NACA 25112 (naca25112-jf) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 25112 (naca25112-jf) Reynolds number: 50,000 Max Cl/Cd: 28.59 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca25112-jf-50000-n5.txt Download as CSV file: xf-naca25112-jf-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 25112
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5300 0.10239 0.09522 -0.0114 1.0000 0.0685
-9.750 -0.5276 0.09801 0.09086 -0.0131 1.0000 0.0679
-9.500 -0.5301 0.09287 0.08577 -0.0163 1.0000 0.0675
-9.250 -0.5369 0.08744 0.08036 -0.0200 1.0000 0.0672
-9.000 -0.5472 0.08246 0.07539 -0.0223 1.0000 0.0670
-8.750 -0.5580 0.07776 0.07064 -0.0236 1.0000 0.0669
-8.500 -0.5667 0.07298 0.06576 -0.0245 1.0000 0.0670
-8.250 -0.5730 0.06835 0.06097 -0.0247 1.0000 0.0673
-8.000 -0.5766 0.06385 0.05626 -0.0244 1.0000 0.0675
-7.750 -0.5771 0.05955 0.05169 -0.0236 1.0000 0.0677
-7.500 -0.5748 0.05545 0.04726 -0.0224 1.0000 0.0679
-7.250 -0.5719 0.05138 0.04274 -0.0207 1.0000 0.0685
-7.000 -0.5586 0.04904 0.04037 -0.0196 1.0000 0.0702
-6.750 -0.5447 0.04701 0.03824 -0.0183 1.0000 0.0724
-6.500 -0.5327 0.04446 0.03541 -0.0167 1.0000 0.0743
-6.250 -0.5205 0.04175 0.03235 -0.0148 1.0000 0.0757
-6.000 -0.5075 0.03922 0.02941 -0.0128 1.0000 0.0779
-5.750 -0.4938 0.03696 0.02672 -0.0108 1.0000 0.0807
-5.500 -0.4776 0.03554 0.02531 -0.0093 1.0000 0.0833
-5.250 -0.4615 0.03403 0.02364 -0.0076 1.0000 0.0859
-5.000 -0.4460 0.03264 0.02200 -0.0058 1.0000 0.0896
-4.750 -0.4284 0.03126 0.02033 -0.0043 0.9988 0.0936
-4.500 -0.3831 0.02972 0.01873 -0.0082 0.9828 0.0996
-4.250 -0.3376 0.02824 0.01695 -0.0116 0.9659 0.1082
-4.000 -0.2917 0.02702 0.01570 -0.0150 0.9484 0.1176
-3.750 -0.2462 0.02588 0.01452 -0.0181 0.9299 0.1287
-3.500 -0.2016 0.02491 0.01348 -0.0210 0.9103 0.1431
-3.250 -0.1607 0.02402 0.01255 -0.0231 0.8898 0.1604
-3.000 -0.1274 0.02325 0.01178 -0.0238 0.8663 0.1809
-2.750 -0.0979 0.02249 0.01107 -0.0238 0.8439 0.2080
-2.500 -0.0733 0.02164 0.01042 -0.0230 0.8229 0.2500
-2.250 -0.0574 0.02021 0.00982 -0.0208 0.8027 0.3763
-2.000 0.0254 0.02006 0.01113 -0.0248 0.7849 0.9239
-1.750 0.1239 0.02027 0.01077 -0.0369 0.7616 0.9927
-1.500 0.1584 0.02019 0.01037 -0.0382 0.7410 1.0000
-1.250 0.1805 0.02020 0.01013 -0.0372 0.7226 1.0000
-1.000 0.2030 0.02024 0.00993 -0.0362 0.7055 1.0000
-0.750 0.2257 0.02030 0.00978 -0.0354 0.6893 1.0000
-0.500 0.2486 0.02038 0.00967 -0.0346 0.6743 1.0000
-0.250 0.2714 0.02049 0.00960 -0.0337 0.6602 1.0000
0.000 0.2943 0.02061 0.00955 -0.0329 0.6471 1.0000
0.250 0.3172 0.02074 0.00953 -0.0320 0.6350 1.0000
0.500 0.3403 0.02092 0.00960 -0.0313 0.6221 1.0000
0.750 0.3633 0.02111 0.00968 -0.0305 0.6104 1.0000
1.250 0.4092 0.02154 0.00992 -0.0289 0.5886 1.0000
1.500 0.4322 0.02178 0.01008 -0.0281 0.5783 1.0000
1.750 0.4554 0.02203 0.01024 -0.0273 0.5686 1.0000
2.000 0.4783 0.02235 0.01054 -0.0266 0.5581 1.0000
2.250 0.5015 0.02260 0.01067 -0.0256 0.5497 1.0000
2.500 0.5240 0.02298 0.01109 -0.0250 0.5392 1.0000
2.750 0.5468 0.02330 0.01134 -0.0241 0.5307 1.0000
3.000 0.5691 0.02369 0.01175 -0.0232 0.5210 1.0000
3.250 0.5916 0.02407 0.01211 -0.0224 0.5126 1.0000
3.500 0.6138 0.02448 0.01252 -0.0215 0.5036 1.0000
3.750 0.6359 0.02492 0.01298 -0.0206 0.4950 1.0000
4.000 0.6580 0.02535 0.01342 -0.0196 0.4865 1.0000
4.250 0.6796 0.02584 0.01395 -0.0187 0.4779 1.0000
4.500 0.7015 0.02629 0.01444 -0.0177 0.4696 1.0000
4.750 0.7227 0.02685 0.01505 -0.0168 0.4612 1.0000
5.000 0.7444 0.02731 0.01554 -0.0157 0.4529 1.0000
5.250 0.7650 0.02793 0.01624 -0.0147 0.4445 1.0000
5.500 0.7864 0.02841 0.01678 -0.0137 0.4363 1.0000
5.750 0.8062 0.02908 0.01755 -0.0126 0.4277 1.0000
6.000 0.8275 0.02957 0.01809 -0.0115 0.4197 1.0000
6.250 0.8464 0.03031 0.01897 -0.0104 0.4108 1.0000
6.500 0.8678 0.03077 0.01948 -0.0093 0.4029 1.0000
6.750 0.8854 0.03161 0.02047 -0.0081 0.3937 1.0000
7.000 0.9076 0.03198 0.02087 -0.0070 0.3859 1.0000
7.250 0.9232 0.03295 0.02205 -0.0056 0.3762 1.0000
7.500 0.9472 0.03313 0.02223 -0.0046 0.3687 1.0000
7.750 0.9603 0.03427 0.02360 -0.0031 0.3582 1.0000
8.000 0.9806 0.03474 0.02416 -0.0019 0.3497 1.0000
8.250 0.9975 0.03546 0.02502 -0.0006 0.3399 1.0000
8.500 1.0119 0.03636 0.02608 0.0009 0.3298 1.0000
8.750 1.0363 0.03632 0.02602 0.0020 0.3210 1.0000
9.000 1.0452 0.03757 0.02755 0.0038 0.3096 1.0000
9.250 1.0582 0.03842 0.02854 0.0054 0.2989 1.0000
9.500 1.0774 0.03862 0.02876 0.0068 0.2886 1.0000
9.750 1.0878 0.03951 0.02980 0.0086 0.2770 1.0000
10.000 1.0938 0.04074 0.03122 0.0105 0.2655 1.0000
10.250 1.1024 0.04165 0.03222 0.0123 0.2543 1.0000
10.500 1.1130 0.04227 0.03286 0.0142 0.2431 1.0000
10.750 1.1127 0.04376 0.03447 0.0163 0.2321 1.0000
11.000 1.1051 0.04589 0.03671 0.0185 0.2223 1.0000
11.250 1.1056 0.04745 0.03829 0.0200 0.2121 1.0000
11.500 1.1040 0.04945 0.04035 0.0209 0.2019 1.0000
11.750 1.0908 0.05320 0.04426 0.0208 0.1928 1.0000
12.000 1.0892 0.05569 0.04675 0.0210 0.1832 1.0000
12.250 1.0858 0.05856 0.04965 0.0208 0.1736 1.0000
12.500 1.0706 0.06347 0.05470 0.0194 0.1656 1.0000
12.750 1.0729 0.06572 0.05689 0.0195 0.1567 1.0000
13.000 1.0549 0.07146 0.06280 0.0175 0.1496 1.0000
13.250 1.0534 0.07450 0.06582 0.0170 0.1419 1.0000
13.500 1.0361 0.08045 0.07191 0.0148 0.1358 1.0000
13.750 1.0364 0.08334 0.07476 0.0144 0.1290 1.0000
14.000 1.0051 0.09227 0.08390 0.0105 0.1247 1.0000
14.250 1.0245 0.09161 0.08311 0.0121 0.1174 1.0000
14.500 0.9736 0.10505 0.09679 0.0056 0.1150 1.0000
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Polar data table (+)
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