NACA 2408 (naca2408-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2408 (naca2408-il) Reynolds number: 50,000 Max Cl/Cd: 37.42 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca2408-il-50000.txt Download as CSV file: xf-naca2408-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5158 0.11581 0.10876 -0.0005 1.0000 0.2147
-9.000 -0.5047 0.11139 0.10435 0.0000 1.0000 0.2243
-8.750 -0.5244 0.11068 0.10379 -0.0033 1.0000 0.2309
-8.500 -0.5127 0.10634 0.09946 -0.0023 1.0000 0.2449
-8.250 -0.5012 0.10208 0.09521 -0.0015 1.0000 0.2582
-8.000 -0.4921 0.09805 0.09121 -0.0010 1.0000 0.2692
-7.750 -0.4902 0.09472 0.08794 -0.0011 1.0000 0.2807
-7.250 -0.4846 0.08830 0.08163 -0.0003 1.0000 0.3105
-7.000 -0.4846 0.08558 0.07899 0.0007 1.0000 0.3308
-6.750 -0.4857 0.08261 0.07611 0.0014 1.0000 0.3510
-6.500 -0.4754 0.07928 0.07280 0.0035 1.0000 0.3751
-6.250 -0.4705 0.07597 0.06952 0.0049 1.0000 0.3970
-5.500 -0.4465 0.04776 0.04000 -0.0398 1.0000 0.1601
-5.250 -0.4272 0.04311 0.03498 -0.0403 1.0000 0.1525
-5.000 -0.4072 0.03925 0.03059 -0.0407 1.0000 0.1547
-4.750 -0.3850 0.03567 0.02638 -0.0408 1.0000 0.1562
-4.500 -0.3609 0.03247 0.02253 -0.0405 1.0000 0.1573
-4.250 -0.3387 0.03039 0.02033 -0.0397 1.0000 0.1676
-4.000 -0.3137 0.02816 0.01765 -0.0392 1.0000 0.1754
-3.750 -0.2883 0.02626 0.01548 -0.0385 1.0000 0.1834
-3.500 -0.2627 0.02455 0.01358 -0.0378 1.0000 0.1952
-3.250 -0.2371 0.02316 0.01202 -0.0371 1.0000 0.2177
-3.000 -0.2125 0.02182 0.01085 -0.0362 1.0000 0.2541
-2.750 -0.1858 0.02018 0.00951 -0.0355 1.0000 0.3257
-2.500 -0.1645 0.01790 0.00857 -0.0337 1.0000 0.5168
-2.250 -0.1218 0.01600 0.00775 -0.0327 1.0000 1.0000
-2.000 -0.1006 0.01601 0.00727 -0.0320 1.0000 1.0000
-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 0.0497 0.01714 0.00669 -0.0279 1.0000 1.0000
0.000 0.0709 0.01747 0.00690 -0.0276 1.0000 1.0000
0.250 0.0918 0.01784 0.00717 -0.0273 1.0000 1.0000
0.500 0.1125 0.01826 0.00751 -0.0271 1.0000 1.0000
0.750 0.1327 0.01875 0.00795 -0.0269 1.0000 1.0000
1.000 0.1525 0.01931 0.00846 -0.0268 1.0000 1.0000
1.250 0.1719 0.01995 0.00907 -0.0269 1.0000 1.0000
1.500 0.1907 0.02066 0.00978 -0.0270 1.0000 1.0000
1.750 0.2090 0.02146 0.01058 -0.0272 1.0000 1.0000
2.000 0.2269 0.02235 0.01148 -0.0275 1.0000 1.0000
2.250 0.2794 0.02355 0.01277 -0.0342 0.9858 1.0000
2.500 0.3384 0.02464 0.01398 -0.0418 0.9647 1.0000
2.750 0.3896 0.02553 0.01504 -0.0475 0.9419 1.0000
3.000 0.4445 0.02628 0.01599 -0.0533 0.9200 1.0000
3.250 0.4931 0.02685 0.01679 -0.0576 0.8964 1.0000
3.500 0.5394 0.02726 0.01745 -0.0609 0.8722 1.0000
3.750 0.5930 0.02730 0.01783 -0.0647 0.8485 1.0000
4.000 0.6410 0.02703 0.01789 -0.0665 0.8235 1.0000
4.250 0.6805 0.02667 0.01786 -0.0664 0.7957 1.0000
4.500 0.7211 0.02559 0.01708 -0.0647 0.7638 1.0000
4.750 0.7519 0.02392 0.01557 -0.0597 0.7179 1.0000
5.000 0.7757 0.02239 0.01406 -0.0536 0.6627 1.0000
5.250 0.7942 0.02177 0.01339 -0.0486 0.6037 1.0000
5.500 0.8098 0.02164 0.01319 -0.0440 0.5323 1.0000
5.750 0.8138 0.02235 0.01317 -0.0376 0.3749 1.0000
6.000 0.8187 0.02581 0.01499 -0.0334 0.2201 1.0000
6.250 0.8401 0.02806 0.01686 -0.0320 0.1788 1.0000
6.500 0.8678 0.03023 0.01896 -0.0312 0.1592 1.0000
6.750 0.8978 0.03268 0.02152 -0.0306 0.1477 1.0000
7.000 0.9250 0.03533 0.02433 -0.0300 0.1382 1.0000
7.250 0.9498 0.03812 0.02711 -0.0294 0.1278 1.0000
7.500 0.9712 0.04130 0.03099 -0.0279 0.1244 1.0000
7.750 0.9897 0.04448 0.03461 -0.0265 0.1187 1.0000
8.000 1.0078 0.04832 0.03866 -0.0255 0.1136 1.0000
8.250 1.0203 0.05265 0.04355 -0.0238 0.1134 1.0000
8.500 1.0281 0.05723 0.04867 -0.0221 0.1135 1.0000
8.750 1.0307 0.06193 0.05388 -0.0205 0.1134 1.0000
9.000 1.0303 0.06688 0.05923 -0.0191 0.1136 1.0000
9.250 1.0245 0.07189 0.06468 -0.0179 0.1155 1.0000
9.500 0.9834 0.07910 0.07244 -0.0181 0.1245 1.0000
9.750 0.9758 0.08468 0.07811 -0.0182 0.1267 1.0000
10.000 0.7879 0.08467 0.07838 -0.0136 0.1366 1.0000
10.250 0.7659 0.09338 0.08709 -0.0175 0.1439 1.0000
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Polar data table (+)
Polar graphs
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