NACA 64(1)-212 (n64212-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(1)-212 (n64212-il) Reynolds number: 100,000 Max Cl/Cd: 45.88 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64212-il-100000-n5.txt Download as CSV file: xf-n64212-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6049 0.09003 0.08476 -0.0334 1.0000 0.0319
-11.250 -0.6173 0.08310 0.07781 -0.0379 1.0000 0.0316
-11.000 -0.6340 0.07639 0.07108 -0.0424 1.0000 0.0314
-10.750 -0.6527 0.07050 0.06511 -0.0462 1.0000 0.0311
-10.500 -0.6732 0.06536 0.05984 -0.0489 1.0000 0.0310
-10.250 -0.6916 0.06125 0.05560 -0.0498 1.0000 0.0310
-10.000 -0.7099 0.05775 0.05194 -0.0491 1.0000 0.0309
-9.750 -0.7219 0.05429 0.04825 -0.0479 1.0000 0.0309
-9.500 -0.7286 0.05080 0.04448 -0.0467 1.0000 0.0310
-9.250 -0.7315 0.04738 0.04071 -0.0452 1.0000 0.0311
-9.000 -0.7298 0.04419 0.03715 -0.0437 1.0000 0.0313
-8.750 -0.7246 0.04126 0.03380 -0.0420 1.0000 0.0316
-8.500 -0.7167 0.03861 0.03078 -0.0403 1.0000 0.0322
-8.250 -0.7052 0.03642 0.02849 -0.0390 1.0000 0.0332
-8.000 -0.6925 0.03490 0.02686 -0.0375 1.0000 0.0344
-7.750 -0.6797 0.03330 0.02509 -0.0358 1.0000 0.0355
-7.500 -0.6670 0.03160 0.02317 -0.0339 1.0000 0.0363
-7.250 -0.6541 0.03000 0.02133 -0.0318 1.0000 0.0371
-7.000 -0.6408 0.02858 0.01970 -0.0297 1.0000 0.0380
-6.750 -0.6112 0.02691 0.01779 -0.0305 0.9946 0.0394
-6.500 -0.5773 0.02543 0.01610 -0.0321 0.9875 0.0416
-6.250 -0.5447 0.02407 0.01476 -0.0339 0.9803 0.0446
-6.000 -0.5097 0.02286 0.01349 -0.0358 0.9741 0.0476
-5.750 -0.4772 0.02184 0.01236 -0.0371 0.9662 0.0508
-5.500 -0.4451 0.02078 0.01133 -0.0388 0.9587 0.0559
-5.250 -0.4129 0.01994 0.01040 -0.0401 0.9507 0.0617
-5.000 -0.3833 0.01910 0.00954 -0.0411 0.9416 0.0696
-4.750 -0.3513 0.01828 0.00873 -0.0424 0.9341 0.0830
-4.500 -0.3250 0.01743 0.00799 -0.0427 0.9237 0.1108
-4.250 -0.3009 0.01596 0.00719 -0.0433 0.9145 0.2333
-4.000 -0.2810 0.01465 0.00700 -0.0426 0.9048 0.4680
-3.750 -0.2556 0.01454 0.00704 -0.0418 0.8952 0.5458
-3.250 -0.2044 0.01483 0.00740 -0.0397 0.8775 0.6459
-3.000 -0.1797 0.01513 0.00773 -0.0380 0.8694 0.6794
-2.750 -0.1537 0.01524 0.00775 -0.0370 0.8606 0.6960
-2.500 -0.1265 0.01519 0.00758 -0.0368 0.8522 0.7053
-2.250 -0.0990 0.01514 0.00744 -0.0365 0.8442 0.7134
-2.000 -0.0721 0.01509 0.00727 -0.0363 0.8356 0.7227
-1.750 -0.0446 0.01503 0.00714 -0.0360 0.8283 0.7290
-1.500 -0.0178 0.01499 0.00702 -0.0358 0.8198 0.7369
-1.250 0.0096 0.01494 0.00689 -0.0356 0.8127 0.7435
-1.000 0.0362 0.01491 0.00682 -0.0354 0.8043 0.7508
-0.750 0.0635 0.01487 0.00672 -0.0351 0.7973 0.7580
-0.500 0.0898 0.01487 0.00670 -0.0348 0.7896 0.7656
-0.250 0.1169 0.01485 0.00665 -0.0346 0.7827 0.7732
0.000 0.1433 0.01487 0.00665 -0.0343 0.7753 0.7806
0.250 0.1699 0.01487 0.00664 -0.0340 0.7681 0.7887
0.500 0.1964 0.01489 0.00667 -0.0337 0.7615 0.7971
0.750 0.2226 0.01493 0.00673 -0.0333 0.7545 0.8053
1.000 0.2497 0.01494 0.00673 -0.0331 0.7489 0.8141
1.250 0.2749 0.01502 0.00688 -0.0326 0.7409 0.8225
1.500 0.3018 0.01504 0.00691 -0.0323 0.7353 0.8325
1.750 0.3269 0.01514 0.00709 -0.0318 0.7283 0.8415
2.000 0.3530 0.01519 0.00720 -0.0313 0.7221 0.8511
2.250 0.3789 0.01527 0.00733 -0.0309 0.7159 0.8621
2.500 0.4040 0.01535 0.00752 -0.0303 0.7088 0.8721
2.750 0.4307 0.01537 0.00761 -0.0298 0.7028 0.8828
3.000 0.4555 0.01546 0.00782 -0.0292 0.6940 0.8949
3.250 0.4828 0.01548 0.00790 -0.0289 0.6876 0.9074
3.500 0.5094 0.01557 0.00816 -0.0287 0.6787 0.9203
3.750 0.5390 0.01556 0.00826 -0.0288 0.6693 0.9333
4.000 0.5697 0.01541 0.00819 -0.0290 0.6523 0.9466
4.250 0.6021 0.01509 0.00791 -0.0293 0.6254 0.9600
4.500 0.6350 0.01484 0.00764 -0.0298 0.5848 0.9755
4.750 0.6679 0.01478 0.00752 -0.0308 0.5353 0.9984
5.000 0.6864 0.01496 0.00761 -0.0292 0.4863 1.0000
5.250 0.7013 0.01551 0.00769 -0.0270 0.3756 1.0000
5.500 0.7078 0.01715 0.00837 -0.0245 0.2260 1.0000
5.750 0.7191 0.01872 0.00934 -0.0228 0.1315 1.0000
6.000 0.7345 0.01995 0.01026 -0.0215 0.0913 1.0000
6.250 0.7523 0.02096 0.01120 -0.0204 0.0744 1.0000
6.500 0.7698 0.02197 0.01218 -0.0193 0.0646 1.0000
6.750 0.7878 0.02292 0.01314 -0.0182 0.0575 1.0000
7.000 0.8050 0.02397 0.01423 -0.0170 0.0530 1.0000
7.250 0.8232 0.02494 0.01524 -0.0160 0.0483 1.0000
7.500 0.8388 0.02625 0.01649 -0.0148 0.0450 1.0000
7.750 0.8586 0.02739 0.01777 -0.0138 0.0429 1.0000
8.000 0.8792 0.02864 0.01911 -0.0131 0.0405 1.0000
8.250 0.8995 0.02985 0.02037 -0.0124 0.0380 1.0000
8.500 0.9197 0.03135 0.02182 -0.0119 0.0359 1.0000
8.750 0.9434 0.03315 0.02377 -0.0116 0.0346 1.0000
9.000 0.9670 0.03499 0.02584 -0.0112 0.0335 1.0000
9.250 0.9889 0.03705 0.02815 -0.0107 0.0326 1.0000
9.500 1.0083 0.03931 0.03070 -0.0100 0.0318 1.0000
9.750 1.0245 0.04168 0.03336 -0.0091 0.0311 1.0000
10.000 1.0373 0.04391 0.03587 -0.0080 0.0302 1.0000
10.250 1.0476 0.04601 0.03819 -0.0067 0.0293 1.0000
10.500 1.0556 0.04814 0.04050 -0.0054 0.0285 1.0000
10.750 1.0609 0.05052 0.04301 -0.0041 0.0277 1.0000
11.000 1.0610 0.05347 0.04618 -0.0023 0.0274 1.0000
11.250 1.0545 0.05668 0.04964 -0.0003 0.0272 1.0000
11.500 1.0434 0.05985 0.05311 0.0015 0.0271 1.0000
11.750 1.0304 0.06336 0.05689 0.0026 0.0271 1.0000
12.000 1.0147 0.06733 0.06112 0.0030 0.0271 1.0000
12.250 0.9973 0.07177 0.06580 0.0026 0.0271 1.0000
12.500 0.9786 0.07677 0.07102 0.0013 0.0271 1.0000
12.750 0.9591 0.08233 0.07677 -0.0009 0.0271 1.0000
13.000 0.9382 0.08866 0.08328 -0.0041 0.0272 1.0000
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Polar data table (+)
Polar graphs
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