SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il) Reynolds number: 50,000 Max Cl/Cd: 22.48 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nasasc2-0714-il-50000-n5.txt Download as CSV file: xf-nasasc2-0714-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SC(2)-0714 Supercritical airfoil (coordinates fr
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.6068 0.10195 0.09306 -0.0526 1.0000 0.0832
-12.500 -0.6458 0.09171 0.08277 -0.0579 1.0000 0.0830
-12.250 -0.6850 0.08359 0.07460 -0.0611 1.0000 0.0827
-12.000 -0.7222 0.07734 0.06824 -0.0624 1.0000 0.0825
-11.750 -0.7565 0.07255 0.06334 -0.0619 1.0000 0.0824
-11.500 -0.7888 0.06888 0.05957 -0.0597 1.0000 0.0824
-11.250 -0.8176 0.06553 0.05606 -0.0574 1.0000 0.0825
-11.000 -0.8387 0.06185 0.05212 -0.0562 1.0000 0.0830
-10.750 -0.8510 0.05840 0.04837 -0.0552 1.0000 0.0838
-10.500 -0.8437 0.05624 0.04618 -0.0540 1.0000 0.0851
-10.250 -0.8375 0.05398 0.04380 -0.0530 1.0000 0.0863
-10.000 -0.8300 0.05166 0.04130 -0.0520 1.0000 0.0877
-9.750 -0.8203 0.04950 0.03894 -0.0512 1.0000 0.0897
-9.500 -0.8094 0.04727 0.03643 -0.0507 1.0000 0.0923
-9.250 -0.7964 0.04497 0.03371 -0.0503 1.0000 0.0951
-9.000 -0.7797 0.04323 0.03190 -0.0494 1.0000 0.0973
-8.750 -0.7619 0.04181 0.03042 -0.0483 1.0000 0.0997
-8.500 -0.7437 0.04046 0.02897 -0.0474 1.0000 0.1030
-8.250 -0.7247 0.03910 0.02737 -0.0466 1.0000 0.1072
-8.000 -0.7054 0.03792 0.02613 -0.0453 1.0000 0.1109
-7.750 -0.6863 0.03699 0.02524 -0.0437 1.0000 0.1146
-7.500 -0.6668 0.03613 0.02431 -0.0421 1.0000 0.1194
-7.250 -0.6473 0.03537 0.02346 -0.0404 1.0000 0.1251
-7.000 -0.6288 0.03469 0.02288 -0.0386 1.0000 0.1309
-6.750 -0.6096 0.03405 0.02214 -0.0368 1.0000 0.1378
-6.500 -0.5914 0.03333 0.02156 -0.0353 1.0000 0.1455
-6.250 -0.5722 0.03266 0.02087 -0.0340 1.0000 0.1558
-6.000 -0.5531 0.03186 0.02021 -0.0331 1.0000 0.1674
-5.750 -0.5327 0.03099 0.01948 -0.0328 1.0000 0.1832
-5.500 -0.5105 0.03003 0.01872 -0.0330 1.0000 0.2061
-5.250 -0.4855 0.02875 0.01785 -0.0345 1.0000 0.2446
-5.000 -0.4583 0.02728 0.01725 -0.0365 1.0000 0.3344
-4.750 -0.4546 0.02813 0.01906 -0.0291 1.0000 0.4332
-4.500 -0.4491 0.02982 0.02102 -0.0213 1.0000 0.5002
-4.000 -0.3944 0.03093 0.02174 -0.0222 1.0000 0.6004
-3.750 -0.3760 0.03173 0.02245 -0.0196 1.0000 0.6216
-3.500 -0.3574 0.03240 0.02302 -0.0173 1.0000 0.6404
-3.250 -0.3402 0.03306 0.02360 -0.0146 1.0000 0.6582
-3.000 -0.3259 0.03380 0.02430 -0.0110 1.0000 0.6768
-2.750 -0.3131 0.03451 0.02499 -0.0070 1.0000 0.6963
-2.500 -0.3005 0.03506 0.02551 -0.0031 1.0000 0.7149
-2.250 -0.2870 0.03536 0.02578 0.0003 1.0000 0.7307
-2.000 -0.2693 0.03541 0.02578 0.0021 1.0000 0.7429
-1.750 -0.2466 0.03538 0.02568 0.0021 1.0000 0.7531
-1.500 -0.2269 0.03523 0.02549 0.0031 0.9998 0.7595
-1.250 -0.1921 0.03528 0.02547 0.0009 0.9945 0.7658
-1.000 -0.1530 0.03537 0.02548 -0.0028 0.9892 0.7720
-0.750 -0.1219 0.03537 0.02546 -0.0039 0.9833 0.7768
-0.500 -0.0875 0.03543 0.02550 -0.0061 0.9767 0.7825
-0.250 -0.0460 0.03562 0.02565 -0.0101 0.9699 0.7880
0.000 -0.0145 0.03556 0.02561 -0.0114 0.9617 0.7913
0.250 0.0235 0.03564 0.02571 -0.0142 0.9546 0.7948
0.500 0.0580 0.03564 0.02574 -0.0164 0.9448 0.7984
0.750 0.1008 0.03576 0.02589 -0.0203 0.9360 0.8016
1.000 0.1388 0.03577 0.02597 -0.0232 0.9256 0.8041
1.250 0.1712 0.03567 0.02595 -0.0245 0.9145 0.8066
1.500 0.2104 0.03554 0.02591 -0.0270 0.9030 0.8094
1.750 0.2542 0.03526 0.02575 -0.0300 0.8897 0.8122
2.000 0.2953 0.03482 0.02542 -0.0323 0.8729 0.8151
2.250 0.3317 0.03424 0.02497 -0.0336 0.8501 0.8183
2.500 0.3726 0.03314 0.02402 -0.0345 0.8253 0.8211
2.750 0.4052 0.03207 0.02309 -0.0339 0.7963 0.8238
3.000 0.4383 0.03105 0.02223 -0.0335 0.7658 0.8260
3.250 0.4678 0.03024 0.02157 -0.0327 0.7291 0.8283
3.500 0.5027 0.02928 0.02072 -0.0324 0.6775 0.8307
3.750 0.5706 0.02765 0.01838 -0.0352 0.5199 0.8324
4.000 0.5956 0.02869 0.01840 -0.0345 0.3745 0.8343
4.250 0.6101 0.02983 0.01896 -0.0328 0.2921 0.8360
4.500 0.6282 0.03086 0.01962 -0.0319 0.2415 0.8376
4.750 0.6500 0.03183 0.02034 -0.0315 0.2082 0.8395
5.000 0.6744 0.03280 0.02112 -0.0315 0.1862 0.8417
5.250 0.7023 0.03372 0.02193 -0.0321 0.1685 0.8440
5.500 0.7338 0.03466 0.02283 -0.0332 0.1543 0.8463
5.750 0.7698 0.03564 0.02386 -0.0349 0.1426 0.8485
6.000 0.8028 0.03663 0.02481 -0.0361 0.1336 0.8503
6.250 0.8350 0.03761 0.02587 -0.0370 0.1258 0.8521
6.500 0.8671 0.03877 0.02701 -0.0381 0.1194 0.8539
6.750 0.8982 0.03999 0.02842 -0.0389 0.1133 0.8560
7.000 0.9285 0.04131 0.02971 -0.0398 0.1087 0.8583
7.250 0.9577 0.04291 0.03152 -0.0406 0.1041 0.8608
7.500 0.9850 0.04459 0.03346 -0.0411 0.0997 0.8633
7.750 1.0088 0.04612 0.03511 -0.0410 0.0966 0.8657
8.000 1.0333 0.04781 0.03677 -0.0411 0.0938 0.8681
8.250 1.0492 0.04998 0.03950 -0.0400 0.0908 0.8705
8.500 1.0655 0.05221 0.04208 -0.0391 0.0880 0.8726
8.750 1.0818 0.05457 0.04473 -0.0384 0.0861 0.8748
9.000 1.0974 0.05686 0.04722 -0.0378 0.0842 0.8772
9.250 1.1137 0.05894 0.04938 -0.0373 0.0825 0.8797
9.500 1.1124 0.06196 0.05285 -0.0347 0.0811 0.8822
9.750 1.1034 0.06537 0.05677 -0.0317 0.0799 0.8847
10.000 1.0895 0.06878 0.06058 -0.0285 0.0790 0.8871
10.250 1.0726 0.07273 0.06490 -0.0260 0.0783 0.8895
10.500 1.0511 0.07736 0.06989 -0.0244 0.0779 0.8915
10.750 1.0230 0.08293 0.07578 -0.0239 0.0779 0.8930
11.000 0.9871 0.08994 0.08310 -0.0253 0.0781 0.8942
11.250 0.9428 0.09973 0.09315 -0.0301 0.0787 0.8949
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