05351 -0.0531 0.9885 0.0569
-8.750 -0.6914 0.05771 0.04925 -0.0543 0.9802 0.0579
-8.500 -0.6717 0.05459 0.04594 -0.0559 0.9740 0.0591
-8.250 -0.6564 0.05166 0.04268 -0.0564 0.9664 0.0599
-8.000 -0.6346 0.04866 0.03926 -0.0576 0.9607 0.0606
-7.750 -0.6168 0.04628 0.03655 -0.0575 0.9533 0.0616
-7.500 -0.5905 0.04403 0.03390 -0.0587 0.9480 0.0641
-7.250 -0.5692 0.04214 0.03159 -0.0586 0.9413 0.0663
-7.000 -0.5415 0.04027 0.02929 -0.0590 0.9358 0.0681
-6.750 -0.5070 0.03840 0.02726 -0.0605 0.9322 0.0699
-6.500 -0.4815 0.03718 0.02598 -0.0603 0.9265 0.0725
-6.250 -0.4521 0.03616 0.02483 -0.0606 0.9212 0.0770
-6.000 -0.4162 0.03521 0.02366 -0.0615 0.9176 0.0816
-5.750 -0.3861 0.03424 0.02271 -0.0619 0.9135 0.0859
-5.500 -0.3680 0.03359 0.02198 -0.0605 0.9064 0.0918
-5.250 -0.3424 0.03270 0.02107 -0.0608 0.9016 0.0999
-5.000 -0.3237 0.03196 0.02022 -0.0599 0.8955 0.1096
-4.750 -0.3091 0.03110 0.01943 -0.0586 0.8887 0.1239
-4.500 -0.2882 0.02962 0.01832 -0.0590 0.8841 0.1639
-4.250 -0.2880 0.02782 0.01748 -0.0563 0.8761 0.2901
-4.000 -0.2784 0.02782 0.01886 -0.0511 0.8707 0.5635
-3.750 -0.2540 0.02878 0.01969 -0.0487 0.8669 0.6439
-3.500 -0.2532 0.03016 0.02111 -0.0413 0.8586 0.6918
-3.250 -0.2369 0.03226 0.02320 -0.0340 0.8542 0.7469
-3.000 -0.2038 0.03315 0.02386 -0.0323 0.8515 0.7715
-2.750 -0.2000 0.03311 0.02369 -0.0288 0.8438 0.7833
-2.500 -0.1738 0.03314 0.02352 -0.0286 0.8392 0.7913
-2.250 -0.1463 0.03295 0.02310 -0.0292 0.8356 0.8001
-2.000 -0.1332 0.03300 0.02302 -0.0271 0.8294 0.8072
-1.750 -0.1186 0.03288 0.02275 -0.0258 0.8237 0.8157
-1.500 -0.0872 0.03284 0.02255 -0.0268 0.8202 0.8211
-1.250 -0.0706 0.03281 0.02239 -0.0258 0.8151 0.8288
-1.000 -0.0569 0.03288 0.02236 -0.0241 0.8090 0.8354
-0.750 -0.0316 0.03287 0.02223 -0.0244 0.8051 0.8419
-0.500 -0.0014 0.03281 0.02205 -0.0255 0.8021 0.8484
-0.250 0.0029 0.03306 0.02226 -0.0224 0.7947 0.8559
0.000 0.0236 0.03311 0.02223 -0.0221 0.7901 0.8634
0.250 0.0548 0.03319 0.02223 -0.0232 0.7871 0.8690
0.500 0.0647 0.03343 0.02242 -0.0213 0.7810 0.8778
0.750 0.0852 0.03366 0.02263 -0.0209 0.7759 0.8847
1.000 0.1122 0.03378 0.02270 -0.0214 0.7722 0.8923
1.250 0.1463 0.03389 0.02278 -0.0231 0.7695 0.8986
1.500 0.1488 0.03439 0.02329 -0.0203 0.7616 0.9097
1.750 0.1787 0.03465 0.02355 -0.0216 0.7576 0.9170
2.000 0.2116 0.03482 0.02371 -0.0231 0.7545 0.9253
2.250 0.2285 0.03539 0.02432 -0.0229 0.7479 0.9357
2.500 0.2588 0.03580 0.02477 -0.0246 0.7430 0.9446
2.750 0.2971 0.03609 0.02510 -0.0273 0.7395 0.9530
3.000 0.3271 0.03667 0.02575 -0.0293 0.7340 0.9633
3.250 0.3590 0.03729 0.02646 -0.0318 0.7279 0.9737
3.500 0.4020 0.03763 0.02690 -0.0355 0.7239 0.9830
3.750 0.4234 0.03825 0.02760 -0.0364 0.7169 1.0000
4.000 0.4316 0.03860 0.02797 -0.0344 0.7098 1.0000
4.250 0.4625 0.03876 0.02818 -0.0354 0.7060 1.0000
4.750 0.4977 0.03992 0.02947 -0.0347 0.6910 1.0000
5.000 0.5080 0.04088 0.03048 -0.0337 0.6811 1.0000
5.250 0.5410 0.04114 0.03087 -0.0349 0.6757 1.0000
5.500 0.5548 0.04206 0.03188 -0.0343 0.6656 1.0000
5.750 0.5889 0.04222 0.03218 -0.0354 0.6597 1.0000
6.000 0.6030 0.04312 0.03319 -0.0347 0.6486 1.0000
6.250 0.6420 0.04291 0.03318 -0.0358 0.6428 1.0000
6.500 0.6558 0.04374 0.03414 -0.0349 0.6301 1.0000
6.750 0.6762 0.04421 0.03477 -0.0343 0.6183 1.0000
7.000 0.7189 0.04331 0.03414 -0.0351 0.6111 1.0000
7.500 0.7630 0.04308 0.03432 -0.0329 0.5815 1.0000
7.750 0.7925 0.04146 0.03294 -0.0311 0.5614 1.0000
8.000 0.8131 0.03958 0.03123 -0.0279 0.5293 1.0000
8.250 0.8244 0.03879 0.03055 -0.0248 0.4880 1.0000
8.500 0.8340 0.03885 0.03067 -0.0224 0.4358 1.0000
8.750 0.8696 0.03618 0.02707 -0.0186 0.2962 1.0000
9.000 0.8622 0.03870 0.02886 -0.0160 0.2148 1.0000
9.250 0.8546 0.04164 0.03129 -0.0141 0.1632 1.0000
9.500 0.8517 0.04440 0.03371 -0.0127 0.1307 1.0000
9.750 0.8539 0.04683 0.03596 -0.0116 0.1116 1.0000
10.000 0.8594 0.04902 0.03806 -0.0106 0.0992 1.0000
10.250 0.8672 0.05105 0.04003 -0.0097 0.0900 1.0000
10.500 0.8786 0.05281 0.04180 -0.0088 0.0823 1.0000
10.750 0.8947 0.05426 0.04331 -0.0079 0.0766 1.0000
11.000 0.9137 0.05556 0.04468 -0.0071 0.0710 1.0000
11.250 0.9398 0.05656 0.04572 -0.0064 0.0662 1.0000
11.500 0.9768 0.05729 0.04669 -0.0058 0.0620 1.0000
11.750 1.0062 0.05862 0.04804 -0.0055 0.0584 1.0000
12.000 1.0343 0.06052 0.05017 -0.0053 0.0556 1.0000
12.250 1.0546 0.06300 0.05300 -0.0050 0.0537 1.0000
12.500 1.0698 0.06586 0.05618 -0.0046 0.0525 1.0000
12.750 1.0779 0.06896 0.05957 -0.0042 0.0514 1.0000
13.000 1.0817 0.07220 0.06306 -0.0038 0.0505 1.0000
13.250 1.0822 0.07558 0.06665 -0.0035 0.0495 1.0000
13.500 1.0818 0.07907 0.07032 -0.0034 0.0487 1.0000
14.000 1.0662 0.08753 0.07921 -0.0040 0.0476 1.0000
14.250 1.0482 0.09271 0.08469 -0.0050 0.0475 1.0000
14.500 1.0281 0.09843 0.09068 -0.0067 0.0475 1.0000
14.750 1.0072 0.10465 0.09712 -0.0091 0.0476 1.0000
15.000 0.9855 0.11150 0.10417 -0.0123 0.0477 1.0000
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Polar data table (+)
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