NACA 65(1)-212 (naca651212-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(1)-212 (naca651212-il) Reynolds number: 100,000 Max Cl/Cd: 42.15 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca651212-il-100000-n5.txt Download as CSV file: xf-naca651212-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4366 0.09476 0.08988 -0.0369 1.0000 0.0352
-11.000 -0.4455 0.08857 0.08372 -0.0397 1.0000 0.0351
-10.750 -0.4578 0.08140 0.07657 -0.0431 1.0000 0.0346
-10.250 -0.6354 0.06697 0.06142 -0.0553 1.0000 0.0289
-10.000 -0.6511 0.06350 0.05785 -0.0548 1.0000 0.0288
-9.750 -0.6661 0.06048 0.05472 -0.0530 1.0000 0.0287
-9.500 -0.6791 0.05734 0.05137 -0.0510 1.0000 0.0288
-9.250 -0.6902 0.05431 0.04811 -0.0485 1.0000 0.0291
-9.000 -0.6958 0.05109 0.04475 -0.0463 1.0000 0.0295
-8.750 -0.6978 0.04865 0.04219 -0.0438 1.0000 0.0300
-8.500 -0.6958 0.04691 0.04041 -0.0414 1.0000 0.0308
-8.250 -0.6966 0.04515 0.03850 -0.0383 1.0000 0.0314
-8.000 -0.6992 0.04313 0.03627 -0.0347 1.0000 0.0318
-7.750 -0.6858 0.04008 0.03281 -0.0342 0.9953 0.0320
-7.500 -0.6608 0.03688 0.02913 -0.0355 0.9879 0.0324
-7.250 -0.6333 0.03414 0.02596 -0.0367 0.9814 0.0331
-7.000 -0.6031 0.03188 0.02331 -0.0381 0.9758 0.0345
-6.750 -0.5732 0.03008 0.02110 -0.0391 0.9695 0.0365
-6.500 -0.5399 0.02823 0.01889 -0.0405 0.9648 0.0376
-6.250 -0.5070 0.02668 0.01707 -0.0417 0.9599 0.0384
-6.000 -0.4761 0.02479 0.01517 -0.0427 0.9546 0.0397
-5.750 -0.4432 0.02351 0.01387 -0.0442 0.9502 0.0422
-5.500 -0.4154 0.02262 0.01292 -0.0446 0.9430 0.0456
-5.250 -0.3850 0.02165 0.01187 -0.0454 0.9373 0.0482
-5.000 -0.3589 0.02074 0.01089 -0.0455 0.9303 0.0505
-4.750 -0.3329 0.01992 0.01004 -0.0457 0.9233 0.0547
-4.500 -0.3055 0.01935 0.00935 -0.0460 0.9170 0.0617
-4.250 -0.2816 0.01865 0.00865 -0.0457 0.9092 0.0705
-4.000 -0.2550 0.01785 0.00796 -0.0459 0.9035 0.0949
-3.750 -0.2417 0.01614 0.00724 -0.0446 0.8945 0.2832
-3.500 -0.2271 0.01499 0.00738 -0.0422 0.8883 0.5653
-3.250 -0.2070 0.01518 0.00775 -0.0399 0.8805 0.6528
-3.000 -0.1848 0.01578 0.00847 -0.0369 0.8755 0.7158
-2.750 -0.1655 0.01638 0.00907 -0.0336 0.8682 0.7487
-2.500 -0.1391 0.01647 0.00903 -0.0329 0.8627 0.7615
-2.250 -0.1116 0.01642 0.00885 -0.0328 0.8575 0.7685
-2.000 -0.0864 0.01636 0.00866 -0.0325 0.8507 0.7752
-1.750 -0.0576 0.01630 0.00850 -0.0325 0.8461 0.7805
-1.500 -0.0326 0.01624 0.00833 -0.0324 0.8397 0.7880
-1.250 -0.0058 0.01623 0.00826 -0.0321 0.8342 0.7926
-1.000 0.0228 0.01617 0.00811 -0.0322 0.8301 0.7985
-0.750 0.0469 0.01617 0.00807 -0.0318 0.8232 0.8050
-0.500 0.0738 0.01617 0.00803 -0.0316 0.8181 0.8102
-0.250 0.1024 0.01610 0.00791 -0.0319 0.8144 0.8168
0.000 0.1257 0.01618 0.00799 -0.0312 0.8073 0.8224
0.250 0.1527 0.01617 0.00797 -0.0311 0.8025 0.8286
0.500 0.1803 0.01616 0.00794 -0.0311 0.7984 0.8351
0.750 0.2039 0.01626 0.00808 -0.0305 0.7917 0.8409
1.000 0.2309 0.01626 0.00808 -0.0305 0.7870 0.8484
1.250 0.2578 0.01629 0.00816 -0.0303 0.7827 0.8539
1.500 0.2817 0.01640 0.00832 -0.0298 0.7761 0.8615
1.750 0.3091 0.01642 0.00839 -0.0297 0.7717 0.8677
2.000 0.3348 0.01650 0.00854 -0.0294 0.7667 0.8753
2.250 0.3591 0.01662 0.00875 -0.0289 0.7605 0.8827
2.500 0.3868 0.01663 0.00884 -0.0289 0.7561 0.8904
2.750 0.4118 0.01676 0.00908 -0.0285 0.7500 0.8982
3.000 0.4371 0.01684 0.00928 -0.0282 0.7439 0.9075
3.250 0.4685 0.01678 0.00932 -0.0286 0.7392 0.9144
3.500 0.4921 0.01690 0.00959 -0.0280 0.7299 0.9245
3.750 0.5238 0.01679 0.00964 -0.0285 0.7227 0.9323
4.000 0.5530 0.01645 0.00942 -0.0281 0.7052 0.9411
4.250 0.5805 0.01549 0.00840 -0.0262 0.6595 0.9506
4.500 0.6086 0.01501 0.00782 -0.0252 0.5927 0.9597
4.750 0.6361 0.01509 0.00756 -0.0248 0.4787 0.9699
5.000 0.6469 0.01714 0.00813 -0.0232 0.2256 0.9867
5.250 0.6536 0.01891 0.00905 -0.0211 0.0965 1.0000
5.500 0.6634 0.01980 0.00975 -0.0186 0.0715 1.0000
5.750 0.6784 0.02062 0.01056 -0.0169 0.0616 1.0000
6.250 0.7116 0.02229 0.01227 -0.0142 0.0495 1.0000
6.500 0.7283 0.02320 0.01322 -0.0129 0.0463 1.0000
6.750 0.7431 0.02440 0.01440 -0.0114 0.0439 1.0000
7.000 0.7620 0.02547 0.01555 -0.0103 0.0419 1.0000
7.250 0.7829 0.02652 0.01669 -0.0096 0.0393 1.0000
7.500 0.8046 0.02767 0.01788 -0.0090 0.0369 1.0000
7.750 0.8284 0.02906 0.01931 -0.0088 0.0355 1.0000
8.000 0.8544 0.03078 0.02106 -0.0089 0.0342 1.0000
8.250 0.8840 0.03321 0.02355 -0.0095 0.0333 1.0000
8.500 0.9088 0.03510 0.02572 -0.0092 0.0327 1.0000
8.750 0.9303 0.03700 0.02794 -0.0086 0.0318 1.0000
9.000 0.9484 0.03898 0.03027 -0.0076 0.0304 1.0000
9.250 0.9641 0.04122 0.03287 -0.0064 0.0294 1.0000
9.500 0.9769 0.04385 0.03585 -0.0051 0.0290 1.0000
9.750 0.9857 0.04663 0.03898 -0.0034 0.0286 1.0000
10.000 0.9902 0.04958 0.04229 -0.0014 0.0283 1.0000
10.250 0.9901 0.05264 0.04569 0.0008 0.0282 1.0000
10.500 0.9837 0.05567 0.04903 0.0036 0.0281 1.0000
10.750 0.9728 0.05885 0.05249 0.0062 0.0281 1.0000
11.000 0.9588 0.06230 0.05620 0.0083 0.0282 1.0000
11.250 0.9421 0.06610 0.06025 0.0097 0.0283 1.0000
11.500 0.9230 0.07037 0.06474 0.0101 0.0284 1.0000
11.750 0.9013 0.07531 0.06989 0.0094 0.0285 1.0000
12.000 0.8775 0.08110 0.07587 0.0075 0.0287 1.0000
12.250 0.8513 0.08811 0.08305 0.0040 0.0290 1.0000
12.500 0.8242 0.09662 0.09168 -0.0012 0.0295 1.0000
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Polar data table (+)
Polar graphs
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