NACA 65(1)-212 (naca651212-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(1)-212 (naca651212-il) Reynolds number: 50,000 Max Cl/Cd: 28.4 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca651212-il-50000-n5.txt Download as CSV file: xf-naca651212-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(1)-212
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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4086 0.12586 0.11887 -0.0267 1.0000 0.0709
-12.250 -0.4087 0.12168 0.11470 -0.0283 1.0000 0.0672
-11.750 -0.5294 0.11830 0.11085 -0.0289 1.0000 0.0604
-11.500 -0.5256 0.11400 0.10657 -0.0300 1.0000 0.0592
-11.250 -0.5250 0.10929 0.10190 -0.0319 1.0000 0.0579
-11.000 -0.5272 0.10412 0.09677 -0.0344 1.0000 0.0567
-10.750 -0.5324 0.09824 0.09095 -0.0378 1.0000 0.0555
-10.500 -0.5420 0.09126 0.08402 -0.0424 1.0000 0.0542
-10.250 -0.5625 0.08371 0.07648 -0.0479 1.0000 0.0527
-10.000 -0.5932 0.07715 0.06987 -0.0521 1.0000 0.0513
-9.500 -0.6523 0.06968 0.06202 -0.0512 1.0000 0.0497
-9.250 -0.6590 0.06625 0.05842 -0.0500 1.0000 0.0495
-9.000 -0.6654 0.06302 0.05501 -0.0483 1.0000 0.0495
-8.750 -0.6718 0.06005 0.05178 -0.0461 1.0000 0.0496
-8.500 -0.6737 0.05686 0.04848 -0.0441 1.0000 0.0502
-8.250 -0.6694 0.05427 0.04588 -0.0423 1.0000 0.0515
-8.000 -0.6675 0.05192 0.04339 -0.0400 1.0000 0.0525
-7.750 -0.6662 0.04956 0.04081 -0.0373 1.0000 0.0533
-7.500 -0.6639 0.04717 0.03814 -0.0345 1.0000 0.0537
-7.250 -0.6594 0.04481 0.03546 -0.0318 1.0000 0.0539
-7.000 -0.6523 0.04257 0.03289 -0.0293 1.0000 0.0543
-6.750 -0.6426 0.04046 0.03046 -0.0269 1.0000 0.0548
-6.500 -0.6305 0.03849 0.02815 -0.0248 1.0000 0.0556
-6.250 -0.6170 0.03682 0.02618 -0.0229 1.0000 0.0575
-6.000 -0.6018 0.03531 0.02433 -0.0210 1.0000 0.0599
-5.750 -0.5849 0.03399 0.02264 -0.0192 1.0000 0.0618
-5.500 -0.5659 0.03235 0.02102 -0.0178 1.0000 0.0635
-5.250 -0.5365 0.03099 0.01956 -0.0181 0.9965 0.0661
-5.000 -0.5035 0.02990 0.01831 -0.0190 0.9912 0.0712
-4.750 -0.4713 0.02886 0.01716 -0.0200 0.9858 0.0772
-4.500 -0.4427 0.02784 0.01606 -0.0207 0.9792 0.0835
-4.250 -0.4137 0.02685 0.01494 -0.0217 0.9730 0.0929
-4.000 -0.3871 0.02579 0.01392 -0.0225 0.9660 0.1103
-3.750 -0.3622 0.02427 0.01276 -0.0234 0.9593 0.1585
-3.500 -0.3566 0.02201 0.01304 -0.0196 0.9522 0.5792
-3.000 -0.3254 0.02473 0.01594 -0.0072 0.9384 0.7837
-2.750 -0.2938 0.02609 0.01712 -0.0036 0.9350 0.8340
-2.500 -0.2644 0.02605 0.01681 -0.0041 0.9283 0.8436
-2.250 -0.2307 0.02596 0.01643 -0.0058 0.9228 0.8526
-2.000 -0.2004 0.02585 0.01609 -0.0070 0.9170 0.8617
-1.750 -0.1697 0.02578 0.01583 -0.0081 0.9107 0.8691
-1.500 -0.1364 0.02569 0.01554 -0.0100 0.9058 0.8776
-1.250 -0.1059 0.02566 0.01537 -0.0111 0.8996 0.8845
-1.000 -0.0779 0.02559 0.01518 -0.0120 0.8935 0.8934
-0.750 -0.0341 0.02560 0.01504 -0.0156 0.8901 0.8987
-0.500 -0.0148 0.02559 0.01497 -0.0150 0.8823 0.9085
-0.250 0.0258 0.02562 0.01491 -0.0181 0.8779 0.9143
0.000 0.0556 0.02564 0.01487 -0.0193 0.8725 0.9229
0.250 0.0903 0.02572 0.01493 -0.0215 0.8666 0.9296
0.500 0.1255 0.02576 0.01494 -0.0237 0.8618 0.9375
0.750 0.1644 0.02587 0.01506 -0.0267 0.8568 0.9437
1.000 0.1965 0.02600 0.01521 -0.0286 0.8506 0.9521
1.250 0.2415 0.02608 0.01535 -0.0327 0.8466 0.9575
1.500 0.2761 0.02626 0.01559 -0.0351 0.8407 0.9655
1.750 0.3140 0.02643 0.01584 -0.0380 0.8348 0.9731
2.000 0.3577 0.02652 0.01606 -0.0418 0.8306 0.9794
2.250 0.3899 0.02681 0.01647 -0.0440 0.8233 0.9892
2.500 0.4295 0.02697 0.01679 -0.0472 0.8177 0.9980
2.750 0.4405 0.02731 0.01723 -0.0452 0.8092 1.0000
3.000 0.4557 0.02751 0.01754 -0.0437 0.8015 1.0000
3.250 0.4558 0.02791 0.01800 -0.0397 0.7910 1.0000
3.500 0.4817 0.02801 0.01824 -0.0396 0.7847 1.0000
3.750 0.4825 0.02844 0.01874 -0.0357 0.7731 1.0000
4.000 0.4959 0.02878 0.01922 -0.0337 0.7630 1.0000
4.250 0.5269 0.02882 0.01946 -0.0340 0.7553 1.0000
4.500 0.5425 0.02916 0.01996 -0.0322 0.7430 1.0000
4.750 0.5651 0.02928 0.02029 -0.0312 0.7304 1.0000
5.000 0.6068 0.02771 0.01906 -0.0302 0.7052 1.0000
5.250 0.6406 0.02342 0.01475 -0.0231 0.6118 1.0000
5.500 0.6514 0.02294 0.01428 -0.0189 0.5360 1.0000
5.750 0.6590 0.02350 0.01317 -0.0133 0.2732 1.0000
6.000 0.6509 0.02596 0.01461 -0.0093 0.1524 1.0000
6.250 0.6546 0.02779 0.01605 -0.0067 0.1134 1.0000
6.500 0.6629 0.02927 0.01740 -0.0044 0.0981 1.0000
6.750 0.6738 0.03063 0.01873 -0.0025 0.0874 1.0000
7.000 0.6868 0.03203 0.02006 -0.0010 0.0793 1.0000
7.250 0.7073 0.03328 0.02148 0.0001 0.0737 1.0000
7.500 0.7337 0.03467 0.02289 0.0004 0.0680 1.0000
7.750 0.7735 0.03617 0.02460 -0.0007 0.0619 1.0000
8.000 0.8142 0.03804 0.02663 -0.0019 0.0584 1.0000
8.250 0.8502 0.04035 0.02906 -0.0030 0.0558 1.0000
8.500 0.8782 0.04288 0.03186 -0.0032 0.0534 1.0000
8.750 0.8991 0.04526 0.03469 -0.0025 0.0513 1.0000
9.000 0.9169 0.04800 0.03783 -0.0016 0.0498 1.0000
9.250 0.9308 0.05103 0.04126 -0.0004 0.0491 1.0000
9.500 0.9399 0.05417 0.04479 0.0011 0.0487 1.0000
9.750 0.9441 0.05743 0.04843 0.0028 0.0484 1.0000
10.000 0.9435 0.06081 0.05221 0.0048 0.0483 1.0000
10.250 0.9381 0.06420 0.05592 0.0068 0.0483 1.0000
10.500 0.9268 0.06748 0.05947 0.0090 0.0482 1.0000
10.750 0.9122 0.07101 0.06323 0.0107 0.0481 1.0000
11.000 0.8945 0.07496 0.06740 0.0116 0.0483 1.0000
11.250 0.8742 0.07947 0.07211 0.0114 0.0486 1.0000
11.500 0.8518 0.08470 0.07751 0.0100 0.0490 1.0000
11.750 0.8273 0.09093 0.08384 0.0072 0.0495 1.0000
12.000 0.8028 0.09825 0.09126 0.0030 0.0502 1.0000
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Polar data table (+)
Polar graphs
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