SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il) Reynolds number: 100,000 Max Cl/Cd: 31.06 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nasasc2-0714-il-100000-n5.txt Download as CSV file: xf-nasasc2-0714-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.7678 0.07565 0.06881 -0.0683 1.0000 0.0521
-13.500 -0.8104 0.06834 0.06126 -0.0706 1.0000 0.0520
-13.250 -0.8413 0.06334 0.05607 -0.0707 1.0000 0.0521
-13.000 -0.8667 0.05947 0.05200 -0.0696 1.0000 0.0523
-12.750 -0.8888 0.05631 0.04866 -0.0676 1.0000 0.0525
-12.500 -0.9094 0.05370 0.04588 -0.0647 1.0000 0.0528
-12.250 -0.9296 0.05154 0.04355 -0.0610 1.0000 0.0532
-12.000 -0.9439 0.04925 0.04106 -0.0581 1.0000 0.0536
-11.750 -0.9513 0.04680 0.03831 -0.0563 1.0000 0.0543
-11.500 -0.9520 0.04455 0.03579 -0.0549 1.0000 0.0552
-11.250 -0.9415 0.04325 0.03451 -0.0538 1.0000 0.0561
-11.000 -0.9309 0.04198 0.03320 -0.0527 1.0000 0.0571
-10.750 -0.9195 0.04063 0.03174 -0.0517 1.0000 0.0583
-10.500 -0.9068 0.03917 0.03014 -0.0508 1.0000 0.0596
-10.250 -0.8927 0.03766 0.02843 -0.0499 1.0000 0.0610
-10.000 -0.8771 0.03622 0.02675 -0.0491 1.0000 0.0625
-9.750 -0.8602 0.03498 0.02540 -0.0482 1.0000 0.0640
-9.500 -0.8423 0.03406 0.02452 -0.0475 1.0000 0.0656
-9.250 -0.8236 0.03315 0.02357 -0.0469 1.0000 0.0674
-9.000 -0.8043 0.03221 0.02254 -0.0462 1.0000 0.0694
-8.750 -0.7843 0.03128 0.02148 -0.0454 1.0000 0.0714
-8.500 -0.7641 0.03041 0.02053 -0.0447 1.0000 0.0735
-8.250 -0.7436 0.02966 0.01984 -0.0443 1.0000 0.0759
-8.000 -0.7222 0.02896 0.01914 -0.0439 1.0000 0.0786
-7.750 -0.7004 0.02829 0.01840 -0.0434 1.0000 0.0816
-7.500 -0.6785 0.02761 0.01768 -0.0428 1.0000 0.0844
-7.250 -0.6557 0.02695 0.01710 -0.0428 1.0000 0.0879
-7.000 -0.6322 0.02640 0.01654 -0.0427 1.0000 0.0923
-6.750 -0.6083 0.02583 0.01597 -0.0426 1.0000 0.0969
-6.500 -0.5781 0.02523 0.01543 -0.0440 0.9985 0.1025
-6.250 -0.5460 0.02474 0.01494 -0.0456 0.9966 0.1104
-6.000 -0.5133 0.02421 0.01449 -0.0474 0.9948 0.1200
-5.750 -0.4793 0.02372 0.01410 -0.0495 0.9933 0.1319
-5.500 -0.4459 0.02324 0.01373 -0.0515 0.9913 0.1486
-5.250 -0.4120 0.02274 0.01338 -0.0537 0.9893 0.1732
-5.000 -0.3758 0.02207 0.01302 -0.0567 0.9878 0.2188
-4.750 -0.3313 0.02088 0.01255 -0.0624 0.9873 0.3317
-4.500 -0.3055 0.02101 0.01363 -0.0615 0.9848 0.4761
-4.000 -0.2542 0.02258 0.01540 -0.0587 0.9779 0.5746
-3.750 -0.2185 0.02289 0.01560 -0.0607 0.9748 0.6000
-3.250 -0.1566 0.02408 0.01668 -0.0610 0.9683 0.6254
-3.000 -0.1300 0.02448 0.01703 -0.0606 0.9634 0.6367
-2.750 -0.1033 0.02517 0.01771 -0.0597 0.9589 0.6517
-2.500 -0.0823 0.02616 0.01873 -0.0565 0.9548 0.6628
-2.250 -0.0624 0.02677 0.01936 -0.0540 0.9496 0.6730
-2.000 -0.0353 0.02704 0.01961 -0.0538 0.9449 0.6817
-1.750 -0.0006 0.02709 0.01962 -0.0554 0.9413 0.6875
-1.500 0.0330 0.02716 0.01969 -0.0564 0.9382 0.6904
-1.250 0.0567 0.02715 0.01969 -0.0558 0.9311 0.6940
-1.000 0.0937 0.02706 0.01958 -0.0581 0.9266 0.6987
-0.750 0.1384 0.02688 0.01938 -0.0621 0.9230 0.7038
-0.500 0.1604 0.02685 0.01940 -0.0606 0.9137 0.7064
-0.250 0.1965 0.02670 0.01928 -0.0619 0.9084 0.7091
0.000 0.2276 0.02653 0.01915 -0.0628 0.9003 0.7117
0.250 0.2673 0.02621 0.01887 -0.0651 0.8931 0.7147
0.500 0.3071 0.02581 0.01850 -0.0677 0.8831 0.7183
0.750 0.3571 0.02489 0.01763 -0.0713 0.8708 0.7208
1.000 0.3906 0.02404 0.01683 -0.0711 0.8517 0.7221
1.250 0.4217 0.02335 0.01621 -0.0707 0.8333 0.7236
1.500 0.4515 0.02287 0.01580 -0.0704 0.8154 0.7254
1.750 0.4824 0.02236 0.01537 -0.0702 0.7915 0.7275
2.000 0.5172 0.02172 0.01474 -0.0706 0.7512 0.7299
2.250 0.5955 0.02066 0.01301 -0.0778 0.6055 0.7317
2.500 0.6252 0.02146 0.01293 -0.0780 0.4522 0.7346
2.750 0.6491 0.02243 0.01323 -0.0780 0.3381 0.7377
3.000 0.6671 0.02318 0.01358 -0.0763 0.2651 0.7393
3.250 0.6875 0.02385 0.01396 -0.0751 0.2129 0.7410
3.500 0.7099 0.02445 0.01435 -0.0744 0.1773 0.7427
3.750 0.7328 0.02505 0.01479 -0.0737 0.1542 0.7447
4.000 0.7569 0.02563 0.01527 -0.0734 0.1382 0.7468
4.250 0.7823 0.02618 0.01579 -0.0733 0.1256 0.7488
4.500 0.8082 0.02677 0.01634 -0.0734 0.1160 0.7506
4.750 0.8344 0.02743 0.01692 -0.0737 0.1084 0.7526
5.000 0.8626 0.02807 0.01759 -0.0743 0.1017 0.7545
5.250 0.8855 0.02868 0.01819 -0.0736 0.0966 0.7558
5.500 0.9077 0.02940 0.01889 -0.0728 0.0924 0.7572
5.750 0.9310 0.03002 0.01961 -0.0721 0.0880 0.7588
6.000 0.9539 0.03071 0.02030 -0.0714 0.0843 0.7607
6.250 0.9779 0.03158 0.02114 -0.0710 0.0813 0.7627
6.500 1.0038 0.03236 0.02206 -0.0709 0.0779 0.7647
6.750 1.0294 0.03317 0.02291 -0.0710 0.0747 0.7666
7.000 1.0551 0.03411 0.02379 -0.0712 0.0722 0.7685
7.250 1.0834 0.03525 0.02504 -0.0717 0.0699 0.7705
7.500 1.1094 0.03632 0.02628 -0.0718 0.0673 0.7722
7.750 1.1310 0.03726 0.02731 -0.0710 0.0651 0.7736
8.000 1.1525 0.03823 0.02828 -0.0703 0.0633 0.7751
8.250 1.1754 0.03956 0.02966 -0.0698 0.0618 0.7769
8.500 1.1970 0.04107 0.03147 -0.0691 0.0602 0.7789
8.750 1.2171 0.04261 0.03325 -0.0682 0.0586 0.7811
9.000 1.2362 0.04405 0.03487 -0.0674 0.0570 0.7835
9.250 1.2550 0.04541 0.03633 -0.0667 0.0557 0.7858
9.500 1.2747 0.04681 0.03776 -0.0663 0.0545 0.7880
9.750 1.2871 0.04865 0.03981 -0.0645 0.0535 0.7894
10.000 1.2928 0.05093 0.04251 -0.0618 0.0525 0.7910
10.250 1.2946 0.05330 0.04525 -0.0588 0.0517 0.7926
10.500 1.2919 0.05570 0.04798 -0.0554 0.0511 0.7944
10.750 1.2886 0.05835 0.05094 -0.0524 0.0504 0.7963
11.000 1.2835 0.06113 0.05402 -0.0497 0.0498 0.7983
11.250 1.2769 0.06405 0.05719 -0.0473 0.0492 0.8004
11.500 1.2694 0.06712 0.06049 -0.0453 0.0487 0.8025
11.750 1.2585 0.07046 0.06406 -0.0436 0.0483 0.8042
12.000 1.2452 0.07404 0.06786 -0.0421 0.0479 0.8057
12.250 1.2282 0.07831 0.07237 -0.0414 0.0476 0.8071
12.500 1.2066 0.08352 0.07782 -0.0417 0.0474 0.8084
12.750 1.1567 0.09354 0.08827 -0.0456 0.0476 0.8089
|
Polar data table (+)
Polar graphs
<< Back to SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il)