NACA 23012 12% (naca23012-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 23012 12% (naca23012-il) Reynolds number: 200,000 Max Cl/Cd: 50.98 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca23012-il-200000.txt Download as CSV file: xf-naca23012-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4467 0.08553 0.08207 -0.0213 1.0000 0.0708
-9.750 -0.4662 0.07820 0.07477 -0.0259 1.0000 0.0728
-9.500 -0.6405 0.07260 0.06884 -0.0321 1.0000 0.0661
-9.250 -0.6385 0.06965 0.06588 -0.0315 1.0000 0.0670
-9.000 -0.6405 0.06639 0.06257 -0.0311 1.0000 0.0682
-8.750 -0.6444 0.06295 0.05902 -0.0305 1.0000 0.0697
-8.500 -0.6509 0.05950 0.05536 -0.0294 1.0000 0.0724
-8.250 -0.6805 0.05710 0.05215 -0.0251 1.0000 0.0759
-8.000 -0.6624 0.05203 0.04733 -0.0254 1.0000 0.0775
-7.750 -0.6480 0.04964 0.04502 -0.0243 1.0000 0.0795
-7.500 -0.6392 0.04753 0.04280 -0.0223 1.0000 0.0827
-7.250 -0.6455 0.04565 0.04030 -0.0180 1.0000 0.0895
-7.000 -0.6311 0.04231 0.03707 -0.0169 1.0000 0.0913
-6.750 -0.6296 0.03261 0.02581 -0.0098 1.0000 0.0541
-6.500 -0.6152 0.03053 0.02346 -0.0075 1.0000 0.0543
-6.250 -0.5992 0.02848 0.02116 -0.0053 1.0000 0.0543
-6.000 -0.5816 0.02651 0.01896 -0.0034 1.0000 0.0542
-5.750 -0.5630 0.02498 0.01720 -0.0016 1.0000 0.0545
-5.500 -0.5437 0.02331 0.01535 0.0000 1.0000 0.0553
-5.250 -0.5237 0.02192 0.01398 0.0011 1.0000 0.0570
-5.000 -0.5034 0.02110 0.01314 0.0024 1.0000 0.0587
-4.750 -0.4825 0.02021 0.01219 0.0037 1.0000 0.0602
-4.500 -0.4615 0.01943 0.01133 0.0050 1.0000 0.0618
-4.250 -0.4408 0.01895 0.01073 0.0063 1.0000 0.0639
-4.000 -0.4001 0.01768 0.00957 0.0034 0.9958 0.0681
-3.750 -0.3570 0.01694 0.00885 0.0004 0.9903 0.0727
-3.500 -0.3142 0.01600 0.00797 -0.0028 0.9846 0.0790
-3.250 -0.2723 0.01542 0.00742 -0.0056 0.9769 0.0871
-3.000 -0.2276 0.01455 0.00665 -0.0092 0.9711 0.0993
-2.750 -0.1878 0.01381 0.00598 -0.0116 0.9611 0.1171
-2.500 -0.1542 0.01155 0.00514 -0.0138 0.9520 0.4045
-2.250 -0.1250 0.01023 0.00504 -0.0132 0.9415 0.6812
-2.000 -0.0956 0.00990 0.00500 -0.0123 0.9272 0.7632
-1.750 -0.0664 0.00976 0.00498 -0.0112 0.9124 0.8139
-1.500 -0.0379 0.00972 0.00497 -0.0100 0.8965 0.8530
-1.250 -0.0085 0.00975 0.00499 -0.0089 0.8791 0.8822
-1.000 0.0202 0.00983 0.00500 -0.0077 0.8600 0.9082
-0.750 0.0552 0.01001 0.00508 -0.0078 0.8391 0.9277
-0.500 0.0975 0.01028 0.00523 -0.0093 0.8143 0.9455
-0.250 0.1392 0.01042 0.00521 -0.0113 0.7878 0.9575
0.000 0.1833 0.01049 0.00510 -0.0142 0.7569 0.9642
0.250 0.2228 0.01058 0.00500 -0.0163 0.7238 0.9731
0.500 0.2638 0.01069 0.00490 -0.0188 0.6892 0.9816
0.750 0.3067 0.01078 0.00477 -0.0219 0.6519 0.9885
1.000 0.3491 0.01088 0.00466 -0.0249 0.6117 0.9956
1.250 0.3865 0.01098 0.00454 -0.0271 0.5727 1.0000
1.500 0.4092 0.01109 0.00445 -0.0264 0.5381 1.0000
1.750 0.4319 0.01123 0.00440 -0.0256 0.5036 1.0000
2.000 0.4546 0.01141 0.00438 -0.0249 0.4702 1.0000
2.250 0.4773 0.01161 0.00440 -0.0241 0.4395 1.0000
2.500 0.4997 0.01186 0.00446 -0.0233 0.4123 1.0000
2.750 0.5220 0.01210 0.00456 -0.0225 0.3880 1.0000
3.000 0.5441 0.01237 0.00469 -0.0215 0.3680 1.0000
3.250 0.5664 0.01264 0.00485 -0.0206 0.3513 1.0000
3.500 0.5886 0.01291 0.00503 -0.0197 0.3368 1.0000
3.750 0.6108 0.01320 0.00524 -0.0187 0.3242 1.0000
4.000 0.6329 0.01355 0.00546 -0.0177 0.3136 1.0000
4.250 0.6555 0.01379 0.00571 -0.0168 0.3032 1.0000
4.500 0.6778 0.01415 0.00598 -0.0158 0.2942 1.0000
4.750 0.7003 0.01443 0.00626 -0.0149 0.2855 1.0000
5.000 0.7228 0.01482 0.00659 -0.0139 0.2780 1.0000
5.250 0.7455 0.01512 0.00689 -0.0130 0.2701 1.0000
5.500 0.7681 0.01556 0.00726 -0.0121 0.2633 1.0000
5.750 0.7910 0.01586 0.00762 -0.0112 0.2561 1.0000
6.000 0.8138 0.01632 0.00798 -0.0104 0.2497 1.0000
6.250 0.8365 0.01666 0.00841 -0.0094 0.2430 1.0000
6.500 0.8592 0.01702 0.00877 -0.0086 0.2366 1.0000
6.750 0.8822 0.01754 0.00927 -0.0078 0.2307 1.0000
7.000 0.9048 0.01787 0.00968 -0.0069 0.2242 1.0000
7.250 0.9279 0.01834 0.01010 -0.0061 0.2183 1.0000
7.500 0.9504 0.01878 0.01065 -0.0053 0.2122 1.0000
7.750 0.9732 0.01914 0.01105 -0.0045 0.2059 1.0000
8.000 0.9962 0.01974 0.01160 -0.0038 0.2000 1.0000
8.250 1.0181 0.02004 0.01206 -0.0029 0.1935 1.0000
8.500 1.0408 0.02046 0.01244 -0.0022 0.1876 1.0000
8.750 1.0625 0.02094 0.01306 -0.0013 0.1813 1.0000
9.000 1.0843 0.02127 0.01343 -0.0004 0.1749 1.0000
9.250 1.1057 0.02180 0.01399 0.0004 0.1688 1.0000
9.500 1.1264 0.02211 0.01442 0.0014 0.1619 1.0000
9.750 1.1471 0.02264 0.01492 0.0022 0.1557 1.0000
10.000 1.1667 0.02298 0.01543 0.0034 0.1486 1.0000
10.250 1.1861 0.02355 0.01594 0.0043 0.1424 1.0000
10.500 1.2044 0.02395 0.01654 0.0056 0.1352 1.0000
10.750 1.2219 0.02458 0.01714 0.0068 0.1287 1.0000
11.000 1.2385 0.02505 0.01777 0.0081 0.1214 1.0000
11.250 1.2535 0.02579 0.01855 0.0096 0.1147 1.0000
11.500 1.2674 0.02642 0.01925 0.0112 0.1077 1.0000
11.750 1.2792 0.02731 0.02023 0.0130 0.1010 1.0000
12.000 1.2870 0.02818 0.02110 0.0152 0.0951 1.0000
12.250 1.2944 0.02927 0.02232 0.0174 0.0891 1.0000
12.500 1.2993 0.03051 0.02356 0.0194 0.0841 1.0000
12.750 1.3044 0.03194 0.02514 0.0211 0.0789 1.0000
13.000 1.3071 0.03356 0.02678 0.0226 0.0746 1.0000
13.250 1.3087 0.03552 0.02885 0.0239 0.0705 1.0000
13.500 1.3101 0.03756 0.03099 0.0247 0.0668 1.0000
13.750 1.3079 0.04010 0.03349 0.0254 0.0638 1.0000
14.000 1.3070 0.04276 0.03638 0.0255 0.0609 1.0000
14.250 1.3050 0.04564 0.03936 0.0252 0.0583 1.0000
14.500 1.3016 0.04872 0.04241 0.0249 0.0561 1.0000
14.750 1.2962 0.05235 0.04624 0.0240 0.0541 1.0000
15.000 1.2903 0.05618 0.05023 0.0228 0.0522 1.0000
15.250 1.2849 0.05999 0.05413 0.0214 0.0505 1.0000
15.500 1.2806 0.06357 0.05771 0.0204 0.0489 1.0000
15.750 1.2737 0.06760 0.06183 0.0193 0.0476 1.0000
16.000 1.2623 0.07267 0.06710 0.0171 0.0465 1.0000
16.250 1.2516 0.07771 0.07231 0.0148 0.0455 1.0000
16.500 1.2420 0.08265 0.07737 0.0126 0.0445 1.0000
16.750 1.2354 0.08713 0.08193 0.0106 0.0434 1.0000
17.000 1.2351 0.09038 0.08516 0.0097 0.0423 1.0000
17.250 1.2283 0.09477 0.08961 0.0083 0.0413 1.0000
17.500 1.2101 0.10178 0.09685 0.0044 0.0409 1.0000
17.750 1.1904 0.10928 0.10455 0.0001 0.0406 1.0000
18.000 1.1680 0.11750 0.11297 -0.0047 0.0403 1.0000
18.250 1.1410 0.12703 0.12271 -0.0104 0.0402 1.0000
18.500 1.1019 0.13967 0.13558 -0.0181 0.0404 1.0000
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