SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il) Xfoil prediction polar at RE=200,000 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: 200,000 Max Cl/Cd: 43.75 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nasasc2-0714-il-200000-n5.txt Download as CSV file: xf-nasasc2-0714-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.8390 0.09522 0.09007 -0.0598 1.0000 0.0347
-16.500 -0.8944 0.08117 0.07567 -0.0685 1.0000 0.0347
-16.250 -0.9245 0.07305 0.06728 -0.0728 1.0000 0.0348
-16.000 -0.9470 0.06692 0.06091 -0.0756 1.0000 0.0351
-15.750 -0.9648 0.06201 0.05576 -0.0771 1.0000 0.0353
-15.500 -0.9796 0.05796 0.05148 -0.0778 1.0000 0.0356
-15.250 -0.9820 0.05550 0.04897 -0.0776 1.0000 0.0359
-15.000 -0.9835 0.05329 0.04672 -0.0771 1.0000 0.0362
-14.750 -0.9849 0.05124 0.04461 -0.0764 1.0000 0.0365
-14.500 -0.9862 0.04933 0.04263 -0.0755 1.0000 0.0369
-14.250 -0.9880 0.04749 0.04072 -0.0743 1.0000 0.0372
-14.000 -0.9901 0.04575 0.03890 -0.0728 1.0000 0.0376
-13.750 -0.9920 0.04411 0.03717 -0.0710 1.0000 0.0380
-13.500 -0.9941 0.04258 0.03555 -0.0690 1.0000 0.0385
-13.250 -0.9963 0.04114 0.03400 -0.0667 1.0000 0.0389
-13.000 -0.9985 0.03980 0.03256 -0.0641 1.0000 0.0394
-12.750 -1.0012 0.03857 0.03120 -0.0612 1.0000 0.0400
-12.500 -1.0051 0.03745 0.02996 -0.0580 1.0000 0.0405
-12.250 -1.0106 0.03644 0.02883 -0.0543 1.0000 0.0410
-12.000 -1.0117 0.03542 0.02774 -0.0512 1.0000 0.0415
-11.750 -1.0064 0.03442 0.02675 -0.0491 1.0000 0.0421
-11.500 -0.9962 0.03345 0.02577 -0.0479 0.9996 0.0428
-11.250 -0.9731 0.03239 0.02466 -0.0490 0.9978 0.0437
-11.000 -0.9493 0.03136 0.02356 -0.0501 0.9959 0.0448
-10.750 -0.9244 0.03037 0.02246 -0.0511 0.9942 0.0459
-10.500 -0.8984 0.02945 0.02141 -0.0522 0.9927 0.0472
-10.250 -0.8750 0.02850 0.02043 -0.0528 0.9905 0.0484
-10.000 -0.8495 0.02765 0.01958 -0.0538 0.9882 0.0496
-9.750 -0.8227 0.02688 0.01879 -0.0550 0.9861 0.0511
-9.500 -0.7953 0.02615 0.01800 -0.0561 0.9844 0.0526
-9.250 -0.7669 0.02545 0.01723 -0.0573 0.9829 0.0542
-9.000 -0.7379 0.02472 0.01648 -0.0587 0.9817 0.0559
-8.750 -0.7109 0.02403 0.01581 -0.0598 0.9796 0.0577
-8.500 -0.6843 0.02342 0.01518 -0.0607 0.9769 0.0598
-8.250 -0.6556 0.02283 0.01456 -0.0618 0.9747 0.0619
-8.000 -0.6258 0.02222 0.01392 -0.0632 0.9730 0.0641
-7.750 -0.5943 0.02161 0.01335 -0.0651 0.9714 0.0670
-7.500 -0.5613 0.02110 0.01284 -0.0671 0.9701 0.0705
-7.250 -0.5272 0.02057 0.01229 -0.0693 0.9689 0.0741
-7.000 -0.4922 0.02004 0.01181 -0.0718 0.9679 0.0787
-6.750 -0.4661 0.01965 0.01139 -0.0722 0.9647 0.0835
-6.500 -0.4345 0.01914 0.01095 -0.0739 0.9624 0.0900
-6.250 -0.4013 0.01873 0.01055 -0.0758 0.9604 0.0977
-6.000 -0.3669 0.01832 0.01018 -0.0780 0.9588 0.1076
-5.750 -0.3312 0.01787 0.00982 -0.0804 0.9575 0.1205
-5.500 -0.2943 0.01744 0.00948 -0.0831 0.9563 0.1376
-5.250 -0.2558 0.01695 0.00913 -0.0863 0.9553 0.1637
-5.000 -0.2150 0.01633 0.00877 -0.0902 0.9547 0.2107
-4.750 -0.1696 0.01546 0.00834 -0.0955 0.9544 0.2969
-4.500 -0.1209 0.01448 0.00813 -0.1016 0.9546 0.4486
-4.250 -0.0925 0.01472 0.00882 -0.1012 0.9526 0.5340
-4.000 -0.0686 0.01496 0.00911 -0.1003 0.9482 0.5686
-3.750 -0.0393 0.01520 0.00937 -0.1003 0.9451 0.5882
-3.500 -0.0060 0.01534 0.00948 -0.1014 0.9428 0.6022
-3.250 0.0285 0.01546 0.00956 -0.1027 0.9411 0.6129
-3.000 0.0609 0.01569 0.00979 -0.1032 0.9394 0.6207
-2.750 0.0941 0.01591 0.00999 -0.1041 0.9367 0.6338
-2.500 0.1082 0.01649 0.01066 -0.1003 0.9295 0.6405
-2.250 0.1415 0.01672 0.01088 -0.1012 0.9270 0.6514
-2.000 0.1702 0.01698 0.01119 -0.1005 0.9246 0.6543
-1.750 0.2057 0.01699 0.01122 -0.1017 0.9229 0.6569
-1.500 0.2288 0.01702 0.01126 -0.1005 0.9145 0.6604
-1.250 0.2717 0.01666 0.01088 -0.1036 0.9107 0.6651
-1.000 0.3176 0.01622 0.01043 -0.1072 0.9080 0.6684
-0.750 0.3452 0.01604 0.01029 -0.1065 0.8988 0.6698
-0.500 0.3894 0.01535 0.00961 -0.1086 0.8888 0.6711
-0.250 0.4190 0.01495 0.00922 -0.1081 0.8705 0.6727
0.000 0.4512 0.01465 0.00894 -0.1084 0.8539 0.6743
0.250 0.4836 0.01439 0.00868 -0.1089 0.8339 0.6760
0.500 0.5232 0.01402 0.00823 -0.1107 0.8001 0.6779
0.750 0.5656 0.01376 0.00769 -0.1130 0.7279 0.6799
1.000 0.5951 0.01416 0.00743 -0.1129 0.6082 0.6825
1.250 0.6155 0.01497 0.00755 -0.1117 0.4855 0.6856
1.500 0.6318 0.01579 0.00791 -0.1094 0.3916 0.6866
1.750 0.6502 0.01655 0.00827 -0.1077 0.3068 0.6878
2.000 0.6709 0.01721 0.00862 -0.1064 0.2428 0.6891
2.250 0.6937 0.01776 0.00893 -0.1055 0.1970 0.6905
2.500 0.7172 0.01826 0.00925 -0.1048 0.1638 0.6923
2.750 0.7418 0.01870 0.00957 -0.1042 0.1405 0.6945
3.000 0.7677 0.01911 0.00988 -0.1040 0.1230 0.6969
3.250 0.7950 0.01947 0.01016 -0.1041 0.1100 0.6990
3.500 0.8233 0.01981 0.01044 -0.1045 0.1000 0.7012
3.750 0.8509 0.02020 0.01076 -0.1048 0.0924 0.7031
4.000 0.8752 0.02056 0.01114 -0.1040 0.0864 0.7040
4.250 0.8987 0.02101 0.01155 -0.1032 0.0816 0.7050
4.500 0.9230 0.02139 0.01198 -0.1025 0.0775 0.7061
4.750 0.9468 0.02183 0.01242 -0.1017 0.0739 0.7073
5.000 0.9700 0.02234 0.01291 -0.1009 0.0707 0.7087
5.250 0.9940 0.02278 0.01340 -0.1002 0.0678 0.7102
5.500 1.0177 0.02326 0.01391 -0.0995 0.0652 0.7121
5.750 1.0406 0.02387 0.01448 -0.0988 0.0629 0.7141
6.000 1.0646 0.02444 0.01508 -0.0982 0.0608 0.7161
6.250 1.0894 0.02497 0.01567 -0.0979 0.0585 0.7182
6.500 1.1142 0.02555 0.01624 -0.0976 0.0564 0.7203
6.750 1.1344 0.02621 0.01692 -0.0963 0.0548 0.7213
7.000 1.1546 0.02700 0.01774 -0.0950 0.0534 0.7224
7.250 1.1759 0.02764 0.01850 -0.0939 0.0519 0.7236
7.500 1.1967 0.02832 0.01926 -0.0927 0.0503 0.7249
7.750 1.2169 0.02900 0.01999 -0.0914 0.0489 0.7264
8.000 1.2363 0.02972 0.02074 -0.0902 0.0477 0.7280
8.250 1.2548 0.03065 0.02166 -0.0888 0.0466 0.7297
8.500 1.2743 0.03144 0.02260 -0.0875 0.0456 0.7316
8.750 1.2928 0.03231 0.02359 -0.0861 0.0445 0.7338
9.000 1.3106 0.03320 0.02458 -0.0846 0.0435 0.7362
9.250 1.3273 0.03408 0.02554 -0.0830 0.0425 0.7381
9.500 1.3422 0.03495 0.02649 -0.0811 0.0417 0.7394
9.750 1.3567 0.03586 0.02745 -0.0792 0.0410 0.7408
10.000 1.3709 0.03696 0.02859 -0.0774 0.0403 0.7423
10.250 1.3849 0.03814 0.02998 -0.0756 0.0395 0.7439
10.500 1.3978 0.03942 0.03145 -0.0737 0.0387 0.7456
10.750 1.4097 0.04077 0.03297 -0.0717 0.0380 0.7474
11.000 1.4205 0.04218 0.03452 -0.0698 0.0374 0.7494
11.250 1.4303 0.04362 0.03611 -0.0678 0.0368 0.7514
11.500 1.4393 0.04511 0.03771 -0.0659 0.0364 0.7535
11.750 1.4467 0.04665 0.03936 -0.0639 0.0359 0.7553
12.000 1.4524 0.04822 0.04105 -0.0618 0.0356 0.7568
12.250 1.4575 0.04990 0.04284 -0.0597 0.0352 0.7584
12.500 1.4616 0.05175 0.04478 -0.0578 0.0349 0.7601
12.750 1.4619 0.05409 0.04729 -0.0558 0.0345 0.7619
13.000 1.4572 0.05697 0.05046 -0.0538 0.0342 0.7636
13.250 1.4500 0.06020 0.05396 -0.0522 0.0338 0.7654
13.500 1.4407 0.06382 0.05785 -0.0510 0.0334 0.7670
13.750 1.4287 0.06791 0.06220 -0.0503 0.0331 0.7687
14.000 1.4145 0.07255 0.06709 -0.0503 0.0329 0.7702
14.250 1.3971 0.07795 0.07275 -0.0513 0.0326 0.7717
14.500 1.3754 0.08436 0.07942 -0.0533 0.0325 0.7725
14.750 1.3478 0.09252 0.08788 -0.0572 0.0323 0.7732
15.000 1.3071 0.10440 0.10012 -0.0646 0.0323 0.7736
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Polar data table (+)
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