NACA 0012 AIRFOILS (n0012-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0012 AIRFOILS (n0012-il) Reynolds number: 100,000 Max Cl/Cd: 36.1 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n0012-il-100000-n5.txt Download as CSV file: xf-n0012-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0012 AIRFOILS
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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.8751 0.09584 0.09008 -0.0133 1.0000 0.0392
-13.750 -0.9212 0.08276 0.07678 -0.0224 1.0000 0.0386
-13.500 -0.9550 0.07345 0.06721 -0.0287 1.0000 0.0383
-13.250 -0.9811 0.06643 0.05992 -0.0328 1.0000 0.0384
-13.000 -1.0020 0.06089 0.05410 -0.0352 1.0000 0.0386
-12.750 -1.0192 0.05635 0.04927 -0.0361 1.0000 0.0389
-12.500 -1.0332 0.05253 0.04514 -0.0358 1.0000 0.0394
-12.250 -1.0442 0.04926 0.04152 -0.0345 1.0000 0.0399
-12.000 -1.0447 0.04681 0.03892 -0.0330 1.0000 0.0405
-11.750 -1.0402 0.04492 0.03695 -0.0314 1.0000 0.0413
-11.500 -1.0359 0.04320 0.03513 -0.0296 1.0000 0.0422
-11.250 -1.0301 0.04152 0.03330 -0.0277 1.0000 0.0434
-11.000 -1.0224 0.03971 0.03125 -0.0260 1.0000 0.0450
-10.750 -1.0131 0.03782 0.02903 -0.0243 1.0000 0.0467
-10.500 -0.9997 0.03620 0.02733 -0.0230 1.0000 0.0481
-10.250 -0.9851 0.03484 0.02594 -0.0217 1.0000 0.0497
-10.000 -0.9701 0.03353 0.02451 -0.0204 1.0000 0.0518
-9.750 -0.9540 0.03219 0.02292 -0.0190 1.0000 0.0544
-9.500 -0.9377 0.03089 0.02157 -0.0178 1.0000 0.0567
-9.250 -0.9208 0.02978 0.02043 -0.0165 1.0000 0.0592
-9.000 -0.9030 0.02869 0.01922 -0.0152 1.0000 0.0626
-8.750 -0.8854 0.02758 0.01803 -0.0139 1.0000 0.0660
-8.500 -0.8678 0.02663 0.01706 -0.0126 1.0000 0.0697
-8.250 -0.8488 0.02572 0.01601 -0.0114 1.0000 0.0744
-8.000 -0.8315 0.02476 0.01510 -0.0100 1.0000 0.0790
-7.750 -0.8125 0.02394 0.01420 -0.0086 1.0000 0.0850
-7.500 -0.7946 0.02308 0.01337 -0.0072 1.0000 0.0913
-7.250 -0.7753 0.02235 0.01257 -0.0059 1.0000 0.0993
-7.000 -0.7571 0.02157 0.01185 -0.0045 1.0000 0.1083
-6.750 -0.7385 0.02085 0.01115 -0.0030 1.0000 0.1189
-6.500 -0.7196 0.02017 0.01051 -0.0016 1.0000 0.1316
-6.250 -0.7005 0.01953 0.00992 -0.0002 1.0000 0.1470
-6.000 -0.6813 0.01892 0.00936 0.0012 1.0000 0.1653
-5.750 -0.6617 0.01835 0.00887 0.0025 1.0000 0.1867
-5.500 -0.6423 0.01779 0.00842 0.0038 1.0000 0.2113
-5.250 -0.6226 0.01728 0.00803 0.0051 1.0000 0.2383
-5.000 -0.6027 0.01681 0.00766 0.0064 1.0000 0.2677
-4.750 -0.5826 0.01637 0.00735 0.0077 1.0000 0.2988
-4.500 -0.5623 0.01598 0.00708 0.0090 1.0000 0.3309
-4.250 -0.5419 0.01562 0.00684 0.0103 1.0000 0.3635
-4.000 -0.5212 0.01530 0.00665 0.0115 1.0000 0.3966
-3.750 -0.5004 0.01501 0.00649 0.0127 1.0000 0.4296
-3.500 -0.4793 0.01476 0.00636 0.0139 1.0000 0.4626
-3.250 -0.4580 0.01454 0.00625 0.0151 1.0000 0.4955
-3.000 -0.4365 0.01435 0.00619 0.0162 1.0000 0.5284
-2.750 -0.4120 0.01419 0.00616 0.0168 0.9987 0.5620
-2.500 -0.3736 0.01405 0.00614 0.0146 0.9910 0.5999
-2.250 -0.3346 0.01394 0.00616 0.0124 0.9831 0.6367
-2.000 -0.2976 0.01384 0.00616 0.0107 0.9737 0.6713
-1.750 -0.2601 0.01376 0.00618 0.0091 0.9644 0.7043
-1.500 -0.2196 0.01370 0.00622 0.0069 0.9562 0.7357
-1.250 -0.1837 0.01365 0.00624 0.0057 0.9448 0.7644
-1.000 -0.1475 0.01362 0.00626 0.0046 0.9332 0.7918
-0.750 -0.1093 0.01360 0.00630 0.0031 0.9219 0.8157
-0.500 -0.0724 0.01359 0.00631 0.0020 0.9087 0.8382
-0.250 -0.0370 0.01358 0.00632 0.0011 0.8932 0.8589
0.000 0.0000 0.01358 0.00633 0.0000 0.8767 0.8767
0.250 0.0370 0.01358 0.00632 -0.0011 0.8589 0.8932
0.500 0.0724 0.01359 0.00631 -0.0020 0.8382 0.9087
0.750 0.1093 0.01360 0.00630 -0.0031 0.8157 0.9219
1.000 0.1475 0.01362 0.00626 -0.0046 0.7918 0.9332
1.250 0.1837 0.01365 0.00624 -0.0057 0.7644 0.9448
1.500 0.2196 0.01370 0.00622 -0.0069 0.7358 0.9562
1.750 0.2601 0.01376 0.00618 -0.0091 0.7043 0.9644
2.000 0.2976 0.01383 0.00615 -0.0107 0.6713 0.9737
2.250 0.3346 0.01394 0.00616 -0.0124 0.6367 0.9832
2.500 0.3736 0.01405 0.00614 -0.0146 0.5999 0.9910
2.750 0.4120 0.01419 0.00616 -0.0168 0.5620 0.9987
3.000 0.4365 0.01435 0.00619 -0.0162 0.5284 1.0000
3.250 0.4579 0.01454 0.00625 -0.0151 0.4956 1.0000
3.500 0.4792 0.01476 0.00636 -0.0139 0.4627 1.0000
3.750 0.5003 0.01501 0.00648 -0.0127 0.4297 1.0000
4.000 0.5212 0.01530 0.00664 -0.0115 0.3967 1.0000
4.250 0.5418 0.01562 0.00684 -0.0103 0.3636 1.0000
4.500 0.5623 0.01598 0.00708 -0.0090 0.3309 1.0000
4.750 0.5825 0.01637 0.00735 -0.0077 0.2989 1.0000
5.000 0.6026 0.01680 0.00766 -0.0064 0.2678 1.0000
5.250 0.6225 0.01727 0.00802 -0.0051 0.2383 1.0000
5.500 0.6422 0.01779 0.00842 -0.0038 0.2113 1.0000
5.750 0.6617 0.01835 0.00886 -0.0025 0.1868 1.0000
6.000 0.6812 0.01892 0.00936 -0.0012 0.1653 1.0000
6.250 0.7005 0.01953 0.00991 0.0002 0.1470 1.0000
6.500 0.7195 0.02017 0.01051 0.0016 0.1316 1.0000
6.750 0.7385 0.02085 0.01115 0.0030 0.1189 1.0000
7.000 0.7571 0.02157 0.01184 0.0045 0.1083 1.0000
7.250 0.7753 0.02235 0.01257 0.0059 0.0993 1.0000
7.500 0.7946 0.02308 0.01337 0.0072 0.0913 1.0000
7.750 0.8125 0.02394 0.01419 0.0086 0.0850 1.0000
8.000 0.8315 0.02476 0.01510 0.0100 0.0790 1.0000
8.250 0.8489 0.02571 0.01601 0.0113 0.0744 1.0000
8.500 0.8678 0.02662 0.01706 0.0126 0.0697 1.0000
8.750 0.8855 0.02758 0.01803 0.0139 0.0660 1.0000
9.000 0.9031 0.02869 0.01922 0.0152 0.0626 1.0000
9.250 0.9210 0.02978 0.02043 0.0165 0.0592 1.0000
9.500 0.9379 0.03089 0.02157 0.0177 0.0567 1.0000
9.750 0.9542 0.03220 0.02292 0.0190 0.0544 1.0000
10.000 0.9703 0.03354 0.02451 0.0203 0.0518 1.0000
10.250 0.9853 0.03484 0.02594 0.0216 0.0497 1.0000
10.500 0.9999 0.03620 0.02733 0.0229 0.0481 1.0000
10.750 1.0133 0.03783 0.02903 0.0242 0.0467 1.0000
11.000 1.0227 0.03972 0.03125 0.0259 0.0450 1.0000
11.250 1.0305 0.04152 0.03330 0.0276 0.0434 1.0000
11.500 1.0363 0.04320 0.03513 0.0295 0.0422 1.0000
11.750 1.0408 0.04492 0.03696 0.0313 0.0412 1.0000
12.000 1.0454 0.04682 0.03893 0.0329 0.0405 1.0000
12.250 1.0447 0.04928 0.04154 0.0344 0.0399 1.0000
12.500 1.0338 0.05256 0.04517 0.0357 0.0394 1.0000
12.750 1.0198 0.05638 0.04931 0.0359 0.0389 1.0000
13.000 1.0026 0.06093 0.05415 0.0350 0.0385 1.0000
13.250 0.9817 0.06649 0.05999 0.0326 0.0383 1.0000
13.500 0.9556 0.07354 0.06731 0.0285 0.0383 1.0000
13.750 0.9215 0.08293 0.07695 0.0221 0.0386 1.0000
14.000 0.8751 0.09617 0.09041 0.0128 0.0392 1.0000
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