NACA 64-215 AIRFOIL (n64215-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-215 AIRFOIL (n64215-il) Reynolds number: 50,000 Max Cl/Cd: 26.61 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64215-il-50000-n5.txt Download as CSV file: xf-n64215-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-215 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5944 0.10703 0.09935 -0.0372 1.0000 0.0615
-12.750 -0.6101 0.09931 0.09162 -0.0417 1.0000 0.0612
-12.500 -0.6325 0.09142 0.08369 -0.0466 1.0000 0.0609
-12.250 -0.6559 0.08437 0.07656 -0.0507 1.0000 0.0605
-12.000 -0.6802 0.07815 0.07023 -0.0540 1.0000 0.0602
-11.750 -0.7034 0.07284 0.06477 -0.0562 1.0000 0.0600
-11.500 -0.7249 0.06827 0.06002 -0.0574 1.0000 0.0600
-11.250 -0.7432 0.06442 0.05598 -0.0574 1.0000 0.0600
-11.000 -0.7588 0.06110 0.05245 -0.0565 1.0000 0.0601
-10.750 -0.7720 0.05816 0.04929 -0.0546 1.0000 0.0604
-10.500 -0.7791 0.05527 0.04611 -0.0529 1.0000 0.0607
-10.250 -0.7818 0.05247 0.04298 -0.0511 1.0000 0.0612
-10.000 -0.7768 0.04992 0.04023 -0.0496 1.0000 0.0622
-9.750 -0.7651 0.04791 0.03819 -0.0486 1.0000 0.0639
-9.500 -0.7550 0.04606 0.03622 -0.0472 1.0000 0.0660
-9.250 -0.7449 0.04418 0.03415 -0.0455 1.0000 0.0680
-9.000 -0.7333 0.04234 0.03207 -0.0438 1.0000 0.0699
-8.750 -0.7194 0.04063 0.03009 -0.0419 1.0000 0.0717
-8.500 -0.7029 0.03915 0.02862 -0.0405 1.0000 0.0745
-8.250 -0.6902 0.03807 0.02753 -0.0385 1.0000 0.0777
-8.000 -0.6765 0.03705 0.02641 -0.0364 1.0000 0.0812
-7.750 -0.6610 0.03614 0.02530 -0.0341 1.0000 0.0846
-7.500 -0.6506 0.03529 0.02459 -0.0316 1.0000 0.0884
-7.250 -0.6456 0.03463 0.02392 -0.0285 1.0000 0.0927
-7.000 -0.6320 0.03386 0.02301 -0.0267 0.9977 0.0986
-6.750 -0.6017 0.03257 0.02178 -0.0284 0.9878 0.1080
-6.500 -0.5742 0.03124 0.02049 -0.0300 0.9776 0.1220
-6.250 -0.5495 0.02979 0.01912 -0.0313 0.9670 0.1426
-6.000 -0.5292 0.02796 0.01764 -0.0326 0.9562 0.1809
-5.750 -0.5136 0.02567 0.01626 -0.0335 0.9460 0.2873
-5.500 -0.4959 0.02550 0.01710 -0.0312 0.9352 0.4600
-5.250 -0.4672 0.02606 0.01756 -0.0308 0.9262 0.5308
-5.000 -0.4381 0.02687 0.01823 -0.0299 0.9176 0.5754
-4.750 -0.4095 0.02804 0.01929 -0.0280 0.9091 0.6092
-4.500 -0.3796 0.02904 0.02014 -0.0266 0.9013 0.6390
-4.250 -0.3474 0.03002 0.02099 -0.0251 0.8940 0.6583
-4.000 -0.3189 0.03028 0.02105 -0.0246 0.8859 0.6737
-3.750 -0.2864 0.03050 0.02109 -0.0246 0.8788 0.6834
-3.500 -0.2622 0.03031 0.02074 -0.0243 0.8700 0.6930
-3.250 -0.2343 0.03017 0.02042 -0.0245 0.8627 0.7009
-3.000 -0.2128 0.02992 0.02003 -0.0240 0.8538 0.7091
-2.750 -0.1827 0.02979 0.01975 -0.0244 0.8475 0.7157
-2.500 -0.1668 0.02952 0.01937 -0.0233 0.8380 0.7245
-2.250 -0.1338 0.02942 0.01913 -0.0240 0.8328 0.7300
-2.000 -0.1200 0.02924 0.01887 -0.0226 0.8230 0.7384
-1.750 -0.0904 0.02910 0.01862 -0.0230 0.8174 0.7439
-1.500 -0.0704 0.02907 0.01852 -0.0222 0.8095 0.7503
-1.250 -0.0487 0.02886 0.01822 -0.0220 0.8027 0.7579
-1.000 -0.0188 0.02879 0.01808 -0.0224 0.7976 0.7628
-0.750 -0.0032 0.02882 0.01807 -0.0211 0.7889 0.7700
-0.500 0.0238 0.02871 0.01790 -0.0214 0.7839 0.7765
-0.250 0.0443 0.02882 0.01799 -0.0207 0.7772 0.7827
0.000 0.0640 0.02879 0.01792 -0.0202 0.7704 0.7909
0.250 0.0943 0.02878 0.01789 -0.0205 0.7662 0.7963
0.500 0.1077 0.02900 0.01812 -0.0191 0.7583 0.8049
0.750 0.1314 0.02911 0.01824 -0.0188 0.7529 0.8118
1.000 0.1602 0.02911 0.01823 -0.0191 0.7490 0.8191
1.250 0.1719 0.02948 0.01864 -0.0174 0.7409 0.8278
1.500 0.1958 0.02962 0.01880 -0.0171 0.7357 0.8363
1.750 0.2252 0.02966 0.01887 -0.0175 0.7322 0.8443
2.000 0.2336 0.03020 0.01947 -0.0155 0.7238 0.8553
2.250 0.2603 0.03037 0.01970 -0.0156 0.7189 0.8637
2.500 0.2903 0.03041 0.01979 -0.0161 0.7153 0.8735
2.750 0.2993 0.03108 0.02056 -0.0143 0.7063 0.8856
3.000 0.3301 0.03122 0.02078 -0.0150 0.7015 0.8954
3.250 0.3549 0.03154 0.02121 -0.0151 0.6957 0.9074
3.500 0.3764 0.03204 0.02182 -0.0152 0.6879 0.9208
3.750 0.4164 0.03211 0.02202 -0.0174 0.6837 0.9310
4.000 0.4415 0.03283 0.02289 -0.0186 0.6752 0.9452
4.250 0.4825 0.03307 0.02330 -0.0215 0.6693 0.9564
4.500 0.5271 0.03317 0.02358 -0.0247 0.6641 0.9670
4.750 0.5604 0.03386 0.02446 -0.0275 0.6541 0.9824
5.000 0.6138 0.03339 0.02421 -0.0311 0.6490 0.9919
5.250 0.6063 0.03419 0.02507 -0.0272 0.6364 1.0000
5.500 0.6105 0.03460 0.02552 -0.0243 0.6252 1.0000
5.750 0.6494 0.03374 0.02482 -0.0245 0.6171 1.0000
6.000 0.6630 0.03392 0.02511 -0.0226 0.6030 1.0000
6.250 0.6878 0.03340 0.02472 -0.0212 0.5878 1.0000
6.500 0.7232 0.03192 0.02339 -0.0201 0.5695 1.0000
6.750 0.7451 0.03108 0.02268 -0.0179 0.5468 1.0000
7.000 0.7705 0.02985 0.02155 -0.0157 0.5196 1.0000
7.250 0.7806 0.02970 0.02148 -0.0128 0.4879 1.0000
7.500 0.7829 0.03012 0.02198 -0.0097 0.4509 1.0000
7.750 0.7890 0.03041 0.02224 -0.0068 0.3934 1.0000
8.000 0.8042 0.03022 0.02116 -0.0034 0.2877 1.0000
8.250 0.7984 0.03230 0.02265 -0.0008 0.2265 1.0000
8.500 0.7935 0.03470 0.02464 0.0011 0.1859 1.0000
8.750 0.7918 0.03706 0.02671 0.0025 0.1580 1.0000
9.000 0.7941 0.03925 0.02872 0.0036 0.1370 1.0000
9.250 0.7994 0.04127 0.03062 0.0046 0.1224 1.0000
9.500 0.8074 0.04315 0.03242 0.0056 0.1110 1.0000
9.750 0.8172 0.04492 0.03407 0.0064 0.1019 1.0000
10.000 0.8337 0.04632 0.03557 0.0074 0.0936 1.0000
10.250 0.8512 0.04772 0.03689 0.0082 0.0871 1.0000
10.500 0.8735 0.04894 0.03829 0.0090 0.0807 1.0000
10.750 0.9031 0.04999 0.03924 0.0096 0.0757 1.0000
11.000 0.9285 0.05152 0.04108 0.0102 0.0708 1.0000
11.250 0.9517 0.05316 0.04279 0.0105 0.0671 1.0000
11.500 0.9802 0.05512 0.04482 0.0107 0.0643 1.0000
11.750 0.9916 0.05777 0.04786 0.0112 0.0620 1.0000
12.000 0.9990 0.06051 0.05086 0.0116 0.0598 1.0000
12.250 1.0049 0.06329 0.05385 0.0120 0.0581 1.0000
12.500 1.0102 0.06620 0.05694 0.0122 0.0569 1.0000
12.750 1.0144 0.06939 0.06029 0.0123 0.0559 1.0000
13.000 1.0174 0.07285 0.06391 0.0122 0.0552 1.0000
13.250 1.0043 0.07727 0.06861 0.0118 0.0549 1.0000
13.500 0.9871 0.08222 0.07386 0.0107 0.0547 1.0000
13.750 0.9671 0.08776 0.07967 0.0089 0.0546 1.0000
14.000 0.9433 0.09419 0.08635 0.0062 0.0546 1.0000
14.250 0.9200 0.10114 0.09348 0.0027 0.0548 1.0000
14.500 0.8957 0.10894 0.10144 -0.0016 0.0550 1.0000
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