NACA 0012 AIRFOILS (n0012-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0012 AIRFOILS (n0012-il) Reynolds number: 500,000 Max Cl/Cd: 61.71 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n0012-il-500000-n5.txt Download as CSV file: xf-n0012-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.1683 0.10069 0.09689 -0.0021 1.0000 0.0140
-17.500 -1.1891 0.09312 0.08920 -0.0060 1.0000 0.0141
-17.250 -1.2099 0.08573 0.08168 -0.0098 1.0000 0.0141
-17.000 -1.2297 0.07862 0.07444 -0.0135 1.0000 0.0142
-16.750 -1.2482 0.07193 0.06762 -0.0169 1.0000 0.0142
-16.500 -1.2642 0.06573 0.06129 -0.0201 1.0000 0.0143
-16.250 -1.2774 0.06009 0.05551 -0.0230 1.0000 0.0144
-16.000 -1.2876 0.05502 0.05031 -0.0256 1.0000 0.0145
-15.750 -1.2949 0.05052 0.04568 -0.0277 1.0000 0.0146
-15.500 -1.2995 0.04660 0.04164 -0.0294 1.0000 0.0148
-15.250 -1.3018 0.04316 0.03807 -0.0306 1.0000 0.0150
-15.000 -1.3021 0.04016 0.03496 -0.0314 1.0000 0.0152
-14.750 -1.3008 0.03755 0.03223 -0.0318 1.0000 0.0154
-14.500 -1.2982 0.03526 0.02983 -0.0317 1.0000 0.0156
-14.250 -1.2939 0.03328 0.02774 -0.0313 1.0000 0.0159
-14.000 -1.2885 0.03156 0.02589 -0.0305 1.0000 0.0162
-13.750 -1.2815 0.03007 0.02429 -0.0295 1.0000 0.0166
-13.500 -1.2731 0.02878 0.02288 -0.0282 1.0000 0.0169
-13.250 -1.2678 0.02736 0.02140 -0.0265 1.0000 0.0172
-13.000 -1.2593 0.02623 0.02021 -0.0247 1.0000 0.0176
-12.750 -1.2491 0.02528 0.01919 -0.0229 1.0000 0.0180
-12.500 -1.2378 0.02443 0.01826 -0.0209 1.0000 0.0185
-12.250 -1.2249 0.02365 0.01740 -0.0191 1.0000 0.0189
-12.000 -1.2093 0.02289 0.01656 -0.0176 1.0000 0.0195
-11.750 -1.1925 0.02217 0.01577 -0.0163 1.0000 0.0200
-11.500 -1.1753 0.02145 0.01497 -0.0150 1.0000 0.0205
-11.250 -1.1580 0.02071 0.01419 -0.0137 1.0000 0.0212
-11.000 -1.1389 0.02009 0.01353 -0.0126 1.0000 0.0220
-10.750 -1.1189 0.01952 0.01291 -0.0116 1.0000 0.0229
-10.500 -1.0984 0.01898 0.01231 -0.0106 1.0000 0.0238
-10.250 -1.0782 0.01842 0.01168 -0.0096 1.0000 0.0246
-10.000 -1.0580 0.01784 0.01108 -0.0085 1.0000 0.0256
-9.750 -1.0369 0.01734 0.01055 -0.0075 1.0000 0.0267
-9.500 -1.0154 0.01689 0.01006 -0.0066 1.0000 0.0280
-9.250 -0.9940 0.01644 0.00956 -0.0055 1.0000 0.0292
-9.000 -0.9731 0.01596 0.00908 -0.0045 1.0000 0.0308
-8.750 -0.9517 0.01556 0.00865 -0.0034 1.0000 0.0325
-8.500 -0.9302 0.01520 0.00824 -0.0023 1.0000 0.0340
-8.250 -0.9096 0.01477 0.00782 -0.0010 1.0000 0.0360
-8.000 -0.8883 0.01441 0.00745 0.0001 1.0000 0.0384
-7.750 -0.8670 0.01408 0.00709 0.0013 1.0000 0.0407
-7.500 -0.8461 0.01371 0.00674 0.0026 1.0000 0.0437
-7.250 -0.8248 0.01342 0.00643 0.0038 1.0000 0.0466
-7.000 -0.8039 0.01308 0.00611 0.0050 1.0000 0.0504
-6.750 -0.7799 0.01279 0.00582 0.0056 0.9995 0.0547
-6.500 -0.7471 0.01242 0.00548 0.0044 0.9969 0.0608
-6.250 -0.7137 0.01209 0.00517 0.0030 0.9945 0.0678
-6.000 -0.6812 0.01177 0.00488 0.0018 0.9914 0.0761
-5.750 -0.6486 0.01145 0.00460 0.0006 0.9878 0.0862
-5.500 -0.6149 0.01112 0.00433 -0.0008 0.9848 0.0986
-5.250 -0.5817 0.01079 0.00407 -0.0021 0.9814 0.1131
-5.000 -0.5512 0.01046 0.00382 -0.0028 0.9757 0.1296
-4.750 -0.5185 0.01014 0.00359 -0.0040 0.9711 0.1496
-4.500 -0.4888 0.00985 0.00338 -0.0044 0.9640 0.1702
-4.250 -0.4576 0.00953 0.00317 -0.0052 0.9573 0.1940
-4.000 -0.4287 0.00925 0.00298 -0.0055 0.9484 0.2186
-3.750 -0.3988 0.00897 0.00280 -0.0059 0.9395 0.2454
-3.500 -0.3711 0.00871 0.00264 -0.0058 0.9277 0.2713
-3.250 -0.3437 0.00847 0.00249 -0.0057 0.9150 0.2982
-3.000 -0.3166 0.00826 0.00234 -0.0054 0.9008 0.3257
-2.750 -0.2901 0.00806 0.00221 -0.0050 0.8850 0.3532
-2.500 -0.2637 0.00789 0.00210 -0.0045 0.8675 0.3801
-2.250 -0.2373 0.00774 0.00199 -0.0041 0.8486 0.4076
-2.000 -0.2111 0.00761 0.00189 -0.0036 0.8285 0.4342
-1.500 -0.1585 0.00741 0.00173 -0.0026 0.7855 0.4872
-1.250 -0.1321 0.00734 0.00167 -0.0022 0.7625 0.5131
-1.000 -0.1057 0.00729 0.00162 -0.0017 0.7391 0.5392
-0.750 -0.0793 0.00724 0.00158 -0.0013 0.7149 0.5648
-0.500 -0.0529 0.00722 0.00155 -0.0008 0.6905 0.5906
-0.250 -0.0265 0.00719 0.00154 -0.0004 0.6655 0.6157
0.000 0.0000 0.00720 0.00153 0.0000 0.6407 0.6407
0.250 0.0265 0.00719 0.00154 0.0004 0.6155 0.6656
0.500 0.0529 0.00722 0.00155 0.0008 0.5906 0.6906
0.750 0.0794 0.00724 0.00158 0.0013 0.5650 0.7147
1.000 0.1058 0.00729 0.00162 0.0017 0.5393 0.7390
1.250 0.1321 0.00734 0.00167 0.0022 0.5130 0.7625
1.500 0.1585 0.00741 0.00173 0.0026 0.4874 0.7855
1.750 0.1848 0.00751 0.00180 0.0031 0.4607 0.8076
2.000 0.2111 0.00761 0.00189 0.0036 0.4341 0.8285
2.250 0.2373 0.00774 0.00199 0.0041 0.4075 0.8487
2.500 0.2637 0.00789 0.00210 0.0045 0.3803 0.8676
2.750 0.2901 0.00806 0.00221 0.0050 0.3534 0.8850
3.000 0.3167 0.00826 0.00234 0.0054 0.3260 0.9008
3.250 0.3437 0.00848 0.00249 0.0057 0.2980 0.9150
3.500 0.3711 0.00871 0.00264 0.0058 0.2713 0.9277
3.750 0.3988 0.00897 0.00280 0.0059 0.2452 0.9395
4.000 0.4287 0.00925 0.00298 0.0055 0.2186 0.9484
4.250 0.4576 0.00953 0.00317 0.0052 0.1941 0.9573
4.500 0.4889 0.00985 0.00338 0.0044 0.1701 0.9640
4.750 0.5185 0.01014 0.00359 0.0040 0.1497 0.9711
5.000 0.5512 0.01046 0.00382 0.0028 0.1297 0.9757
5.250 0.5818 0.01079 0.00406 0.0021 0.1131 0.9814
5.500 0.6150 0.01112 0.00433 0.0008 0.0986 0.9848
5.750 0.6487 0.01145 0.00460 -0.0007 0.0862 0.9878
6.000 0.6813 0.01177 0.00488 -0.0018 0.0761 0.9914
6.250 0.7138 0.01209 0.00517 -0.0030 0.0678 0.9945
6.500 0.7472 0.01242 0.00548 -0.0044 0.0608 0.9969
6.750 0.7799 0.01279 0.00582 -0.0057 0.0547 0.9995
7.000 0.8038 0.01308 0.00611 -0.0050 0.0504 1.0000
7.250 0.8247 0.01342 0.00642 -0.0037 0.0467 1.0000
7.500 0.8461 0.01371 0.00674 -0.0025 0.0437 1.0000
7.750 0.8670 0.01408 0.00709 -0.0013 0.0407 1.0000
8.000 0.8883 0.01441 0.00745 -0.0001 0.0384 1.0000
8.250 0.9096 0.01477 0.00781 0.0010 0.0360 1.0000
8.500 0.9302 0.01520 0.00824 0.0023 0.0340 1.0000
8.750 0.9517 0.01556 0.00865 0.0034 0.0325 1.0000
9.000 0.9731 0.01596 0.00908 0.0045 0.0308 1.0000
9.250 0.9941 0.01644 0.00956 0.0055 0.0292 1.0000
9.500 1.0154 0.01689 0.01005 0.0066 0.0280 1.0000
9.750 1.0370 0.01734 0.01055 0.0075 0.0267 1.0000
10.000 1.0581 0.01783 0.01108 0.0085 0.0256 1.0000
10.250 1.0783 0.01842 0.01168 0.0095 0.0246 1.0000
10.500 1.0986 0.01898 0.01230 0.0106 0.0238 1.0000
10.750 1.1190 0.01952 0.01291 0.0116 0.0229 1.0000
11.000 1.1390 0.02009 0.01353 0.0126 0.0220 1.0000
11.250 1.1582 0.02071 0.01418 0.0137 0.0212 1.0000
11.500 1.1756 0.02145 0.01497 0.0150 0.0205 1.0000
11.750 1.1928 0.02217 0.01577 0.0163 0.0200 1.0000
12.000 1.2097 0.02289 0.01656 0.0176 0.0195 1.0000
12.250 1.2253 0.02365 0.01740 0.0190 0.0189 1.0000
12.500 1.2383 0.02443 0.01826 0.0208 0.0185 1.0000
12.750 1.2496 0.02528 0.01919 0.0228 0.0180 1.0000
13.000 1.2599 0.02623 0.02021 0.0246 0.0176 1.0000
13.250 1.2685 0.02736 0.02140 0.0264 0.0172 1.0000
13.500 1.2740 0.02877 0.02287 0.0281 0.0168 1.0000
13.750 1.2822 0.03007 0.02429 0.0293 0.0166 1.0000
14.000 1.2893 0.03156 0.02589 0.0304 0.0162 1.0000
14.250 1.2950 0.03327 0.02772 0.0311 0.0159 1.0000
14.500 1.2994 0.03524 0.02981 0.0316 0.0156 1.0000
14.750 1.3021 0.03752 0.03220 0.0316 0.0154 1.0000
15.000 1.3035 0.04013 0.03493 0.0312 0.0152 1.0000
15.250 1.3033 0.04311 0.03803 0.0304 0.0149 1.0000
15.500 1.3012 0.04654 0.04158 0.0292 0.0148 1.0000
15.750 1.2967 0.05047 0.04563 0.0275 0.0146 1.0000
16.000 1.2895 0.05495 0.05023 0.0253 0.0145 1.0000
16.250 1.2794 0.06003 0.05545 0.0228 0.0144 1.0000
16.500 1.2662 0.06567 0.06122 0.0199 0.0143 1.0000
16.750 1.2503 0.07187 0.06756 0.0166 0.0142 1.0000
17.000 1.2320 0.07855 0.07437 0.0132 0.0142 1.0000
17.250 1.2122 0.08566 0.08161 0.0095 0.0141 1.0000
17.500 1.1914 0.09306 0.08914 0.0057 0.0141 1.0000
17.750 1.1705 0.10066 0.09686 0.0018 0.0140 1.0000
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