NASA SC(2)-0706 AIRFOIL (sc20706-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0706 AIRFOIL (sc20706-il) Reynolds number: 50,000 Max Cl/Cd: 25.29 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20706-il-50000-n5.txt Download as CSV file: xf-sc20706-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0706 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4817 0.10788 0.10088 -0.0133 1.0000 0.1244
-10.250 -0.5012 0.09868 0.09173 -0.0207 1.0000 0.0657
-9.750 -0.6046 0.09807 0.09080 -0.0209 1.0000 0.0512
-9.500 -0.6040 0.09385 0.08663 -0.0218 1.0000 0.0509
-9.250 -0.6036 0.08942 0.08225 -0.0234 1.0000 0.0506
-9.000 -0.6027 0.08450 0.07737 -0.0266 1.0000 0.0502
-8.750 -0.6014 0.07960 0.07248 -0.0298 1.0000 0.0497
-8.500 -0.5993 0.07467 0.06751 -0.0329 1.0000 0.0492
-8.250 -0.5952 0.06965 0.06241 -0.0360 1.0000 0.0486
-8.000 -0.5883 0.06450 0.05712 -0.0391 1.0000 0.0477
-7.750 -0.5775 0.05920 0.05158 -0.0425 1.0000 0.0468
-7.500 -0.5621 0.05385 0.04588 -0.0459 1.0000 0.0459
-7.250 -0.5416 0.04865 0.04020 -0.0492 1.0000 0.0453
-7.000 -0.5169 0.04387 0.03487 -0.0521 1.0000 0.0451
-6.750 -0.4892 0.03961 0.03001 -0.0545 1.0000 0.0453
-6.500 -0.4600 0.03592 0.02565 -0.0562 1.0000 0.0461
-6.250 -0.4301 0.03303 0.02212 -0.0574 1.0000 0.0494
-6.000 -0.4020 0.03048 0.01916 -0.0580 1.0000 0.0535
-5.750 -0.3755 0.02839 0.01683 -0.0579 1.0000 0.0566
-5.500 -0.3498 0.02657 0.01475 -0.0570 1.0000 0.0601
-5.250 -0.3250 0.02505 0.01303 -0.0560 1.0000 0.0667
-5.000 -0.2998 0.02383 0.01158 -0.0553 1.0000 0.0777
-4.750 -0.2741 0.02243 0.01016 -0.0549 1.0000 0.0876
-4.500 -0.2447 0.02108 0.00886 -0.0558 1.0000 0.1134
-4.250 -0.2043 0.01842 0.00729 -0.0605 1.0000 0.2780
-4.000 -0.1903 0.01753 0.00797 -0.0562 1.0000 0.6256
-3.750 -0.1784 0.01784 0.00831 -0.0510 1.0000 0.7153
-3.500 -0.1736 0.01812 0.00856 -0.0439 1.0000 0.7755
-3.250 -0.1677 0.01812 0.00851 -0.0374 1.0000 0.8203
-3.000 -0.1562 0.01788 0.00814 -0.0330 1.0000 0.8538
-2.750 -0.1409 0.01749 0.00762 -0.0298 1.0000 0.8807
-2.500 -0.1214 0.01706 0.00704 -0.0279 1.0000 0.9026
-2.250 -0.0986 0.01663 0.00648 -0.0270 1.0000 0.9223
-2.000 -0.0735 0.01622 0.00591 -0.0266 1.0000 0.9421
-1.750 -0.0446 0.01585 0.00545 -0.0273 1.0000 0.9629
-1.500 -0.0177 0.01552 0.00509 -0.0277 1.0000 0.9931
-1.250 0.0127 0.01548 0.00497 -0.0291 1.0000 1.0000
-1.000 0.0452 0.01553 0.00495 -0.0310 1.0000 1.0000
-0.750 0.0778 0.01561 0.00500 -0.0327 1.0000 1.0000
-0.500 0.1102 0.01571 0.00510 -0.0345 1.0000 1.0000
-0.250 0.1424 0.01584 0.00527 -0.0361 1.0000 1.0000
0.000 0.1743 0.01599 0.00550 -0.0376 1.0000 1.0000
0.250 0.2058 0.01616 0.00577 -0.0390 1.0000 1.0000
0.500 0.2370 0.01635 0.00609 -0.0403 1.0000 1.0000
0.750 0.2678 0.01657 0.00648 -0.0415 1.0000 1.0000
1.000 0.2981 0.01682 0.00698 -0.0426 1.0000 1.0000
1.250 0.3281 0.01709 0.00750 -0.0436 1.0000 1.0000
1.500 0.3577 0.01739 0.00810 -0.0446 1.0000 1.0000
1.750 0.3870 0.01772 0.00880 -0.0454 1.0000 1.0000
2.000 0.5013 0.01982 0.00808 -0.0574 0.1595 1.0000
2.250 0.5299 0.02173 0.00957 -0.0578 0.1030 1.0000
2.500 0.5607 0.02315 0.01106 -0.0584 0.0806 1.0000
2.750 0.5937 0.02483 0.01290 -0.0590 0.0714 1.0000
3.000 0.6254 0.02657 0.01475 -0.0597 0.0607 1.0000
3.250 0.6581 0.02849 0.01701 -0.0599 0.0551 1.0000
3.500 0.6895 0.03080 0.01959 -0.0601 0.0522 1.0000
3.750 0.7183 0.03343 0.02243 -0.0603 0.0493 1.0000
4.000 0.7461 0.03609 0.02567 -0.0599 0.0459 1.0000
4.250 0.7722 0.03903 0.02922 -0.0593 0.0434 1.0000
4.500 0.7960 0.04252 0.03336 -0.0585 0.0429 1.0000
4.750 0.8173 0.04633 0.03773 -0.0576 0.0429 1.0000
5.000 0.8359 0.05046 0.04241 -0.0567 0.0431 1.0000
5.250 0.8518 0.05489 0.04733 -0.0559 0.0436 1.0000
5.500 0.8652 0.05954 0.05242 -0.0552 0.0442 1.0000
5.750 0.8762 0.06435 0.05760 -0.0547 0.0451 1.0000
6.000 0.8849 0.06926 0.06279 -0.0545 0.0460 1.0000
6.250 0.8915 0.07423 0.06799 -0.0545 0.0467 1.0000
6.500 0.8960 0.07923 0.07319 -0.0547 0.0472 1.0000
6.750 0.8985 0.08428 0.07840 -0.0551 0.0475 1.0000
7.000 0.8991 0.08936 0.08361 -0.0558 0.0477 1.0000
7.250 0.8988 0.09443 0.08877 -0.0566 0.0480 1.0000
7.500 0.8989 0.09953 0.09392 -0.0574 0.0483 1.0000
8.000 0.7336 0.10502 0.09977 -0.0545 0.0578 1.0000
8.250 0.7388 0.10958 0.10432 -0.0537 0.0608 1.0000
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Polar data table (+)
Polar graphs
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