NASA SC(2)-0412 AIRFOIL (sc20412-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NASA SC(2)-0412 AIRFOIL (sc20412-il) Reynolds number: 50,000 Max Cl/Cd: 24.41 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20412-il-50000.txt Download as CSV file: xf-sc20412-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0412 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5121 0.11805 0.10991 0.0046 1.0000 0.3691
-9.500 -0.6957 0.08588 0.07802 -0.0326 1.0000 0.1869
-9.250 -0.7414 0.07577 0.06779 -0.0381 1.0000 0.1711
-9.000 -0.7357 0.07087 0.06284 -0.0383 1.0000 0.1683
-8.750 -0.7425 0.06558 0.05743 -0.0390 1.0000 0.1651
-8.500 -0.7556 0.05986 0.05140 -0.0400 1.0000 0.1613
-8.250 -0.7597 0.05483 0.04595 -0.0405 1.0000 0.1597
-8.000 -0.7520 0.05106 0.04186 -0.0405 1.0000 0.1613
-7.750 -0.7404 0.04748 0.03790 -0.0405 1.0000 0.1634
-7.500 -0.7251 0.04403 0.03401 -0.0406 1.0000 0.1653
-7.250 -0.7067 0.04098 0.03042 -0.0408 1.0000 0.1691
-7.000 -0.6862 0.03835 0.02766 -0.0404 1.0000 0.1744
-6.750 -0.6640 0.03619 0.02532 -0.0398 1.0000 0.1802
-6.500 -0.6408 0.03406 0.02280 -0.0396 1.0000 0.1880
-6.250 -0.6187 0.03231 0.02112 -0.0386 1.0000 0.1970
-6.000 -0.5957 0.03059 0.01932 -0.0376 1.0000 0.2072
-5.750 -0.5729 0.02916 0.01781 -0.0364 1.0000 0.2210
-5.500 -0.5514 0.02784 0.01662 -0.0346 1.0000 0.2372
-5.250 -0.5313 0.02663 0.01568 -0.0324 1.0000 0.2588
-5.000 -0.5117 0.02531 0.01467 -0.0305 1.0000 0.2909
-4.750 -0.4938 0.02349 0.01357 -0.0288 1.0000 0.3532
-4.500 -0.4937 0.02350 0.01552 -0.0192 1.0000 0.5164
-4.250 -0.4878 0.02731 0.01932 -0.0081 1.0000 0.6450
-4.000 -0.4798 0.02981 0.02168 0.0011 1.0000 0.6901
-3.750 -0.4696 0.03150 0.02324 0.0092 1.0000 0.7256
-3.500 -0.4564 0.03258 0.02417 0.0162 1.0000 0.7598
-3.250 -0.4384 0.03309 0.02453 0.0216 1.0000 0.7941
-3.000 -0.4146 0.03311 0.02438 0.0253 1.0000 0.8288
-2.750 -0.3174 0.03287 0.02370 0.0183 1.0000 0.8899
-2.500 -0.1757 0.03092 0.02124 -0.0010 1.0000 0.9439
-2.250 -0.1040 0.02934 0.01945 -0.0104 1.0000 0.9703
-2.000 -0.0475 0.02804 0.01804 -0.0174 1.0000 0.9861
-1.750 0.0044 0.02698 0.01690 -0.0238 1.0000 0.9993
-1.500 0.0144 0.02666 0.01659 -0.0222 1.0000 1.0000
-1.250 0.0210 0.02644 0.01639 -0.0200 1.0000 1.0000
-1.000 0.0266 0.02626 0.01624 -0.0175 1.0000 1.0000
-0.750 0.0314 0.02613 0.01614 -0.0149 1.0000 1.0000
-0.500 0.0353 0.02603 0.01607 -0.0122 1.0000 1.0000
-0.250 0.0386 0.02596 0.01604 -0.0094 1.0000 1.0000
0.000 0.0415 0.02592 0.01604 -0.0065 1.0000 1.0000
0.250 0.0440 0.02589 0.01605 -0.0036 1.0000 1.0000
0.500 0.0461 0.02587 0.01608 -0.0007 1.0000 1.0000
0.750 0.0479 0.02586 0.01612 0.0022 1.0000 1.0000
1.000 0.0495 0.02586 0.01617 0.0051 1.0000 1.0000
1.250 0.0508 0.02586 0.01624 0.0080 1.0000 1.0000
1.500 0.0520 0.02587 0.01631 0.0109 1.0000 1.0000
1.750 0.0529 0.02588 0.01639 0.0137 1.0000 1.0000
2.000 0.0538 0.02590 0.01649 0.0164 1.0000 1.0000
2.250 0.0550 0.02593 0.01660 0.0190 1.0000 1.0000
2.500 0.0565 0.02600 0.01676 0.0214 1.0000 1.0000
2.750 0.0612 0.02616 0.01702 0.0230 1.0000 1.0000
3.000 0.0713 0.02651 0.01747 0.0235 1.0000 1.0000
3.250 0.0898 0.02712 0.01822 0.0223 0.9983 1.0000
3.500 0.2572 0.02876 0.02034 -0.0020 0.9306 1.0000
3.750 0.5134 0.02340 0.01610 -0.0291 0.8044 1.0000
4.000 0.5527 0.02264 0.01312 -0.0214 0.4111 1.0000
4.250 0.5685 0.02450 0.01413 -0.0194 0.3282 1.0000
4.500 0.5921 0.02580 0.01516 -0.0186 0.2851 1.0000
4.750 0.6184 0.02711 0.01619 -0.0183 0.2584 1.0000
5.000 0.6415 0.02833 0.01740 -0.0175 0.2388 1.0000
5.250 0.6647 0.02972 0.01870 -0.0168 0.2246 1.0000
5.500 0.6832 0.03096 0.02011 -0.0153 0.2124 1.0000
5.750 0.7015 0.03253 0.02184 -0.0139 0.2035 1.0000
6.000 0.7189 0.03403 0.02343 -0.0124 0.1948 1.0000
6.250 0.7341 0.03585 0.02551 -0.0107 0.1881 1.0000
6.500 0.7508 0.03776 0.02773 -0.0093 0.1818 1.0000
6.750 0.7724 0.04012 0.03003 -0.0090 0.1752 1.0000
7.000 0.7877 0.04275 0.03329 -0.0078 0.1717 1.0000
7.250 0.8037 0.04573 0.03678 -0.0071 0.1680 1.0000
7.500 0.8215 0.04874 0.04010 -0.0069 0.1639 1.0000
7.750 0.8355 0.05260 0.04438 -0.0067 0.1631 1.0000
8.000 0.8403 0.05743 0.04980 -0.0065 0.1647 1.0000
8.250 0.8378 0.06302 0.05592 -0.0066 0.1677 1.0000
8.500 0.8353 0.06875 0.06199 -0.0075 0.1710 1.0000
8.750 0.8411 0.07436 0.06775 -0.0087 0.1741 1.0000
9.000 0.6586 0.11393 0.10793 -0.0529 0.3964 1.0000
9.250 0.6542 0.11692 0.11089 -0.0539 0.3803 1.0000
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Polar data table (+)
Polar graphs
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