NACA 23012 12% (naca23012-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 23012 12% (naca23012-il) Reynolds number: 50,000 Max Cl/Cd: 28.32 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca23012-il-50000-n5.txt Download as CSV file: xf-naca23012-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 23012 12%
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5870 0.09595 0.08841 -0.0226 1.0000 0.0639
-10.250 -0.5904 0.09081 0.08329 -0.0252 1.0000 0.0633
-10.000 -0.5998 0.08537 0.07785 -0.0283 1.0000 0.0627
-9.750 -0.6142 0.08027 0.07271 -0.0306 1.0000 0.0622
-9.500 -0.6311 0.07586 0.06824 -0.0312 1.0000 0.0618
-9.250 -0.6452 0.07164 0.06390 -0.0311 1.0000 0.0616
-9.000 -0.6557 0.06757 0.05964 -0.0305 1.0000 0.0616
-8.750 -0.6626 0.06371 0.05553 -0.0294 1.0000 0.0619
-8.500 -0.6662 0.06003 0.05154 -0.0280 1.0000 0.0624
-8.250 -0.6664 0.05654 0.04768 -0.0263 1.0000 0.0629
-8.000 -0.6630 0.05325 0.04399 -0.0245 1.0000 0.0634
-7.750 -0.6562 0.05017 0.04051 -0.0225 1.0000 0.0637
-7.500 -0.6463 0.04733 0.03725 -0.0206 1.0000 0.0640
-7.250 -0.6330 0.04470 0.03440 -0.0190 1.0000 0.0649
-7.000 -0.6164 0.04264 0.03231 -0.0178 1.0000 0.0667
-6.750 -0.6003 0.04070 0.03018 -0.0163 1.0000 0.0687
-6.500 -0.5835 0.03871 0.02791 -0.0146 1.0000 0.0706
-6.250 -0.5650 0.03675 0.02562 -0.0130 1.0000 0.0720
-6.000 -0.5453 0.03498 0.02351 -0.0115 1.0000 0.0738
-5.750 -0.5248 0.03335 0.02168 -0.0101 1.0000 0.0765
-5.500 -0.5035 0.03191 0.02025 -0.0091 1.0000 0.0796
-5.250 -0.4810 0.03058 0.01882 -0.0079 1.0000 0.0825
-5.000 -0.4582 0.02944 0.01752 -0.0067 1.0000 0.0863
-4.750 -0.4356 0.02826 0.01635 -0.0056 1.0000 0.0907
-4.500 -0.4139 0.02725 0.01537 -0.0043 1.0000 0.0954
-4.250 -0.3926 0.02646 0.01445 -0.0029 1.0000 0.1014
-4.000 -0.3732 0.02551 0.01359 -0.0015 1.0000 0.1077
-3.750 -0.3539 0.02478 0.01279 0.0000 1.0000 0.1158
-3.500 -0.3356 0.02396 0.01201 0.0014 1.0000 0.1255
-3.250 -0.3170 0.02319 0.01128 0.0027 1.0000 0.1388
-3.000 -0.2989 0.02234 0.01059 0.0039 1.0000 0.1613
-2.750 -0.2866 0.02033 0.01003 0.0054 1.0000 0.3534
-2.500 -0.2775 0.01928 0.01036 0.0100 1.0000 0.6318
-2.250 -0.2596 0.01930 0.01081 0.0137 1.0000 0.7606
-2.000 -0.2149 0.01980 0.01138 0.0128 0.9945 0.8630
-1.750 -0.1272 0.02074 0.01208 0.0042 0.9937 0.9503
-1.500 -0.0429 0.02089 0.01194 -0.0067 0.9859 0.9764
-1.250 0.0275 0.02075 0.01158 -0.0156 0.9711 0.9878
-1.000 0.0968 0.02047 0.01113 -0.0242 0.9525 0.9977
-0.750 0.1492 0.02014 0.01067 -0.0294 0.9271 1.0000
-0.500 0.1895 0.01983 0.01026 -0.0320 0.8966 1.0000
-0.250 0.2244 0.01955 0.00987 -0.0332 0.8644 1.0000
0.000 0.2544 0.01932 0.00952 -0.0334 0.8313 1.0000
0.250 0.2807 0.01915 0.00922 -0.0327 0.7981 1.0000
0.500 0.3044 0.01905 0.00897 -0.0315 0.7649 1.0000
0.750 0.3265 0.01902 0.00877 -0.0300 0.7319 1.0000
1.000 0.3479 0.01904 0.00862 -0.0283 0.6991 1.0000
1.250 0.3687 0.01912 0.00851 -0.0266 0.6666 1.0000
1.500 0.3893 0.01925 0.00845 -0.0249 0.6344 1.0000
1.750 0.4097 0.01944 0.00846 -0.0232 0.6027 1.0000
2.000 0.4300 0.01967 0.00852 -0.0216 0.5719 1.0000
2.250 0.4504 0.01994 0.00861 -0.0201 0.5426 1.0000
2.500 0.4709 0.02026 0.00873 -0.0186 0.5159 1.0000
2.750 0.4917 0.02061 0.00896 -0.0172 0.4898 1.0000
3.000 0.5132 0.02100 0.00917 -0.0160 0.4664 1.0000
3.250 0.5349 0.02141 0.00946 -0.0149 0.4450 1.0000
3.500 0.5568 0.02186 0.00981 -0.0138 0.4254 1.0000
3.750 0.5789 0.02232 0.01018 -0.0128 0.4076 1.0000
4.000 0.6012 0.02281 0.01059 -0.0119 0.3917 1.0000
4.250 0.6236 0.02332 0.01103 -0.0109 0.3777 1.0000
4.500 0.6461 0.02385 0.01150 -0.0100 0.3647 1.0000
4.750 0.6685 0.02442 0.01207 -0.0091 0.3519 1.0000
5.000 0.6912 0.02501 0.01267 -0.0083 0.3408 1.0000
5.250 0.7141 0.02561 0.01319 -0.0075 0.3310 1.0000
5.500 0.7363 0.02627 0.01394 -0.0066 0.3202 1.0000
5.750 0.7593 0.02693 0.01458 -0.0059 0.3116 1.0000
6.000 0.7814 0.02765 0.01540 -0.0051 0.3022 1.0000
6.250 0.8039 0.02839 0.01616 -0.0043 0.2940 1.0000
6.500 0.8258 0.02916 0.01703 -0.0035 0.2855 1.0000
6.750 0.8481 0.02998 0.01790 -0.0027 0.2780 1.0000
7.000 0.8692 0.03084 0.01889 -0.0019 0.2698 1.0000
7.250 0.8914 0.03168 0.01976 -0.0011 0.2629 1.0000
7.500 0.9110 0.03271 0.02102 -0.0002 0.2550 1.0000
7.750 0.9341 0.03348 0.02172 0.0005 0.2485 1.0000
8.000 0.9508 0.03475 0.02333 0.0016 0.2406 1.0000
8.250 0.9726 0.03559 0.02419 0.0024 0.2341 1.0000
8.500 0.9884 0.03695 0.02583 0.0035 0.2266 1.0000
8.750 1.0076 0.03798 0.02697 0.0045 0.2199 1.0000
9.000 1.0241 0.03926 0.02842 0.0056 0.2133 1.0000
9.250 1.0384 0.04063 0.03005 0.0069 0.2061 1.0000
9.500 1.0587 0.04153 0.03094 0.0077 0.2002 1.0000
9.750 1.0645 0.04354 0.03336 0.0095 0.1929 1.0000
10.000 1.0848 0.04428 0.03408 0.0104 0.1869 1.0000
10.250 1.0859 0.04662 0.03682 0.0123 0.1804 1.0000
10.500 1.0972 0.04792 0.03825 0.0137 0.1741 1.0000
10.750 1.1045 0.04960 0.04008 0.0152 0.1686 1.0000
11.000 1.0962 0.05242 0.04323 0.0174 0.1631 1.0000
11.250 1.1192 0.05250 0.04323 0.0183 0.1573 1.0000
11.500 1.0925 0.05658 0.04765 0.0209 0.1539 1.0000
11.750 1.0571 0.06197 0.05332 0.0220 0.1513 1.0000
12.000 0.9917 0.07273 0.06429 0.0180 0.1506 1.0000
12.250 0.8694 0.09881 0.09032 0.0020 0.1474 1.0000
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Polar data table (+)
Polar graphs
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