NASA SC(2)-0712 AIRFOIL (sc20712-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0712 AIRFOIL (sc20712-il) Reynolds number: 50,000 Max Cl/Cd: 24.84 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20712-il-50000.txt Download as CSV file: xf-sc20712-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0712 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4497 0.10651 0.09848 -0.0106 1.0000 0.3920
-9.250 -0.6838 0.07104 0.06327 -0.0447 1.0000 0.1704
-9.000 -0.6910 0.06579 0.05793 -0.0454 1.0000 0.1666
-8.750 -0.7060 0.05893 0.05066 -0.0485 1.0000 0.1616
-8.500 -0.7027 0.05354 0.04479 -0.0509 1.0000 0.1604
-8.250 -0.6889 0.04968 0.04062 -0.0520 1.0000 0.1622
-8.000 -0.6706 0.04582 0.03635 -0.0535 1.0000 0.1636
-7.750 -0.6484 0.04237 0.03245 -0.0549 1.0000 0.1660
-7.500 -0.6222 0.03934 0.02881 -0.0569 1.0000 0.1714
-7.250 -0.5982 0.03679 0.02611 -0.0571 1.0000 0.1766
-7.000 -0.5733 0.03482 0.02398 -0.0571 1.0000 0.1836
-6.750 -0.5475 0.03287 0.02181 -0.0573 1.0000 0.1927
-6.500 -0.5221 0.03131 0.02010 -0.0569 1.0000 0.2032
-6.250 -0.4993 0.02992 0.01881 -0.0558 1.0000 0.2162
-6.000 -0.4766 0.02868 0.01763 -0.0545 1.0000 0.2323
-5.750 -0.4535 0.02752 0.01652 -0.0533 1.0000 0.2547
-5.500 -0.4317 0.02630 0.01563 -0.0519 1.0000 0.2861
-5.250 -0.4077 0.02460 0.01467 -0.0513 1.0000 0.3490
-5.000 -0.4057 0.02458 0.01641 -0.0427 1.0000 0.4974
-4.500 -0.4058 0.02998 0.02180 -0.0214 1.0000 0.6565
-4.250 -0.4029 0.03160 0.02332 -0.0127 1.0000 0.6914
-4.000 -0.3978 0.03264 0.02426 -0.0052 1.0000 0.7243
-3.750 -0.3913 0.03321 0.02472 0.0014 1.0000 0.7563
-3.500 -0.3860 0.03332 0.02473 0.0084 1.0000 0.7853
-3.250 -0.3786 0.03305 0.02436 0.0142 1.0000 0.8157
-3.000 -0.3707 0.03247 0.02369 0.0196 1.0000 0.8488
-2.750 -0.3567 0.03147 0.02258 0.0243 1.0000 0.8835
-2.500 -0.3130 0.03036 0.02126 0.0233 1.0000 0.9258
-2.250 -0.1994 0.02962 0.02015 0.0076 1.0000 0.9613
-2.000 -0.1187 0.02895 0.01927 -0.0036 1.0000 0.9802
-1.750 -0.0631 0.02844 0.01865 -0.0106 1.0000 0.9928
-1.500 -0.0278 0.02808 0.01824 -0.0139 1.0000 1.0000
-1.250 -0.0233 0.02782 0.01799 -0.0114 1.0000 1.0000
-1.000 -0.0190 0.02757 0.01776 -0.0088 1.0000 1.0000
-0.750 -0.0148 0.02735 0.01755 -0.0062 1.0000 1.0000
-0.500 -0.0108 0.02714 0.01736 -0.0037 1.0000 1.0000
-0.250 -0.0069 0.02693 0.01719 -0.0011 1.0000 1.0000
0.000 -0.0032 0.02674 0.01703 0.0015 1.0000 1.0000
0.250 0.0005 0.02656 0.01689 0.0041 1.0000 1.0000
0.500 0.0045 0.02639 0.01677 0.0065 1.0000 1.0000
0.750 0.0088 0.02625 0.01668 0.0088 1.0000 1.0000
1.000 0.0153 0.02617 0.01666 0.0107 1.0000 1.0000
1.250 0.0268 0.02622 0.01678 0.0116 1.0000 1.0000
1.500 0.0433 0.02645 0.01708 0.0115 1.0000 1.0000
1.750 0.0636 0.02684 0.01756 0.0106 1.0000 1.0000
2.000 0.0863 0.02737 0.01819 0.0092 1.0000 1.0000
2.250 0.1105 0.02804 0.01898 0.0075 1.0000 1.0000
2.500 0.1355 0.02885 0.01992 0.0054 1.0000 1.0000
2.750 0.1607 0.02981 0.02104 0.0031 1.0000 1.0000
3.000 0.2356 0.03163 0.02311 -0.0077 0.9730 1.0000
3.250 0.3489 0.03194 0.02382 -0.0215 0.9128 1.0000
3.500 0.4430 0.02993 0.02227 -0.0287 0.8561 1.0000
3.750 0.5278 0.02534 0.01825 -0.0298 0.7794 1.0000
4.000 0.6071 0.02444 0.01442 -0.0270 0.3308 1.0000
4.250 0.6430 0.02636 0.01580 -0.0284 0.2712 1.0000
4.500 0.6847 0.02815 0.01734 -0.0308 0.2362 1.0000
4.750 0.7210 0.02987 0.01901 -0.0324 0.2143 1.0000
5.000 0.7547 0.03177 0.02093 -0.0336 0.1993 1.0000
5.250 0.7869 0.03390 0.02305 -0.0347 0.1876 1.0000
5.500 0.8150 0.03586 0.02535 -0.0350 0.1783 1.0000
5.750 0.8456 0.03856 0.02807 -0.0361 0.1715 1.0000
6.000 0.8684 0.04093 0.03106 -0.0357 0.1657 1.0000
6.250 0.8923 0.04375 0.03426 -0.0357 0.1617 1.0000
6.500 0.9170 0.04680 0.03752 -0.0361 0.1582 1.0000
6.750 0.9384 0.05052 0.04145 -0.0363 0.1549 1.0000
7.000 0.9512 0.05424 0.04575 -0.0354 0.1540 1.0000
7.250 0.9656 0.05868 0.05060 -0.0351 0.1548 1.0000
7.500 0.9714 0.06313 0.05562 -0.0341 0.1571 1.0000
7.750 0.9444 0.06996 0.06334 -0.0321 0.1660 1.0000
8.000 0.9452 0.07560 0.06920 -0.0323 0.1697 1.0000
8.250 0.5195 0.10893 0.10334 -0.0460 0.4036 1.0000
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Polar data table (+)
Polar graphs
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