NACA 2408 (naca2408-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2408 (naca2408-il) Reynolds number: 500,000 Max Cl/Cd: 67.51 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2408-il-500000-n5.txt Download as CSV file: xf-naca2408-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5791 0.11822 0.11586 0.0023 1.0000 0.0067
-11.000 -0.5806 0.11304 0.11070 0.0002 1.0000 0.0068
-10.500 -0.8500 0.03401 0.03087 -0.0518 1.0000 0.0059
-10.250 -0.8446 0.02992 0.02640 -0.0521 1.0000 0.0060
-10.000 -0.8315 0.02744 0.02364 -0.0517 1.0000 0.0062
-9.750 -0.8151 0.02561 0.02159 -0.0511 1.0000 0.0064
-9.500 -0.7974 0.02404 0.01982 -0.0504 1.0000 0.0066
-9.250 -0.7791 0.02260 0.01818 -0.0496 1.0000 0.0068
-9.000 -0.7604 0.02124 0.01662 -0.0487 1.0000 0.0071
-8.750 -0.7409 0.01999 0.01516 -0.0477 1.0000 0.0074
-8.500 -0.7206 0.01893 0.01391 -0.0468 1.0000 0.0078
-8.250 -0.6997 0.01803 0.01280 -0.0458 1.0000 0.0082
-8.000 -0.6796 0.01690 0.01150 -0.0448 1.0000 0.0086
-7.750 -0.6585 0.01605 0.01053 -0.0439 1.0000 0.0092
-7.500 -0.6367 0.01540 0.00978 -0.0429 1.0000 0.0097
-7.250 -0.6147 0.01478 0.00906 -0.0420 1.0000 0.0103
-7.000 -0.5840 0.01409 0.00825 -0.0429 0.9984 0.0111
-6.750 -0.5521 0.01350 0.00752 -0.0440 0.9964 0.0118
-6.500 -0.5199 0.01282 0.00677 -0.0453 0.9947 0.0137
-6.250 -0.4884 0.01243 0.00636 -0.0462 0.9921 0.0154
-6.000 -0.4560 0.01202 0.00586 -0.0473 0.9895 0.0171
-5.750 -0.4226 0.01158 0.00541 -0.0487 0.9871 0.0200
-5.500 -0.3888 0.01134 0.00515 -0.0501 0.9843 0.0234
-5.250 -0.3557 0.01115 0.00488 -0.0513 0.9802 0.0255
-5.000 -0.3225 0.01067 0.00437 -0.0525 0.9768 0.0287
-4.750 -0.2918 0.01042 0.00410 -0.0532 0.9718 0.0315
-4.500 -0.2604 0.01018 0.00381 -0.0540 0.9669 0.0337
-4.250 -0.2291 0.00997 0.00354 -0.0548 0.9620 0.0352
-4.000 -0.1997 0.00961 0.00314 -0.0551 0.9551 0.0379
-3.750 -0.1693 0.00932 0.00284 -0.0556 0.9490 0.0408
-3.500 -0.1406 0.00909 0.00258 -0.0557 0.9408 0.0438
-3.250 -0.1116 0.00890 0.00235 -0.0559 0.9326 0.0468
-3.000 -0.0832 0.00866 0.00212 -0.0559 0.9232 0.0554
-2.750 -0.0556 0.00844 0.00194 -0.0558 0.9124 0.0715
-2.500 -0.0282 0.00822 0.00178 -0.0556 0.9010 0.0943
-2.250 -0.0009 0.00803 0.00164 -0.0554 0.8888 0.1192
-2.000 0.0262 0.00785 0.00151 -0.0552 0.8754 0.1484
-1.750 0.0532 0.00768 0.00140 -0.0550 0.8611 0.1808
-1.500 0.0801 0.00752 0.00132 -0.0547 0.8458 0.2194
-1.250 0.1069 0.00733 0.00124 -0.0545 0.8296 0.2713
-1.000 0.1335 0.00712 0.00118 -0.0542 0.8128 0.3351
-0.750 0.1593 0.00676 0.00113 -0.0540 0.7949 0.4474
-0.500 0.1846 0.00638 0.00112 -0.0535 0.7767 0.5784
-0.250 0.2100 0.00615 0.00111 -0.0529 0.7573 0.6675
0.000 0.2339 0.00591 0.00114 -0.0519 0.7375 0.7672
0.250 0.2554 0.00569 0.00119 -0.0500 0.7172 0.8755
0.500 0.2855 0.00569 0.00121 -0.0500 0.6940 0.9491
0.750 0.3220 0.00587 0.00120 -0.0519 0.6513 0.9843
1.000 0.3552 0.00611 0.00121 -0.0531 0.6056 1.0000
1.250 0.3806 0.00631 0.00125 -0.0526 0.5706 1.0000
1.500 0.4061 0.00653 0.00130 -0.0521 0.5351 1.0000
1.750 0.4317 0.00676 0.00137 -0.0516 0.5004 1.0000
2.000 0.4575 0.00700 0.00145 -0.0513 0.4650 1.0000
2.250 0.4831 0.00726 0.00155 -0.0509 0.4261 1.0000
2.500 0.5086 0.00757 0.00167 -0.0505 0.3816 1.0000
2.750 0.5340 0.00791 0.00181 -0.0501 0.3345 1.0000
3.000 0.5588 0.00835 0.00199 -0.0497 0.2771 1.0000
3.250 0.5822 0.00903 0.00229 -0.0491 0.1900 1.0000
3.500 0.6065 0.00959 0.00257 -0.0487 0.1297 1.0000
3.750 0.6312 0.01010 0.00286 -0.0483 0.0852 1.0000
4.000 0.6562 0.01057 0.00316 -0.0479 0.0481 1.0000
4.250 0.6821 0.01088 0.00343 -0.0476 0.0406 1.0000
4.500 0.7084 0.01113 0.00369 -0.0473 0.0372 1.0000
4.750 0.7347 0.01139 0.00398 -0.0470 0.0360 1.0000
5.000 0.7608 0.01167 0.00432 -0.0467 0.0348 1.0000
5.250 0.7867 0.01198 0.00467 -0.0464 0.0334 1.0000
5.500 0.8121 0.01235 0.00507 -0.0460 0.0315 1.0000
5.750 0.8371 0.01279 0.00555 -0.0456 0.0295 1.0000
6.000 0.8608 0.01342 0.00627 -0.0449 0.0271 1.0000
6.250 0.8863 0.01374 0.00662 -0.0446 0.0264 1.0000
6.500 0.9118 0.01404 0.00697 -0.0443 0.0254 1.0000
6.750 0.9369 0.01439 0.00738 -0.0439 0.0239 1.0000
7.000 0.9619 0.01475 0.00779 -0.0435 0.0220 1.0000
7.250 0.9865 0.01515 0.00823 -0.0431 0.0202 1.0000
7.500 1.0089 0.01586 0.00897 -0.0423 0.0179 1.0000
7.750 1.0344 0.01611 0.00928 -0.0420 0.0168 1.0000
8.000 1.0590 0.01645 0.00967 -0.0416 0.0149 1.0000
8.250 1.0833 0.01684 0.01007 -0.0412 0.0133 1.0000
8.500 1.1056 0.01750 0.01074 -0.0405 0.0117 1.0000
8.750 1.1281 0.01810 0.01145 -0.0397 0.0109 1.0000
9.000 1.1506 0.01867 0.01209 -0.0391 0.0099 1.0000
9.250 1.1728 0.01926 0.01271 -0.0384 0.0090 1.0000
9.500 1.1920 0.02022 0.01374 -0.0373 0.0080 1.0000
9.750 1.2120 0.02104 0.01469 -0.0363 0.0077 1.0000
10.000 1.2311 0.02194 0.01572 -0.0352 0.0073 1.0000
10.250 1.2494 0.02289 0.01679 -0.0340 0.0069 1.0000
10.500 1.2671 0.02387 0.01788 -0.0328 0.0066 1.0000
10.750 1.2840 0.02487 0.01900 -0.0315 0.0063 1.0000
11.000 1.2996 0.02594 0.02022 -0.0301 0.0060 1.0000
11.250 1.3122 0.02726 0.02165 -0.0284 0.0057 1.0000
11.500 1.3202 0.02895 0.02351 -0.0262 0.0054 1.0000
11.750 1.3294 0.03022 0.02495 -0.0240 0.0053 1.0000
12.000 1.3360 0.03164 0.02654 -0.0217 0.0051 1.0000
12.250 1.3405 0.03323 0.02831 -0.0194 0.0050 1.0000
12.500 1.3432 0.03502 0.03027 -0.0172 0.0048 1.0000
12.750 1.3435 0.03711 0.03254 -0.0154 0.0047 1.0000
13.000 1.3421 0.03949 0.03511 -0.0139 0.0046 1.0000
13.250 1.3385 0.04229 0.03809 -0.0129 0.0045 1.0000
13.500 1.3331 0.04554 0.04153 -0.0126 0.0044 1.0000
13.750 1.3260 0.04929 0.04546 -0.0130 0.0044 1.0000
14.000 1.3162 0.05377 0.05014 -0.0142 0.0043 1.0000
14.250 1.3043 0.05896 0.05551 -0.0163 0.0043 1.0000
14.500 1.2891 0.06515 0.06189 -0.0194 0.0043 1.0000
14.750 1.2700 0.07247 0.06941 -0.0234 0.0043 1.0000
15.000 1.2463 0.08113 0.07826 -0.0284 0.0043 1.0000
15.250 1.2165 0.09154 0.08888 -0.0344 0.0043 1.0000
15.500 1.1795 0.10425 0.10178 -0.0415 0.0044 1.0000
15.750 1.1316 0.12048 0.11821 -0.0502 0.0046 1.0000
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