NACA 23112 (naca23112-jf) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 23112 (naca23112-jf) Reynolds number: 50,000 Max Cl/Cd: 27.32 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca23112-jf-50000-n5.txt Download as CSV file: xf-naca23112-jf-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 23112
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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4493 0.13046 0.12352 -0.0066 1.0000 0.1374
-11.500 -0.4474 0.12617 0.11927 -0.0074 1.0000 0.1379
-11.250 -0.5767 0.12035 0.11294 -0.0042 1.0000 0.0772
-11.000 -0.5568 0.11742 0.10995 -0.0014 1.0000 0.0736
-10.500 -0.5817 0.10164 0.09424 -0.0139 1.0000 0.0646
-10.250 -0.5832 0.09643 0.08905 -0.0166 1.0000 0.0642
-10.000 -0.5897 0.09098 0.08362 -0.0198 1.0000 0.0637
-9.750 -0.6004 0.08577 0.07839 -0.0226 1.0000 0.0633
-9.500 -0.6141 0.08109 0.07368 -0.0241 1.0000 0.0629
-9.250 -0.6285 0.07695 0.06946 -0.0242 1.0000 0.0626
-9.000 -0.6393 0.07281 0.06519 -0.0241 1.0000 0.0625
-8.750 -0.6466 0.06885 0.06104 -0.0234 1.0000 0.0625
-8.500 -0.6504 0.06503 0.05701 -0.0224 1.0000 0.0625
-8.250 -0.6507 0.06136 0.05307 -0.0212 1.0000 0.0624
-8.000 -0.6479 0.05783 0.04926 -0.0197 1.0000 0.0623
-7.750 -0.6426 0.05449 0.04560 -0.0181 1.0000 0.0623
-7.500 -0.6349 0.05135 0.04211 -0.0163 1.0000 0.0625
-7.250 -0.6259 0.04848 0.03881 -0.0143 1.0000 0.0635
-7.000 -0.6157 0.04593 0.03570 -0.0120 1.0000 0.0649
-6.750 -0.5997 0.04341 0.03311 -0.0108 1.0000 0.0664
-6.500 -0.5827 0.04122 0.03075 -0.0094 1.0000 0.0676
-6.250 -0.5648 0.03910 0.02839 -0.0079 1.0000 0.0686
-6.000 -0.5461 0.03725 0.02631 -0.0064 1.0000 0.0706
-5.750 -0.5267 0.03558 0.02437 -0.0049 1.0000 0.0734
-5.500 -0.5062 0.03400 0.02243 -0.0033 1.0000 0.0759
-5.250 -0.4838 0.03233 0.02057 -0.0021 1.0000 0.0776
-5.000 -0.4613 0.03086 0.01914 -0.0012 1.0000 0.0807
-4.750 -0.4386 0.02968 0.01792 -0.0001 1.0000 0.0849
-4.500 -0.4146 0.02859 0.01668 0.0010 1.0000 0.0886
-4.250 -0.3906 0.02745 0.01556 0.0020 1.0000 0.0926
-4.000 -0.3688 0.02654 0.01471 0.0031 1.0000 0.0983
-3.750 -0.3474 0.02579 0.01386 0.0045 1.0000 0.1036
-3.500 -0.3283 0.02496 0.01308 0.0059 1.0000 0.1099
-3.250 -0.3103 0.02431 0.01241 0.0075 1.0000 0.1180
-3.000 -0.2932 0.02363 0.01175 0.0090 1.0000 0.1265
-2.750 -0.2759 0.02303 0.01116 0.0104 1.0000 0.1394
-2.500 -0.2535 0.02222 0.01053 0.0106 0.9966 0.1623
-2.250 -0.2286 0.01929 0.01030 0.0106 0.9838 0.6073
-2.000 -0.1757 0.01961 0.01126 0.0102 0.9735 0.8429
-1.750 -0.0857 0.02055 0.01195 0.0017 0.9679 0.9332
-1.500 0.0322 0.02074 0.01178 -0.0140 0.9608 0.9815
-1.250 0.0971 0.02035 0.01118 -0.0215 0.9301 0.9898
-1.000 0.1563 0.01994 0.01058 -0.0277 0.8944 0.9987
-0.750 0.1918 0.01966 0.01012 -0.0292 0.8547 1.0000
-0.500 0.2176 0.01946 0.00975 -0.0287 0.8151 1.0000
-0.250 0.2403 0.01933 0.00942 -0.0274 0.7773 1.0000
0.000 0.2613 0.01927 0.00914 -0.0258 0.7413 1.0000
0.250 0.2818 0.01926 0.00892 -0.0241 0.7066 1.0000
0.750 0.3222 0.01941 0.00864 -0.0209 0.6403 1.0000
1.000 0.3426 0.01954 0.00858 -0.0194 0.6091 1.0000
1.250 0.3632 0.01972 0.00856 -0.0179 0.5793 1.0000
1.500 0.3839 0.01994 0.00858 -0.0165 0.5516 1.0000
1.750 0.4047 0.02018 0.00864 -0.0152 0.5257 1.0000
2.000 0.4258 0.02047 0.00876 -0.0140 0.5019 1.0000
2.250 0.4469 0.02077 0.00893 -0.0128 0.4795 1.0000
2.500 0.4683 0.02111 0.00912 -0.0116 0.4597 1.0000
2.750 0.4905 0.02148 0.00935 -0.0107 0.4418 1.0000
3.000 0.5128 0.02187 0.00965 -0.0097 0.4253 1.0000
3.250 0.5351 0.02228 0.00998 -0.0088 0.4100 1.0000
3.500 0.5574 0.02272 0.01036 -0.0079 0.3963 1.0000
3.750 0.5798 0.02318 0.01077 -0.0070 0.3839 1.0000
4.000 0.6022 0.02366 0.01115 -0.0061 0.3730 1.0000
4.250 0.6244 0.02417 0.01167 -0.0052 0.3618 1.0000
4.500 0.6468 0.02472 0.01223 -0.0043 0.3520 1.0000
4.750 0.6691 0.02525 0.01271 -0.0034 0.3430 1.0000
5.000 0.6910 0.02588 0.01340 -0.0025 0.3336 1.0000
5.250 0.7135 0.02646 0.01391 -0.0016 0.3260 1.0000
5.500 0.7348 0.02716 0.01477 -0.0007 0.3173 1.0000
5.750 0.7572 0.02778 0.01534 0.0001 0.3102 1.0000
6.000 0.7781 0.02858 0.01628 0.0010 0.3023 1.0000
6.250 0.8000 0.02928 0.01702 0.0019 0.2955 1.0000
6.500 0.8208 0.03013 0.01798 0.0028 0.2884 1.0000
6.750 0.8417 0.03095 0.01890 0.0037 0.2813 1.0000
7.000 0.8636 0.03176 0.01972 0.0045 0.2754 1.0000
7.250 0.8820 0.03283 0.02105 0.0056 0.2681 1.0000
7.500 0.9042 0.03358 0.02179 0.0063 0.2623 1.0000
7.750 0.9213 0.03483 0.02329 0.0074 0.2555 1.0000
8.000 0.9406 0.03584 0.02445 0.0084 0.2492 1.0000
8.250 0.9612 0.03678 0.02543 0.0092 0.2436 1.0000
8.500 0.9746 0.03830 0.02727 0.0105 0.2366 1.0000
8.750 0.9958 0.03914 0.02814 0.0113 0.2311 1.0000
9.000 1.0076 0.04080 0.03011 0.0126 0.2248 1.0000
9.250 1.0218 0.04216 0.03166 0.0138 0.2185 1.0000
9.500 1.0437 0.04292 0.03239 0.0145 0.2134 1.0000
9.750 1.0435 0.04546 0.03538 0.0165 0.2067 1.0000
10.000 1.0610 0.04637 0.03638 0.0175 0.2010 1.0000
10.250 1.0660 0.04844 0.03868 0.0190 0.1956 1.0000
10.500 1.0621 0.05108 0.04162 0.0208 0.1899 1.0000
10.750 1.0896 0.05096 0.04143 0.0215 0.1844 1.0000
11.000 1.0620 0.05552 0.04638 0.0237 0.1802 1.0000
11.250 1.0221 0.06098 0.05208 0.0254 0.1772 1.0000
11.500 0.9132 0.07824 0.06943 0.0172 0.1750 1.0000
11.750 1.0200 0.06586 0.05709 0.0261 0.1685 1.0000
12.000 0.8240 0.10265 0.09378 0.0037 0.1627 1.0000
12.250 0.8305 0.10511 0.09630 0.0035 0.1581 1.0000
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Polar data table (+)
Polar graphs
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