NACA 0012-34 (naca001234-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: NACA 0012-34 (naca001234-il) Reynolds number: 50,000 Max Cl/Cd: 27.51 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001234-il-50000-n5.txt Download as CSV file: xf-naca001234-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0012-34
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6643 0.09163 0.08449 -0.0416 1.0000 0.0343
-11.000 -0.6781 0.08662 0.07943 -0.0435 1.0000 0.0341
-10.750 -0.6931 0.08207 0.07481 -0.0446 1.0000 0.0339
-10.500 -0.7096 0.07798 0.07062 -0.0446 1.0000 0.0338
-10.250 -0.7264 0.07437 0.06689 -0.0435 1.0000 0.0337
-10.000 -0.7432 0.07118 0.06357 -0.0411 1.0000 0.0336
-9.750 -0.7590 0.06825 0.06046 -0.0379 1.0000 0.0336
-9.500 -0.7711 0.06518 0.05717 -0.0347 1.0000 0.0336
-9.250 -0.7802 0.06214 0.05386 -0.0314 1.0000 0.0337
-9.000 -0.7863 0.05912 0.05054 -0.0279 1.0000 0.0338
-8.750 -0.7892 0.05612 0.04721 -0.0245 1.0000 0.0339
-8.500 -0.7887 0.05315 0.04388 -0.0212 1.0000 0.0340
-8.250 -0.7850 0.05026 0.04060 -0.0179 1.0000 0.0341
-8.000 -0.7778 0.04748 0.03740 -0.0149 1.0000 0.0344
-7.750 -0.7658 0.04439 0.03393 -0.0127 1.0000 0.0350
-7.500 -0.7516 0.04180 0.03118 -0.0110 1.0000 0.0368
-7.250 -0.7351 0.03970 0.02888 -0.0093 1.0000 0.0394
-7.000 -0.7138 0.03756 0.02640 -0.0079 1.0000 0.0420
-6.750 -0.6864 0.03544 0.02395 -0.0071 1.0000 0.0441
-6.500 -0.6617 0.03334 0.02182 -0.0064 1.0000 0.0479
-6.250 -0.6431 0.03194 0.02029 -0.0047 1.0000 0.0540
-6.000 -0.6267 0.03054 0.01868 -0.0024 1.0000 0.0589
-5.750 -0.6150 0.02917 0.01726 0.0003 1.0000 0.0663
-5.500 -0.6040 0.02787 0.01586 0.0030 1.0000 0.0801
-5.250 -0.5945 0.02630 0.01441 0.0060 1.0000 0.1030
-5.000 -0.5951 0.02361 0.01298 0.0098 1.0000 0.2462
-4.750 -0.5978 0.02174 0.01255 0.0155 1.0000 0.4871
-4.500 -0.5832 0.02195 0.01366 0.0214 1.0000 0.6804
-4.250 -0.5547 0.02370 0.01537 0.0261 1.0000 0.7746
-4.000 -0.5299 0.02391 0.01523 0.0274 1.0000 0.7993
-3.750 -0.4966 0.02422 0.01514 0.0271 1.0000 0.8189
-3.500 -0.4698 0.02434 0.01496 0.0276 1.0000 0.8391
-3.250 -0.4374 0.02451 0.01482 0.0269 1.0000 0.8561
-3.000 -0.4027 0.02465 0.01464 0.0256 1.0000 0.8715
-2.750 -0.3678 0.02474 0.01447 0.0241 1.0000 0.8862
-2.500 -0.3312 0.02478 0.01427 0.0220 1.0000 0.9000
-2.250 -0.2946 0.02478 0.01403 0.0197 1.0000 0.9134
-2.000 -0.2583 0.02475 0.01382 0.0173 1.0000 0.9263
-1.750 -0.2221 0.02471 0.01362 0.0148 1.0000 0.9390
-1.500 -0.1859 0.02466 0.01342 0.0122 1.0000 0.9516
-1.250 -0.1453 0.02459 0.01323 0.0086 1.0000 0.9623
-1.000 -0.1063 0.02450 0.01304 0.0052 1.0000 0.9733
-0.750 -0.0670 0.02441 0.01289 0.0016 1.0000 0.9840
-0.500 -0.0267 0.02432 0.01275 -0.0023 1.0000 0.9942
-0.250 -0.0012 0.02424 0.01266 -0.0034 1.0000 1.0000
0.000 0.0000 0.02422 0.01265 0.0000 1.0000 1.0000
0.250 0.0012 0.02424 0.01266 0.0034 1.0000 1.0000
0.500 0.0267 0.02431 0.01275 0.0023 0.9942 1.0000
0.750 0.0669 0.02441 0.01289 -0.0016 0.9840 1.0000
1.000 0.1063 0.02450 0.01304 -0.0052 0.9733 1.0000
1.250 0.1452 0.02458 0.01322 -0.0086 0.9623 1.0000
1.500 0.1858 0.02466 0.01341 -0.0122 0.9516 1.0000
1.750 0.2220 0.02471 0.01362 -0.0148 0.9390 1.0000
2.000 0.2582 0.02475 0.01381 -0.0173 0.9264 1.0000
2.250 0.2945 0.02477 0.01402 -0.0196 0.9134 1.0000
2.500 0.3312 0.02477 0.01426 -0.0219 0.9001 1.0000
2.750 0.3678 0.02473 0.01446 -0.0241 0.8863 1.0000
3.000 0.4026 0.02465 0.01464 -0.0256 0.8715 1.0000
3.250 0.4373 0.02451 0.01482 -0.0269 0.8561 1.0000
3.500 0.4698 0.02434 0.01495 -0.0276 0.8391 1.0000
3.750 0.4965 0.02421 0.01513 -0.0271 0.8189 1.0000
4.000 0.5298 0.02390 0.01522 -0.0274 0.7993 1.0000
4.250 0.5547 0.02369 0.01537 -0.0261 0.7746 1.0000
4.500 0.5831 0.02195 0.01366 -0.0214 0.6804 1.0000
4.750 0.5978 0.02173 0.01255 -0.0155 0.4874 1.0000
5.000 0.5951 0.02359 0.01297 -0.0098 0.2474 1.0000
5.250 0.5945 0.02629 0.01440 -0.0060 0.1031 1.0000
5.500 0.6040 0.02786 0.01585 -0.0030 0.0802 1.0000
5.750 0.6150 0.02916 0.01725 -0.0003 0.0664 1.0000
6.000 0.6266 0.03053 0.01868 0.0024 0.0589 1.0000
6.250 0.6431 0.03194 0.02028 0.0047 0.0540 1.0000
6.500 0.6616 0.03334 0.02181 0.0064 0.0479 1.0000
6.750 0.6864 0.03544 0.02394 0.0071 0.0441 1.0000
7.000 0.7137 0.03755 0.02639 0.0079 0.0420 1.0000
7.250 0.7351 0.03970 0.02887 0.0093 0.0394 1.0000
7.500 0.7516 0.04179 0.03117 0.0110 0.0368 1.0000
7.750 0.7658 0.04438 0.03392 0.0127 0.0350 1.0000
8.000 0.7777 0.04748 0.03739 0.0149 0.0344 1.0000
8.250 0.7850 0.05025 0.04059 0.0179 0.0341 1.0000
8.500 0.7887 0.05314 0.04387 0.0212 0.0340 1.0000
8.750 0.7892 0.05612 0.04720 0.0245 0.0339 1.0000
9.000 0.7864 0.05912 0.05054 0.0279 0.0338 1.0000
9.250 0.7804 0.06215 0.05387 0.0314 0.0337 1.0000
9.500 0.7713 0.06519 0.05718 0.0347 0.0336 1.0000
9.750 0.7593 0.06826 0.06048 0.0378 0.0336 1.0000
10.000 0.7437 0.07121 0.06359 0.0410 0.0336 1.0000
10.250 0.7267 0.07439 0.06692 0.0434 0.0337 1.0000
10.500 0.7099 0.07802 0.07066 0.0445 0.0338 1.0000
10.750 0.6937 0.08210 0.07484 0.0445 0.0340 1.0000
11.000 0.6784 0.08668 0.07950 0.0434 0.0341 1.0000
11.250 0.6649 0.09169 0.08455 0.0415 0.0343 1.0000
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Polar data table (+)
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