NACA 23012 12% (naca23012-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 23012 12% (naca23012-il) Reynolds number: 100,000 Max Cl/Cd: 36.38 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca23012-il-100000.txt Download as CSV file: xf-naca23012-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5351 0.10845 0.10329 -0.0041 1.0000 0.1255
-10.000 -0.5476 0.10393 0.09884 -0.0085 1.0000 0.1316
-9.750 -0.6133 0.09584 0.09083 -0.0235 1.0000 0.1336
-9.500 -0.5441 0.09556 0.09054 -0.0101 1.0000 0.1393
-9.250 -0.5469 0.09161 0.08662 -0.0122 1.0000 0.1456
-9.000 -0.6158 0.08385 0.07889 -0.0239 1.0000 0.1494
-8.750 -0.5617 0.08209 0.07723 -0.0172 1.0000 0.1565
-8.500 -0.5836 0.07723 0.07240 -0.0205 1.0000 0.1624
-8.250 -0.6066 0.07210 0.06723 -0.0224 1.0000 0.1695
-8.000 -0.6091 0.06945 0.06454 -0.0219 1.0000 0.1805
-7.750 -0.5924 0.06694 0.06212 -0.0196 1.0000 0.1923
-7.500 -0.5907 0.06417 0.05936 -0.0182 1.0000 0.2068
-7.250 -0.5874 0.06172 0.05693 -0.0165 1.0000 0.2234
-6.500 -0.6046 0.04013 0.03258 -0.0135 1.0000 0.1044
-6.250 -0.5866 0.03707 0.02933 -0.0117 1.0000 0.0973
-6.000 -0.5711 0.03447 0.02640 -0.0095 1.0000 0.0951
-5.750 -0.5542 0.03210 0.02362 -0.0073 1.0000 0.0928
-5.500 -0.5360 0.03014 0.02111 -0.0049 1.0000 0.0902
-5.250 -0.5157 0.02842 0.01915 -0.0032 1.0000 0.0902
-5.000 -0.4952 0.02687 0.01756 -0.0020 1.0000 0.0926
-4.750 -0.4742 0.02563 0.01622 -0.0006 1.0000 0.0953
-4.500 -0.4524 0.02442 0.01488 0.0007 1.0000 0.0972
-4.250 -0.4301 0.02338 0.01369 0.0020 1.0000 0.0997
-4.000 -0.4080 0.02237 0.01259 0.0032 1.0000 0.1037
-3.750 -0.3860 0.02120 0.01158 0.0041 1.0000 0.1090
-3.500 -0.3645 0.02046 0.01084 0.0053 1.0000 0.1147
-3.250 -0.3438 0.01956 0.01007 0.0064 1.0000 0.1223
-3.000 -0.3237 0.01895 0.00954 0.0075 1.0000 0.1318
-2.750 -0.3044 0.01825 0.00896 0.0086 1.0000 0.1454
-2.500 -0.2845 0.01761 0.00846 0.0095 1.0000 0.1680
-2.250 -0.2685 0.01498 0.00827 0.0110 1.0000 0.5923
-2.000 -0.2510 0.01491 0.00913 0.0160 0.9967 0.8299
-1.750 -0.1923 0.01576 0.00996 0.0130 0.9876 0.9265
-1.500 -0.0909 0.01666 0.01059 0.0010 0.9852 0.9694
-1.250 0.0421 0.01689 0.01058 -0.0177 0.9879 0.9991
-1.000 0.1135 0.01648 0.01005 -0.0269 0.9727 1.0000
-0.750 0.1774 0.01597 0.00946 -0.0344 0.9546 1.0000
-0.500 0.2269 0.01547 0.00889 -0.0388 0.9293 1.0000
-0.250 0.2638 0.01502 0.00837 -0.0404 0.8990 1.0000
0.000 0.2908 0.01466 0.00792 -0.0398 0.8661 1.0000
0.250 0.3125 0.01440 0.00754 -0.0381 0.8320 1.0000
0.500 0.3327 0.01421 0.00721 -0.0361 0.7970 1.0000
0.750 0.3528 0.01410 0.00694 -0.0341 0.7614 1.0000
1.000 0.3734 0.01407 0.00672 -0.0322 0.7250 1.0000
1.250 0.3943 0.01411 0.00654 -0.0305 0.6882 1.0000
1.500 0.4153 0.01423 0.00643 -0.0289 0.6506 1.0000
1.750 0.4363 0.01441 0.00640 -0.0274 0.6120 1.0000
2.000 0.4574 0.01465 0.00640 -0.0259 0.5746 1.0000
2.250 0.4786 0.01495 0.00646 -0.0245 0.5395 1.0000
2.500 0.4999 0.01530 0.00659 -0.0233 0.5076 1.0000
2.750 0.5215 0.01569 0.00674 -0.0220 0.4802 1.0000
3.000 0.5432 0.01608 0.00698 -0.0209 0.4547 1.0000
3.250 0.5653 0.01650 0.00724 -0.0198 0.4340 1.0000
3.500 0.5876 0.01695 0.00754 -0.0188 0.4159 1.0000
3.750 0.6100 0.01740 0.00789 -0.0178 0.3996 1.0000
4.000 0.6325 0.01787 0.00830 -0.0169 0.3850 1.0000
4.250 0.6552 0.01837 0.00875 -0.0160 0.3721 1.0000
4.500 0.6781 0.01890 0.00918 -0.0151 0.3607 1.0000
4.750 0.7010 0.01941 0.00964 -0.0142 0.3496 1.0000
5.000 0.7237 0.01998 0.01025 -0.0134 0.3393 1.0000
5.250 0.7476 0.02060 0.01071 -0.0127 0.3304 1.0000
5.500 0.7694 0.02115 0.01141 -0.0116 0.3205 1.0000
5.750 0.7931 0.02184 0.01201 -0.0109 0.3125 1.0000
6.000 0.8149 0.02244 0.01275 -0.0099 0.3035 1.0000
6.250 0.8386 0.02318 0.01341 -0.0093 0.2960 1.0000
6.500 0.8601 0.02385 0.01426 -0.0083 0.2874 1.0000
6.750 0.8843 0.02465 0.01495 -0.0077 0.2804 1.0000
7.000 0.9047 0.02538 0.01592 -0.0066 0.2720 1.0000
7.250 0.9296 0.02619 0.01660 -0.0062 0.2652 1.0000
7.500 0.9486 0.02704 0.01776 -0.0049 0.2570 1.0000
7.750 0.9727 0.02778 0.01841 -0.0044 0.2501 1.0000
8.000 0.9916 0.02883 0.01974 -0.0032 0.2423 1.0000
8.250 1.0146 0.02952 0.02042 -0.0025 0.2350 1.0000
8.500 1.0331 0.03068 0.02179 -0.0014 0.2276 1.0000
8.750 1.0549 0.03138 0.02253 -0.0006 0.2200 1.0000
9.000 1.0734 0.03256 0.02388 0.0005 0.2128 1.0000
9.250 1.0935 0.03329 0.02471 0.0015 0.2049 1.0000
9.500 1.1118 0.03443 0.02597 0.0026 0.1978 1.0000
9.750 1.1301 0.03520 0.02688 0.0038 0.1898 1.0000
10.000 1.1478 0.03628 0.02805 0.0049 0.1827 1.0000
10.250 1.1648 0.03699 0.02889 0.0062 0.1748 1.0000
10.500 1.1805 0.03808 0.03009 0.0075 0.1676 1.0000
10.750 1.1975 0.03863 0.03073 0.0087 0.1598 1.0000
11.000 1.2093 0.03990 0.03216 0.0104 0.1528 1.0000
11.250 1.2272 0.04028 0.03253 0.0115 0.1454 1.0000
11.500 1.2335 0.04189 0.03437 0.0136 0.1388 1.0000
11.750 1.2514 0.04218 0.03461 0.0147 0.1317 1.0000
12.000 1.2516 0.04416 0.03687 0.0172 0.1260 1.0000
12.250 1.2629 0.04483 0.03754 0.0188 0.1196 1.0000
12.500 1.2637 0.04673 0.03958 0.0210 0.1147 1.0000
12.750 1.2513 0.04892 0.04204 0.0243 0.1108 1.0000
13.000 1.2742 0.04924 0.04211 0.0249 0.1046 1.0000
13.250 1.2490 0.05267 0.04593 0.0278 0.1027 1.0000
13.500 1.2259 0.05661 0.05017 0.0290 0.1008 1.0000
13.750 1.2048 0.06092 0.05471 0.0289 0.0988 1.0000
14.000 1.0684 0.08320 0.07768 0.0169 0.1081 1.0000
14.250 1.0478 0.09022 0.08474 0.0133 0.1063 1.0000
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Polar data table (+)
Polar graphs
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