NACA 2408 (naca2408-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2408 (naca2408-il) Reynolds number: 100,000 Max Cl/Cd: 48.88 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2408-il-100000-n5.txt Download as CSV file: xf-naca2408-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5343 0.09125 0.08624 -0.0164 1.0000 0.0281
-8.750 -0.5388 0.08566 0.08072 -0.0199 1.0000 0.0277
-8.500 -0.5469 0.07927 0.07442 -0.0247 1.0000 0.0271
-8.000 -0.5624 0.05876 0.05368 -0.0421 1.0000 0.0256
-7.500 -0.5629 0.04670 0.04104 -0.0461 1.0000 0.0259
-7.250 -0.5531 0.04368 0.03788 -0.0461 1.0000 0.0269
-7.000 -0.5388 0.04185 0.03593 -0.0458 1.0000 0.0286
-6.750 -0.5266 0.03828 0.03197 -0.0455 1.0000 0.0303
-6.500 -0.5133 0.03408 0.02720 -0.0449 1.0000 0.0316
-6.250 -0.4969 0.03039 0.02287 -0.0440 1.0000 0.0331
-6.000 -0.4774 0.02773 0.01955 -0.0430 1.0000 0.0357
-5.750 -0.4577 0.02606 0.01779 -0.0423 1.0000 0.0386
-5.500 -0.4361 0.02438 0.01581 -0.0414 1.0000 0.0413
-5.250 -0.4134 0.02306 0.01407 -0.0405 1.0000 0.0458
-5.000 -0.3913 0.02157 0.01248 -0.0397 1.0000 0.0495
-4.750 -0.3685 0.02062 0.01142 -0.0389 1.0000 0.0540
-4.500 -0.3450 0.01984 0.01036 -0.0381 1.0000 0.0591
-4.250 -0.3221 0.01876 0.00930 -0.0374 1.0000 0.0629
-4.000 -0.2988 0.01815 0.00860 -0.0367 1.0000 0.0691
-3.750 -0.2751 0.01745 0.00782 -0.0360 1.0000 0.0745
-3.500 -0.2514 0.01682 0.00718 -0.0354 1.0000 0.0804
-3.250 -0.2273 0.01626 0.00659 -0.0349 1.0000 0.0889
-3.000 -0.2030 0.01576 0.00609 -0.0345 1.0000 0.1032
-2.750 -0.1784 0.01529 0.00574 -0.0342 1.0000 0.1311
-2.500 -0.1493 0.01479 0.00549 -0.0350 0.9980 0.1863
-2.250 -0.1118 0.01430 0.00527 -0.0374 0.9920 0.2630
-2.000 -0.0751 0.01361 0.00515 -0.0398 0.9863 0.3996
-1.750 -0.0436 0.01272 0.00515 -0.0405 0.9797 0.6179
-1.500 -0.0138 0.01215 0.00519 -0.0397 0.9736 0.8226
-1.250 0.0394 0.01197 0.00501 -0.0444 0.9678 1.0000
-1.000 0.0781 0.01199 0.00485 -0.0468 0.9590 1.0000
-0.750 0.1186 0.01200 0.00471 -0.0495 0.9511 1.0000
-0.500 0.1534 0.01200 0.00460 -0.0510 0.9397 1.0000
-0.250 0.1881 0.01200 0.00450 -0.0523 0.9283 1.0000
0.000 0.2222 0.01198 0.00442 -0.0535 0.9164 1.0000
0.250 0.2558 0.01197 0.00434 -0.0545 0.9039 1.0000
0.500 0.2882 0.01195 0.00428 -0.0553 0.8903 1.0000
0.750 0.3191 0.01195 0.00424 -0.0557 0.8753 1.0000
1.000 0.3493 0.01195 0.00422 -0.0558 0.8592 1.0000
1.250 0.3788 0.01195 0.00421 -0.0558 0.8423 1.0000
1.500 0.4081 0.01197 0.00420 -0.0557 0.8247 1.0000
1.750 0.4362 0.01200 0.00423 -0.0554 0.8056 1.0000
2.000 0.4636 0.01207 0.00428 -0.0549 0.7850 1.0000
2.250 0.4912 0.01214 0.00432 -0.0544 0.7643 1.0000
2.500 0.5176 0.01225 0.00444 -0.0538 0.7412 1.0000
2.750 0.5441 0.01238 0.00455 -0.0531 0.7179 1.0000
3.000 0.5700 0.01253 0.00466 -0.0523 0.6914 1.0000
3.250 0.5945 0.01272 0.00478 -0.0511 0.6547 1.0000
3.500 0.6182 0.01297 0.00488 -0.0498 0.6110 1.0000
3.750 0.6413 0.01329 0.00501 -0.0485 0.5629 1.0000
4.000 0.6647 0.01366 0.00523 -0.0474 0.5180 1.0000
4.250 0.6876 0.01408 0.00551 -0.0463 0.4664 1.0000
4.500 0.7107 0.01454 0.00583 -0.0453 0.4171 1.0000
4.750 0.7326 0.01513 0.00620 -0.0443 0.3511 1.0000
5.000 0.7530 0.01599 0.00670 -0.0431 0.2653 1.0000
5.250 0.7714 0.01727 0.00742 -0.0420 0.1632 1.0000
5.500 0.7902 0.01862 0.00833 -0.0409 0.0962 1.0000
5.750 0.8112 0.01965 0.00927 -0.0399 0.0755 1.0000
6.000 0.8330 0.02054 0.01024 -0.0389 0.0667 1.0000
6.250 0.8535 0.02156 0.01132 -0.0378 0.0612 1.0000
6.500 0.8744 0.02251 0.01242 -0.0367 0.0572 1.0000
6.750 0.8953 0.02345 0.01345 -0.0357 0.0521 1.0000
7.000 0.9136 0.02481 0.01479 -0.0344 0.0487 1.0000
7.250 0.9346 0.02597 0.01615 -0.0333 0.0455 1.0000
7.500 0.9551 0.02718 0.01750 -0.0323 0.0414 1.0000
7.750 0.9745 0.02888 0.01922 -0.0312 0.0387 1.0000
8.000 0.9951 0.03080 0.02133 -0.0302 0.0358 1.0000
8.250 1.0157 0.03259 0.02341 -0.0291 0.0329 1.0000
8.500 1.0352 0.03471 0.02578 -0.0280 0.0308 1.0000
8.750 1.0523 0.03676 0.02797 -0.0270 0.0286 1.0000
9.000 1.0659 0.04003 0.03148 -0.0257 0.0266 1.0000
9.250 1.0784 0.04265 0.03461 -0.0239 0.0255 1.0000
9.500 1.0863 0.04591 0.03837 -0.0219 0.0247 1.0000
9.750 1.0894 0.04939 0.04240 -0.0197 0.0239 1.0000
10.000 1.0880 0.05289 0.04632 -0.0174 0.0231 1.0000
10.250 1.0824 0.05635 0.05015 -0.0152 0.0223 1.0000
10.500 1.0712 0.05967 0.05375 -0.0128 0.0218 1.0000
10.750 1.0561 0.06330 0.05764 -0.0110 0.0215 1.0000
11.000 1.0376 0.06767 0.06224 -0.0106 0.0214 1.0000
11.250 1.0156 0.07314 0.06795 -0.0122 0.0215 1.0000
11.500 0.9902 0.08024 0.07526 -0.0160 0.0220 1.0000
11.750 0.9625 0.08936 0.08450 -0.0224 0.0227 1.0000
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Polar data table (+)
Polar graphs
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