NACA 2408 (naca2408-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2408 (naca2408-il) Reynolds number: 50,000 Max Cl/Cd: 36.67 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2408-il-50000-n5.txt Download as CSV file: xf-naca2408-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2408
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5217 0.09473 0.08766 -0.0178 1.0000 0.0540
-8.500 -0.5231 0.09027 0.08328 -0.0204 1.0000 0.0537
-8.250 -0.5256 0.08569 0.07878 -0.0234 1.0000 0.0537
-8.000 -0.5262 0.08051 0.07364 -0.0278 1.0000 0.0537
-7.750 -0.5256 0.07499 0.06813 -0.0321 1.0000 0.0538
-7.500 -0.5240 0.06940 0.06249 -0.0359 1.0000 0.0540
-7.250 -0.5214 0.06382 0.05679 -0.0391 1.0000 0.0543
-7.000 -0.5171 0.05833 0.05109 -0.0415 1.0000 0.0546
-6.750 -0.5105 0.05301 0.04545 -0.0431 1.0000 0.0548
-6.500 -0.5007 0.04803 0.04006 -0.0440 1.0000 0.0554
-6.250 -0.4881 0.04336 0.03481 -0.0444 1.0000 0.0573
-6.000 -0.4728 0.03947 0.03035 -0.0442 1.0000 0.0604
-5.750 -0.4546 0.03713 0.02784 -0.0436 1.0000 0.0637
-5.500 -0.4347 0.03427 0.02448 -0.0430 1.0000 0.0666
-5.250 -0.4127 0.03177 0.02120 -0.0423 1.0000 0.0729
-5.000 -0.3916 0.02988 0.01928 -0.0416 1.0000 0.0775
-4.750 -0.3684 0.02801 0.01706 -0.0408 1.0000 0.0822
-4.500 -0.3456 0.02661 0.01544 -0.0400 1.0000 0.0904
-4.250 -0.3220 0.02528 0.01385 -0.0391 1.0000 0.0972
-4.000 -0.2979 0.02396 0.01235 -0.0382 1.0000 0.1032
-3.750 -0.2740 0.02290 0.01118 -0.0373 1.0000 0.1117
-3.500 -0.2500 0.02200 0.01022 -0.0367 1.0000 0.1258
-3.250 -0.2261 0.02117 0.00942 -0.0361 1.0000 0.1483
-3.000 -0.2019 0.02027 0.00859 -0.0356 1.0000 0.1798
-2.750 -0.1780 0.01941 0.00802 -0.0353 1.0000 0.2405
-2.500 -0.1549 0.01847 0.00761 -0.0350 1.0000 0.3467
-2.250 -0.1348 0.01736 0.00736 -0.0336 1.0000 0.5143
-2.000 -0.1199 0.01639 0.00733 -0.0294 1.0000 0.7577
-1.750 -0.0793 0.01607 0.00695 -0.0313 1.0000 1.0000
-1.500 -0.0579 0.01616 0.00673 -0.0306 1.0000 1.0000
-1.250 -0.0363 0.01628 0.00657 -0.0300 1.0000 1.0000
-1.000 -0.0147 0.01644 0.00651 -0.0294 1.0000 1.0000
-0.750 0.0068 0.01664 0.00651 -0.0288 1.0000 1.0000
-0.500 0.0283 0.01687 0.00656 -0.0284 1.0000 1.0000
-0.250 0.0604 0.01717 0.00670 -0.0300 0.9950 1.0000
0.000 0.1037 0.01747 0.00686 -0.0337 0.9828 1.0000
0.250 0.1460 0.01775 0.00702 -0.0372 0.9700 1.0000
0.500 0.1874 0.01801 0.00720 -0.0403 0.9566 1.0000
0.750 0.2282 0.01823 0.00739 -0.0432 0.9428 1.0000
1.000 0.2688 0.01842 0.00757 -0.0460 0.9287 1.0000
1.250 0.3092 0.01859 0.00775 -0.0486 0.9144 1.0000
1.500 0.3476 0.01872 0.00793 -0.0507 0.8993 1.0000
1.750 0.3845 0.01882 0.00809 -0.0523 0.8835 1.0000
2.000 0.4203 0.01889 0.00825 -0.0536 0.8673 1.0000
2.250 0.4552 0.01895 0.00839 -0.0546 0.8508 1.0000
2.500 0.4851 0.01906 0.00860 -0.0546 0.8310 1.0000
2.750 0.5165 0.01912 0.00879 -0.0547 0.8120 1.0000
3.000 0.5476 0.01917 0.00894 -0.0547 0.7928 1.0000
3.250 0.5751 0.01930 0.00919 -0.0540 0.7705 1.0000
3.500 0.6044 0.01935 0.00937 -0.0534 0.7493 1.0000
3.750 0.6305 0.01951 0.00965 -0.0524 0.7245 1.0000
4.000 0.6568 0.01965 0.00991 -0.0513 0.6986 1.0000
4.250 0.6825 0.01980 0.01019 -0.0499 0.6703 1.0000
4.500 0.7067 0.01990 0.01032 -0.0481 0.6342 1.0000
4.750 0.7271 0.02003 0.01038 -0.0454 0.5814 1.0000
5.000 0.7452 0.02032 0.01042 -0.0425 0.5128 1.0000
5.250 0.7624 0.02087 0.01073 -0.0400 0.4340 1.0000
5.500 0.7793 0.02170 0.01121 -0.0379 0.3431 1.0000
5.750 0.7948 0.02305 0.01204 -0.0361 0.2373 1.0000
6.000 0.8091 0.02506 0.01345 -0.0346 0.1519 1.0000
6.250 0.8255 0.02696 0.01508 -0.0333 0.1170 1.0000
6.500 0.8433 0.02857 0.01664 -0.0320 0.0987 1.0000
6.750 0.8620 0.03009 0.01823 -0.0307 0.0888 1.0000
7.000 0.8825 0.03166 0.01998 -0.0294 0.0826 1.0000
7.250 0.9045 0.03333 0.02180 -0.0282 0.0773 1.0000
7.500 0.9267 0.03518 0.02374 -0.0273 0.0711 1.0000
7.750 0.9492 0.03700 0.02583 -0.0264 0.0649 1.0000
8.000 0.9721 0.03935 0.02828 -0.0257 0.0613 1.0000
8.250 0.9925 0.04184 0.03124 -0.0245 0.0568 1.0000
8.500 1.0105 0.04440 0.03416 -0.0234 0.0529 1.0000
8.750 1.0271 0.04733 0.03736 -0.0223 0.0507 1.0000
9.000 1.0398 0.05072 0.04097 -0.0211 0.0484 1.0000
9.250 1.0445 0.05434 0.04526 -0.0191 0.0464 1.0000
9.500 1.0455 0.05820 0.04964 -0.0173 0.0449 1.0000
9.750 1.0420 0.06233 0.05421 -0.0155 0.0442 1.0000
10.000 1.0333 0.06659 0.05883 -0.0138 0.0439 1.0000
10.250 1.0188 0.07078 0.06332 -0.0123 0.0438 1.0000
10.500 0.9999 0.07518 0.06794 -0.0115 0.0439 1.0000
10.750 0.9786 0.08028 0.07324 -0.0124 0.0442 1.0000
11.000 0.9560 0.08640 0.07951 -0.0152 0.0446 1.0000
11.250 0.9334 0.09376 0.08697 -0.0200 0.0451 1.0000
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Polar data table (+)
Polar graphs
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