NASA SC(2)-0614 AIRFOIL (sc20614-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0614 AIRFOIL (sc20614-il) Reynolds number: 50,000 Max Cl/Cd: 26.4 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20614-il-50000.txt Download as CSV file: xf-sc20614-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0614 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6932 0.07990 0.07174 -0.0482 1.0000 0.1776
-10.000 -0.7072 0.07511 0.06693 -0.0479 1.0000 0.1761
-9.750 -0.7278 0.07019 0.06198 -0.0477 1.0000 0.1746
-9.500 -0.7501 0.06531 0.05696 -0.0473 1.0000 0.1733
-9.250 -0.7666 0.06058 0.05199 -0.0471 1.0000 0.1726
-9.000 -0.7742 0.05612 0.04720 -0.0472 1.0000 0.1730
-8.750 -0.7723 0.05200 0.04266 -0.0475 1.0000 0.1742
-8.500 -0.7632 0.04819 0.03833 -0.0483 1.0000 0.1761
-8.250 -0.7478 0.04516 0.03512 -0.0482 1.0000 0.1801
-8.000 -0.7295 0.04306 0.03299 -0.0475 1.0000 0.1855
-7.750 -0.7094 0.04049 0.03002 -0.0480 1.0000 0.1911
-7.500 -0.6884 0.03822 0.02755 -0.0480 1.0000 0.1977
-7.250 -0.6667 0.03651 0.02577 -0.0475 1.0000 0.2055
-7.000 -0.6438 0.03470 0.02376 -0.0473 1.0000 0.2144
-6.750 -0.6212 0.03328 0.02228 -0.0467 1.0000 0.2250
-6.500 -0.5998 0.03196 0.02105 -0.0454 1.0000 0.2364
-6.250 -0.5782 0.03077 0.01991 -0.0442 1.0000 0.2506
-6.000 -0.5574 0.02971 0.01898 -0.0425 1.0000 0.2679
-5.750 -0.5365 0.02865 0.01809 -0.0410 1.0000 0.2923
-5.500 -0.5159 0.02744 0.01727 -0.0396 1.0000 0.3285
-5.250 -0.4970 0.02604 0.01689 -0.0376 1.0000 0.4047
-5.000 -0.4989 0.02776 0.01975 -0.0269 1.0000 0.4988
-4.750 -0.4928 0.03108 0.02311 -0.0175 1.0000 0.5825
-4.250 -0.4788 0.03601 0.02784 -0.0007 1.0000 0.6544
-4.000 -0.4695 0.03750 0.02922 0.0062 1.0000 0.6834
-3.750 -0.4594 0.03849 0.03011 0.0122 1.0000 0.7123
-3.500 -0.4489 0.03910 0.03061 0.0176 1.0000 0.7418
-3.250 -0.4369 0.03944 0.03088 0.0238 1.0000 0.7678
-3.000 -0.4235 0.03936 0.03070 0.0286 1.0000 0.7975
-2.750 -0.4087 0.03895 0.03020 0.0325 1.0000 0.8278
-2.500 -0.3858 0.03829 0.02942 0.0350 1.0000 0.8597
-2.250 -0.3346 0.03746 0.02843 0.0325 1.0000 0.8955
-2.000 -0.2578 0.03661 0.02736 0.0239 1.0000 0.9289
-1.750 -0.1843 0.03570 0.02628 0.0145 1.0000 0.9504
-1.500 -0.1421 0.03500 0.02550 0.0102 1.0000 0.9635
-1.250 -0.0992 0.03442 0.02486 0.0055 1.0000 0.9753
-1.000 -0.0627 0.03399 0.02439 0.0020 1.0000 0.9844
-0.750 -0.0336 0.03369 0.02408 -0.0003 1.0000 0.9909
-0.500 -0.0047 0.03347 0.02387 -0.0026 1.0000 0.9967
-0.250 0.0125 0.03335 0.02377 -0.0028 1.0000 1.0000
0.000 0.0159 0.03324 0.02368 -0.0004 1.0000 1.0000
0.250 0.0191 0.03314 0.02363 0.0020 1.0000 1.0000
0.500 0.0221 0.03306 0.02359 0.0044 1.0000 1.0000
0.750 0.0248 0.03300 0.02358 0.0068 1.0000 1.0000
1.000 0.0272 0.03296 0.02359 0.0092 1.0000 1.0000
1.250 0.0293 0.03293 0.02362 0.0116 1.0000 1.0000
1.500 0.0309 0.03293 0.02369 0.0140 1.0000 1.0000
1.750 0.0322 0.03295 0.02378 0.0163 1.0000 1.0000
2.000 0.0332 0.03300 0.02390 0.0185 1.0000 1.0000
2.250 0.0341 0.03310 0.02408 0.0206 1.0000 1.0000
2.500 0.0350 0.03325 0.02433 0.0225 1.0000 1.0000
2.750 0.0884 0.03471 0.02592 0.0150 0.9827 1.0000
3.000 0.1927 0.03639 0.02782 0.0000 0.9397 1.0000
3.250 0.2822 0.03660 0.02828 -0.0104 0.8958 1.0000
3.500 0.3892 0.03527 0.02730 -0.0211 0.8492 1.0000
3.750 0.5530 0.02955 0.02221 -0.0347 0.7834 1.0000
4.000 0.6518 0.02469 0.01573 -0.0337 0.4485 1.0000
4.250 0.6612 0.02658 0.01658 -0.0303 0.3536 1.0000
4.500 0.6847 0.02797 0.01755 -0.0297 0.3028 1.0000
4.750 0.7142 0.02922 0.01857 -0.0300 0.2709 1.0000
5.000 0.7440 0.03051 0.01967 -0.0304 0.2495 1.0000
5.250 0.7681 0.03178 0.02092 -0.0300 0.2341 1.0000
5.500 0.7906 0.03321 0.02240 -0.0293 0.2230 1.0000
5.750 0.8114 0.03462 0.02374 -0.0284 0.2131 1.0000
6.000 0.8247 0.03605 0.02546 -0.0263 0.2058 1.0000
6.250 0.8409 0.03755 0.02706 -0.0247 0.1991 1.0000
6.500 0.8569 0.03942 0.02903 -0.0232 0.1931 1.0000
6.750 0.8683 0.04126 0.03128 -0.0211 0.1879 1.0000
7.000 0.8868 0.04337 0.03361 -0.0203 0.1828 1.0000
7.250 0.9099 0.04606 0.03628 -0.0206 0.1775 1.0000
7.500 0.9192 0.04884 0.03966 -0.0190 0.1747 1.0000
7.750 0.9288 0.05214 0.04347 -0.0178 0.1726 1.0000
8.000 0.9360 0.05568 0.04744 -0.0168 0.1705 1.0000
8.250 0.9402 0.05952 0.05168 -0.0159 0.1689 1.0000
8.500 0.9353 0.06414 0.05674 -0.0148 0.1694 1.0000
8.750 0.9214 0.06954 0.06255 -0.0138 0.1719 1.0000
9.000 0.9084 0.07513 0.06841 -0.0136 0.1746 1.0000
9.250 0.9033 0.08062 0.07405 -0.0140 0.1768 1.0000
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Polar data table (+)
Polar graphs
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