NACA 2408 (naca2408-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2408 (naca2408-il) Reynolds number: 500,000 Max Cl/Cd: 80.56 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca2408-il-500000.txt Download as CSV file: xf-naca2408-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5372 0.10797 0.10566 -0.0038 1.0000 0.0208
-9.750 -0.5347 0.10401 0.10171 -0.0057 1.0000 0.0215
-8.250 -0.6631 0.02974 0.02622 -0.0489 1.0000 0.0126
-8.000 -0.6535 0.02627 0.02235 -0.0476 1.0000 0.0129
-7.750 -0.6375 0.02446 0.02032 -0.0465 1.0000 0.0134
-7.500 -0.6185 0.02359 0.01931 -0.0454 1.0000 0.0141
-7.250 -0.6000 0.02233 0.01787 -0.0441 1.0000 0.0149
-7.000 -0.5822 0.02049 0.01573 -0.0428 1.0000 0.0157
-6.750 -0.5631 0.01883 0.01379 -0.0414 1.0000 0.0165
-6.500 -0.5422 0.01782 0.01255 -0.0402 1.0000 0.0171
-6.250 -0.5228 0.01515 0.00951 -0.0391 1.0000 0.0187
-6.000 -0.5005 0.01481 0.00915 -0.0382 1.0000 0.0204
-5.750 -0.4779 0.01448 0.00876 -0.0374 1.0000 0.0225
-5.500 -0.4548 0.01399 0.00817 -0.0365 1.0000 0.0245
-5.250 -0.4271 0.01293 0.00696 -0.0367 0.9994 0.0273
-5.000 -0.3903 0.01254 0.00656 -0.0388 0.9971 0.0316
-4.750 -0.3529 0.01234 0.00628 -0.0409 0.9951 0.0351
-4.500 -0.3189 0.01137 0.00527 -0.0425 0.9927 0.0404
-4.250 -0.2830 0.01106 0.00491 -0.0443 0.9898 0.0444
-4.000 -0.2458 0.01083 0.00463 -0.0463 0.9874 0.0468
-3.750 -0.2095 0.01012 0.00388 -0.0483 0.9854 0.0510
-3.500 -0.1754 0.00979 0.00353 -0.0497 0.9812 0.0547
-3.250 -0.1385 0.00948 0.00318 -0.0516 0.9783 0.0587
-3.000 -0.1004 0.00905 0.00279 -0.0539 0.9763 0.0717
-2.750 -0.0671 0.00851 0.00249 -0.0552 0.9716 0.1258
-2.500 -0.0329 0.00810 0.00231 -0.0567 0.9672 0.1868
-2.250 0.0008 0.00774 0.00215 -0.0580 0.9627 0.2466
-2.000 0.0301 0.00740 0.00202 -0.0583 0.9548 0.3087
-1.750 0.0596 0.00702 0.00189 -0.0587 0.9476 0.3871
-1.500 0.0865 0.00652 0.00179 -0.0586 0.9384 0.5061
-1.250 0.1110 0.00599 0.00174 -0.0577 0.9276 0.6506
-1.000 0.1333 0.00550 0.00172 -0.0561 0.9164 0.7878
-0.750 0.1543 0.00518 0.00175 -0.0536 0.9046 0.9214
-0.500 0.1985 0.00514 0.00169 -0.0567 0.8947 0.9839
-0.250 0.2396 0.00512 0.00160 -0.0594 0.8818 1.0000
0.000 0.2651 0.00513 0.00153 -0.0587 0.8654 1.0000
0.250 0.2906 0.00517 0.00147 -0.0581 0.8472 1.0000
0.500 0.3159 0.00522 0.00142 -0.0573 0.8247 1.0000
0.750 0.3407 0.00532 0.00137 -0.0564 0.7950 1.0000
1.000 0.3658 0.00544 0.00135 -0.0556 0.7642 1.0000
1.250 0.3911 0.00558 0.00135 -0.0549 0.7336 1.0000
1.500 0.4164 0.00574 0.00136 -0.0542 0.7004 1.0000
1.750 0.4417 0.00593 0.00140 -0.0536 0.6663 1.0000
2.000 0.4670 0.00613 0.00145 -0.0530 0.6315 1.0000
2.250 0.4925 0.00635 0.00152 -0.0524 0.5963 1.0000
2.500 0.5179 0.00659 0.00162 -0.0519 0.5612 1.0000
2.750 0.5437 0.00681 0.00172 -0.0515 0.5298 1.0000
3.000 0.5694 0.00707 0.00184 -0.0511 0.4936 1.0000
3.250 0.5945 0.00738 0.00198 -0.0506 0.4480 1.0000
3.500 0.6197 0.00772 0.00214 -0.0501 0.4019 1.0000
3.750 0.6441 0.00820 0.00235 -0.0496 0.3373 1.0000
4.000 0.6673 0.00887 0.00265 -0.0490 0.2524 1.0000
4.250 0.6893 0.00976 0.00307 -0.0483 0.1540 1.0000
4.500 0.7117 0.01063 0.00356 -0.0476 0.0766 1.0000
4.750 0.7367 0.01112 0.00393 -0.0471 0.0546 1.0000
5.000 0.7622 0.01153 0.00434 -0.0467 0.0483 1.0000
5.250 0.7877 0.01190 0.00476 -0.0463 0.0453 1.0000
5.500 0.8128 0.01236 0.00525 -0.0458 0.0425 1.0000
5.750 0.8367 0.01297 0.00590 -0.0451 0.0393 1.0000
6.000 0.8597 0.01371 0.00674 -0.0443 0.0373 1.0000
6.250 0.8845 0.01414 0.00723 -0.0438 0.0359 1.0000
6.500 0.9085 0.01469 0.00785 -0.0432 0.0339 1.0000
6.750 0.9319 0.01531 0.00851 -0.0426 0.0311 1.0000
7.000 0.9485 0.01711 0.01040 -0.0409 0.0272 1.0000
7.250 0.9735 0.01745 0.01083 -0.0404 0.0258 1.0000
7.500 0.9981 0.01786 0.01131 -0.0399 0.0233 1.0000
7.750 1.0218 0.01835 0.01184 -0.0394 0.0208 1.0000
8.000 1.0417 0.01952 0.01304 -0.0383 0.0188 1.0000
8.250 1.0600 0.02130 0.01497 -0.0369 0.0173 1.0000
8.500 1.0833 0.02183 0.01560 -0.0362 0.0161 1.0000
8.750 1.1059 0.02239 0.01625 -0.0355 0.0147 1.0000
9.000 1.1280 0.02290 0.01684 -0.0349 0.0137 1.0000
9.250 1.1484 0.02371 0.01771 -0.0340 0.0129 1.0000
9.500 1.1572 0.02754 0.02187 -0.0316 0.0119 1.0000
9.750 1.1737 0.02917 0.02371 -0.0302 0.0115 1.0000
10.000 1.1882 0.03107 0.02587 -0.0285 0.0112 1.0000
10.250 1.1995 0.03333 0.02839 -0.0266 0.0108 1.0000
10.500 1.2088 0.03551 0.03083 -0.0246 0.0103 1.0000
10.750 1.2172 0.03738 0.03290 -0.0227 0.0099 1.0000
11.000 1.2243 0.03902 0.03470 -0.0207 0.0095 1.0000
11.250 1.2247 0.04088 0.03675 -0.0180 0.0093 1.0000
11.500 1.2177 0.04344 0.03952 -0.0149 0.0091 1.0000
11.750 1.2072 0.04645 0.04275 -0.0125 0.0090 1.0000
12.000 1.1929 0.05015 0.04668 -0.0110 0.0090 1.0000
12.250 1.1711 0.05534 0.05213 -0.0108 0.0090 1.0000
12.500 1.1430 0.06224 0.05931 -0.0128 0.0091 1.0000
12.750 1.0839 0.07634 0.07384 -0.0207 0.0095 1.0000
13.000 1.0398 0.09048 0.08823 -0.0307 0.0099 1.0000
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Polar data table (+)
Polar graphs
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