NACA 64(1)-212 MOD B (n64212mb-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(1)-212 MOD B (n64212mb-il) Reynolds number: 50,000 Max Cl/Cd: 25.25 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64212mb-il-50000-n5.txt Download as CSV file: xf-n64212mb-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-212 MOD B
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5865 0.08780 0.08020 -0.0342 1.0000 0.0566
-10.500 -0.5969 0.08242 0.07481 -0.0372 1.0000 0.0563
-10.250 -0.6119 0.07721 0.06956 -0.0401 1.0000 0.0559
-10.000 -0.6285 0.07263 0.06492 -0.0419 1.0000 0.0555
-9.750 -0.6459 0.06875 0.06095 -0.0423 1.0000 0.0552
-9.500 -0.6598 0.06503 0.05709 -0.0420 1.0000 0.0550
-9.250 -0.6689 0.06138 0.05323 -0.0414 1.0000 0.0548
-9.000 -0.6738 0.05788 0.04948 -0.0405 1.0000 0.0547
-8.750 -0.6745 0.05455 0.04586 -0.0394 1.0000 0.0547
-8.500 -0.6718 0.05138 0.04236 -0.0381 1.0000 0.0548
-8.250 -0.6659 0.04844 0.03909 -0.0367 1.0000 0.0552
-8.000 -0.6580 0.04576 0.03601 -0.0351 1.0000 0.0560
-7.750 -0.6481 0.04330 0.03318 -0.0334 1.0000 0.0571
-7.500 -0.6334 0.04131 0.03116 -0.0321 1.0000 0.0585
-7.250 -0.6186 0.03950 0.02923 -0.0306 1.0000 0.0599
-7.000 -0.6032 0.03767 0.02720 -0.0290 1.0000 0.0612
-6.750 -0.5866 0.03592 0.02523 -0.0273 1.0000 0.0624
-6.500 -0.5695 0.03437 0.02347 -0.0256 1.0000 0.0643
-6.250 -0.5521 0.03300 0.02189 -0.0237 1.0000 0.0669
-6.000 -0.5351 0.03178 0.02073 -0.0221 1.0000 0.0697
-5.750 -0.5177 0.03071 0.01963 -0.0202 1.0000 0.0727
-5.500 -0.5003 0.02977 0.01857 -0.0182 1.0000 0.0760
-5.250 -0.4849 0.02885 0.01768 -0.0161 1.0000 0.0800
-5.000 -0.4707 0.02803 0.01686 -0.0140 1.0000 0.0849
-4.750 -0.4562 0.02731 0.01602 -0.0119 1.0000 0.0904
-4.500 -0.4435 0.02642 0.01522 -0.0100 1.0000 0.0975
-4.250 -0.4296 0.02560 0.01440 -0.0082 1.0000 0.1067
-4.000 -0.4142 0.02471 0.01356 -0.0069 0.9996 0.1214
-3.750 -0.3841 0.02313 0.01240 -0.0089 0.9924 0.1702
-3.500 -0.3657 0.02091 0.01222 -0.0085 0.9853 0.4860
-3.250 -0.3405 0.02125 0.01279 -0.0069 0.9771 0.6057
-3.000 -0.3183 0.02205 0.01370 -0.0040 0.9692 0.6822
-2.750 -0.3016 0.02332 0.01512 0.0018 0.9614 0.7424
-2.500 -0.2808 0.02400 0.01574 0.0053 0.9539 0.7772
-2.250 -0.2495 0.02404 0.01558 0.0047 0.9475 0.7911
-2.000 -0.2211 0.02398 0.01535 0.0042 0.9404 0.8038
-1.750 -0.1898 0.02400 0.01522 0.0034 0.9338 0.8135
-1.500 -0.1563 0.02398 0.01505 0.0019 0.9282 0.8236
-1.250 -0.1294 0.02394 0.01491 0.0017 0.9200 0.8338
-1.000 -0.0873 0.02390 0.01474 -0.0009 0.9098 0.8423
-0.750 -0.0368 0.02370 0.01441 -0.0045 0.8930 0.8503
-0.500 0.0095 0.02335 0.01395 -0.0069 0.8722 0.8578
-0.250 0.0511 0.02298 0.01351 -0.0084 0.8533 0.8661
0.000 0.0874 0.02267 0.01314 -0.0092 0.8365 0.8748
0.250 0.1214 0.02233 0.01277 -0.0095 0.8192 0.8844
0.500 0.1564 0.02197 0.01238 -0.0100 0.8003 0.8933
0.750 0.1879 0.02159 0.01197 -0.0097 0.7798 0.9040
1.000 0.2223 0.02117 0.01152 -0.0099 0.7544 0.9133
1.250 0.2551 0.02073 0.01104 -0.0098 0.7231 0.9237
1.500 0.2859 0.02039 0.01067 -0.0097 0.6847 0.9353
1.750 0.3205 0.02005 0.01025 -0.0101 0.6293 0.9462
2.000 0.3560 0.01986 0.00963 -0.0104 0.5102 0.9562
2.250 0.3852 0.02055 0.00924 -0.0105 0.3863 0.9674
2.500 0.4198 0.02133 0.00955 -0.0127 0.3467 0.9792
2.750 0.4562 0.02199 0.00995 -0.0152 0.3251 0.9921
3.000 0.4808 0.02248 0.01030 -0.0155 0.3113 1.0000
3.250 0.4931 0.02290 0.01061 -0.0134 0.3023 1.0000
3.500 0.5075 0.02330 0.01095 -0.0115 0.2936 1.0000
3.750 0.5253 0.02380 0.01132 -0.0102 0.2865 1.0000
4.000 0.5470 0.02428 0.01180 -0.0094 0.2796 1.0000
4.250 0.5714 0.02486 0.01231 -0.0091 0.2736 1.0000
4.500 0.5972 0.02547 0.01288 -0.0090 0.2678 1.0000
4.750 0.6232 0.02609 0.01352 -0.0089 0.2616 1.0000
5.000 0.6500 0.02678 0.01415 -0.0089 0.2562 1.0000
5.250 0.6771 0.02754 0.01490 -0.0090 0.2516 1.0000
5.500 0.7039 0.02832 0.01580 -0.0091 0.2473 1.0000
5.750 0.7305 0.02916 0.01670 -0.0091 0.2429 1.0000
6.000 0.7573 0.03004 0.01755 -0.0092 0.2389 1.0000
6.250 0.7831 0.03101 0.01859 -0.0092 0.2348 1.0000
6.500 0.8073 0.03202 0.01984 -0.0091 0.2305 1.0000
6.750 0.8321 0.03312 0.02108 -0.0090 0.2270 1.0000
7.000 0.8570 0.03422 0.02226 -0.0089 0.2236 1.0000
7.250 0.8829 0.03538 0.02341 -0.0090 0.2203 1.0000
7.500 0.9027 0.03677 0.02515 -0.0085 0.2163 1.0000
7.750 0.9232 0.03823 0.02688 -0.0081 0.2124 1.0000
8.000 0.9442 0.03966 0.02849 -0.0077 0.2089 1.0000
8.250 0.9670 0.04096 0.02988 -0.0075 0.2054 1.0000
8.500 0.9859 0.04261 0.03172 -0.0070 0.2018 1.0000
8.750 0.9971 0.04471 0.03425 -0.0060 0.1976 1.0000
9.000 1.0114 0.04656 0.03637 -0.0053 0.1934 1.0000
9.250 1.0314 0.04791 0.03780 -0.0049 0.1893 1.0000
9.500 1.0463 0.04976 0.03982 -0.0042 0.1855 1.0000
9.750 1.0422 0.05286 0.04340 -0.0026 0.1810 1.0000
10.000 1.0472 0.05514 0.04592 -0.0015 0.1764 1.0000
10.250 1.0693 0.05613 0.04694 -0.0011 0.1722 1.0000
10.500 1.0630 0.05925 0.05034 0.0003 0.1685 1.0000
10.750 1.0289 0.06418 0.05563 0.0023 0.1657 1.0000
11.000 0.9831 0.07027 0.06190 0.0029 0.1639 1.0000
11.250 0.9014 0.08314 0.07487 -0.0031 0.1628 1.0000
11.500 0.8681 0.09258 0.08434 -0.0087 0.1588 1.0000
11.750 0.9456 0.08366 0.07551 -0.0006 0.1545 1.0000
12.000 0.8196 0.11060 0.10234 -0.0194 0.1500 1.0000
12.250 0.8104 0.11663 0.10838 -0.0226 0.1452 1.0000
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Polar data table (+)
Polar graphs
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