SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| 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: 36.57 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nasasc2-0714-il-200000.txt Download as CSV file: xf-nasasc2-0714-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6348 0.09803 0.09364 -0.0545 1.0000 0.0646
-13.250 -0.9228 0.06067 0.05512 -0.0687 1.0000 0.0550
-13.000 -0.9511 0.05816 0.05248 -0.0650 1.0000 0.0550
-12.750 -0.9790 0.05600 0.05020 -0.0606 1.0000 0.0550
-12.500 -0.9982 0.05250 0.04652 -0.0585 1.0000 0.0552
-12.250 -1.0046 0.04921 0.04309 -0.0570 1.0000 0.0557
-12.000 -1.0011 0.04704 0.04086 -0.0558 1.0000 0.0563
-11.750 -0.9936 0.04536 0.03913 -0.0547 1.0000 0.0570
-11.500 -0.9850 0.04368 0.03736 -0.0536 1.0000 0.0577
-11.250 -0.9767 0.04166 0.03518 -0.0527 1.0000 0.0585
-11.000 -0.9663 0.03957 0.03288 -0.0521 1.0000 0.0593
-10.750 -0.9534 0.03754 0.03061 -0.0516 1.0000 0.0604
-10.500 -0.9379 0.03570 0.02849 -0.0514 1.0000 0.0618
-10.250 -0.9196 0.03422 0.02667 -0.0516 1.0000 0.0631
-10.000 -0.9015 0.03210 0.02445 -0.0510 1.0000 0.0645
-9.750 -0.8812 0.03100 0.02336 -0.0505 1.0000 0.0659
-9.500 -0.8597 0.03002 0.02232 -0.0503 1.0000 0.0674
-9.250 -0.8376 0.02909 0.02129 -0.0501 1.0000 0.0692
-9.000 -0.8144 0.02822 0.02027 -0.0500 1.0000 0.0713
-8.750 -0.7901 0.02744 0.01930 -0.0501 1.0000 0.0730
-8.500 -0.7695 0.02615 0.01809 -0.0491 1.0000 0.0751
-8.250 -0.7464 0.02548 0.01744 -0.0488 1.0000 0.0771
-8.000 -0.7224 0.02488 0.01681 -0.0487 1.0000 0.0797
-7.750 -0.6975 0.02435 0.01619 -0.0487 1.0000 0.0825
-7.500 -0.6743 0.02356 0.01538 -0.0482 1.0000 0.0851
-7.250 -0.6503 0.02294 0.01486 -0.0480 1.0000 0.0881
-7.000 -0.6250 0.02248 0.01440 -0.0481 1.0000 0.0916
-6.750 -0.5985 0.02213 0.01397 -0.0484 1.0000 0.0954
-6.500 -0.5728 0.02139 0.01338 -0.0486 1.0000 0.1004
-6.250 -0.5451 0.02099 0.01301 -0.0493 1.0000 0.1060
-6.000 -0.5157 0.02041 0.01251 -0.0504 1.0000 0.1132
-5.750 -0.4856 0.02004 0.01216 -0.0516 1.0000 0.1229
-5.500 -0.4517 0.01945 0.01170 -0.0540 1.0000 0.1376
-5.250 -0.4134 0.01877 0.01125 -0.0575 1.0000 0.1617
-5.000 -0.3667 0.01787 0.01076 -0.0631 1.0000 0.2236
-4.750 -0.3001 0.01642 0.01111 -0.0734 1.0000 0.5237
-4.500 -0.2781 0.01698 0.01173 -0.0721 1.0000 0.5799
-4.250 -0.2584 0.01760 0.01235 -0.0703 1.0000 0.6025
-4.000 -0.2385 0.01824 0.01296 -0.0686 1.0000 0.6187
-3.750 -0.2075 0.01898 0.01365 -0.0689 0.9971 0.6336
-3.500 -0.1829 0.02017 0.01490 -0.0668 0.9932 0.6407
-3.250 -0.1552 0.02090 0.01560 -0.0662 0.9887 0.6523
-3.000 -0.1342 0.02196 0.01671 -0.0634 0.9840 0.6574
-2.750 -0.0942 0.02256 0.01725 -0.0658 0.9814 0.6685
-2.500 -0.0764 0.02316 0.01789 -0.0627 0.9743 0.6715
-2.250 -0.0501 0.02394 0.01868 -0.0612 0.9698 0.6763
-2.000 -0.0198 0.02447 0.01920 -0.0613 0.9645 0.6873
-1.750 -0.0049 0.02532 0.02012 -0.0565 0.9569 0.6931
-1.500 0.0309 0.02587 0.02067 -0.0571 0.9521 0.7051
-1.250 0.0461 0.02615 0.02100 -0.0533 0.9434 0.7100
-1.000 0.0993 0.02616 0.02096 -0.0595 0.9403 0.7203
-0.750 0.1201 0.02609 0.02094 -0.0571 0.9324 0.7227
-0.500 0.1544 0.02587 0.02074 -0.0577 0.9261 0.7253
-0.250 0.2009 0.02554 0.02043 -0.0608 0.9226 0.7283
0.000 0.2359 0.02504 0.01994 -0.0621 0.9108 0.7324
0.250 0.3039 0.02384 0.01873 -0.0697 0.8996 0.7378
0.500 0.3444 0.02291 0.01786 -0.0703 0.8925 0.7400
0.750 0.3737 0.02235 0.01736 -0.0694 0.8828 0.7430
1.000 0.4262 0.02116 0.01621 -0.0727 0.8757 0.7457
1.250 0.4663 0.02026 0.01537 -0.0744 0.8628 0.7480
1.500 0.5093 0.01944 0.01459 -0.0769 0.8494 0.7506
1.750 0.5561 0.01876 0.01394 -0.0807 0.8291 0.7541
2.000 0.5932 0.01804 0.01322 -0.0816 0.7980 0.7559
2.250 0.6362 0.01741 0.01235 -0.0832 0.7200 0.7572
2.500 0.6575 0.01798 0.01203 -0.0810 0.5570 0.7587
2.750 0.6637 0.01909 0.01232 -0.0770 0.4104 0.7603
3.000 0.6744 0.02021 0.01273 -0.0744 0.2804 0.7619
3.250 0.6924 0.02115 0.01315 -0.0732 0.1990 0.7636
3.500 0.7154 0.02186 0.01358 -0.0729 0.1598 0.7653
3.750 0.7408 0.02253 0.01406 -0.0730 0.1390 0.7674
4.000 0.7713 0.02313 0.01458 -0.0743 0.1255 0.7702
4.250 0.8001 0.02373 0.01511 -0.0751 0.1163 0.7721
4.500 0.8213 0.02413 0.01546 -0.0738 0.1098 0.7734
4.750 0.8431 0.02472 0.01604 -0.0727 0.1045 0.7750
5.000 0.8669 0.02513 0.01647 -0.0720 0.0994 0.7769
5.250 0.8923 0.02595 0.01718 -0.0719 0.0945 0.7788
5.500 0.9202 0.02651 0.01781 -0.0721 0.0908 0.7808
5.750 0.9490 0.02708 0.01840 -0.0726 0.0868 0.7826
6.000 0.9795 0.02795 0.01917 -0.0737 0.0831 0.7840
6.250 1.0112 0.02883 0.02012 -0.0748 0.0799 0.7854
6.500 1.0432 0.02963 0.02099 -0.0761 0.0768 0.7869
6.750 1.0729 0.03040 0.02175 -0.0769 0.0743 0.7882
7.000 1.1019 0.03195 0.02322 -0.0774 0.0716 0.7894
7.250 1.1246 0.03255 0.02405 -0.0765 0.0697 0.7906
7.500 1.1492 0.03346 0.02510 -0.0760 0.0676 0.7920
7.750 1.1744 0.03449 0.02623 -0.0758 0.0658 0.7935
8.000 1.1998 0.03557 0.02735 -0.0757 0.0643 0.7955
8.250 1.2284 0.03755 0.02932 -0.0765 0.0626 0.7976
8.500 1.2496 0.03922 0.03130 -0.0758 0.0613 0.7996
8.750 1.2698 0.04079 0.03318 -0.0749 0.0599 0.8014
9.000 1.2904 0.04267 0.03532 -0.0744 0.0586 0.8031
9.250 1.3061 0.04450 0.03739 -0.0729 0.0576 0.8044
9.500 1.3199 0.04626 0.03935 -0.0710 0.0568 0.8058
9.750 1.3347 0.04800 0.04123 -0.0695 0.0560 0.8073
10.000 1.3483 0.04990 0.04325 -0.0679 0.0553 0.8089
10.250 1.3604 0.05236 0.04584 -0.0665 0.0546 0.8106
10.500 1.3625 0.05672 0.05046 -0.0644 0.0540 0.8122
10.750 1.3518 0.05936 0.05349 -0.0599 0.0537 0.8138
11.000 1.3340 0.06212 0.05659 -0.0548 0.0535 0.8154
11.250 1.3133 0.06553 0.06033 -0.0502 0.0533 0.8171
11.500 1.2909 0.06962 0.06471 -0.0467 0.0533 0.8187
11.750 1.2650 0.07409 0.06947 -0.0437 0.0533 0.8199
12.000 1.2378 0.07906 0.07469 -0.0418 0.0535 0.8209
12.250 1.2116 0.08465 0.08049 -0.0412 0.0536 0.8218
12.500 1.1886 0.09084 0.08685 -0.0417 0.0539 0.8228
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Polar data table (+)
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