NASA SC(2)-0612 AIRFOIL (sc20612-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0612 AIRFOIL (sc20612-il) Reynolds number: 50,000 Max Cl/Cd: 24.54 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20612-il-50000.txt Download as CSV file: xf-sc20612-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0612 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 -0.6168 0.08876 0.08094 -0.0368 1.0000 0.1969
-9.500 -0.5812 0.08715 0.07927 -0.0333 1.0000 0.2002
-9.250 -0.7136 0.06986 0.06190 -0.0457 1.0000 0.1658
-9.000 -0.7197 0.06486 0.05672 -0.0462 1.0000 0.1624
-8.750 -0.7227 0.06006 0.05170 -0.0467 1.0000 0.1612
-8.500 -0.7218 0.05533 0.04662 -0.0477 1.0000 0.1610
-8.250 -0.7141 0.05084 0.04168 -0.0488 1.0000 0.1616
-8.000 -0.6995 0.04668 0.03699 -0.0501 1.0000 0.1626
-7.750 -0.6799 0.04300 0.03274 -0.0514 1.0000 0.1652
-7.500 -0.6601 0.04069 0.03054 -0.0506 1.0000 0.1712
-7.250 -0.6364 0.03801 0.02744 -0.0512 1.0000 0.1771
-7.000 -0.6129 0.03563 0.02484 -0.0514 1.0000 0.1845
-6.750 -0.5885 0.03376 0.02275 -0.0512 1.0000 0.1935
-6.500 -0.5652 0.03200 0.02096 -0.0507 1.0000 0.2035
-6.250 -0.5406 0.03042 0.01923 -0.0501 1.0000 0.2150
-6.000 -0.5166 0.02913 0.01787 -0.0493 1.0000 0.2297
-5.750 -0.4954 0.02792 0.01678 -0.0476 1.0000 0.2454
-5.500 -0.4748 0.02678 0.01589 -0.0457 1.0000 0.2666
-5.250 -0.4530 0.02556 0.01494 -0.0442 1.0000 0.2985
-5.000 -0.4310 0.02376 0.01400 -0.0433 1.0000 0.3692
-4.750 -0.4337 0.02438 0.01634 -0.0328 1.0000 0.5211
-4.500 -0.4322 0.02766 0.01958 -0.0217 1.0000 0.6297
-4.250 -0.4287 0.02989 0.02169 -0.0125 1.0000 0.6753
-4.000 -0.4238 0.03137 0.02305 -0.0043 1.0000 0.7104
-3.750 -0.4180 0.03231 0.02389 0.0033 1.0000 0.7422
-3.500 -0.4111 0.03276 0.02423 0.0104 1.0000 0.7721
-3.250 -0.4020 0.03275 0.02411 0.0163 1.0000 0.8033
-3.000 -0.3906 0.03239 0.02364 0.0215 1.0000 0.8351
-2.750 -0.3732 0.03174 0.02286 0.0256 1.0000 0.8704
-2.500 -0.2893 0.03081 0.02159 0.0190 1.0000 0.9284
-2.250 -0.1524 0.02961 0.01997 -0.0012 1.0000 0.9668
-2.000 -0.0956 0.02879 0.01901 -0.0083 1.0000 0.9827
-1.750 -0.0454 0.02812 0.01824 -0.0143 1.0000 0.9939
-1.500 -0.0149 0.02769 0.01778 -0.0166 1.0000 1.0000
-1.250 -0.0105 0.02746 0.01756 -0.0141 1.0000 1.0000
-1.000 -0.0062 0.02726 0.01736 -0.0115 1.0000 1.0000
-0.750 -0.0022 0.02707 0.01719 -0.0089 1.0000 1.0000
-0.500 0.0017 0.02690 0.01705 -0.0062 1.0000 1.0000
-0.250 0.0053 0.02674 0.01692 -0.0035 1.0000 1.0000
0.000 0.0087 0.02659 0.01681 -0.0008 1.0000 1.0000
0.250 0.0119 0.02645 0.01671 0.0019 1.0000 1.0000
0.500 0.0149 0.02632 0.01663 0.0045 1.0000 1.0000
0.750 0.0179 0.02620 0.01656 0.0072 1.0000 1.0000
1.000 0.0210 0.02610 0.01651 0.0097 1.0000 1.0000
1.250 0.0245 0.02601 0.01649 0.0121 1.0000 1.0000
1.500 0.0297 0.02597 0.01652 0.0141 1.0000 1.0000
1.750 0.0397 0.02607 0.01670 0.0152 1.0000 1.0000
2.000 0.0548 0.02634 0.01705 0.0152 1.0000 1.0000
2.250 0.0736 0.02677 0.01758 0.0145 1.0000 1.0000
2.500 0.0949 0.02736 0.01829 0.0132 1.0000 1.0000
2.750 0.1176 0.02811 0.01918 0.0114 1.0000 1.0000
3.000 0.1409 0.02902 0.02025 0.0093 1.0000 1.0000
3.250 0.2619 0.03085 0.02243 -0.0080 0.9451 1.0000
3.500 0.3727 0.02996 0.02199 -0.0194 0.8842 1.0000
3.750 0.4847 0.02604 0.01866 -0.0259 0.8115 1.0000
4.000 0.5880 0.02396 0.01398 -0.0251 0.3457 1.0000
4.250 0.6151 0.02570 0.01513 -0.0250 0.2892 1.0000
4.500 0.6498 0.02720 0.01635 -0.0262 0.2556 1.0000
4.750 0.6796 0.02859 0.01773 -0.0265 0.2344 1.0000
5.000 0.7079 0.03014 0.01925 -0.0267 0.2187 1.0000
5.250 0.7356 0.03189 0.02093 -0.0270 0.2056 1.0000
5.500 0.7603 0.03352 0.02285 -0.0267 0.1947 1.0000
5.750 0.7860 0.03561 0.02512 -0.0267 0.1854 1.0000
6.000 0.8123 0.03771 0.02743 -0.0269 0.1770 1.0000
6.250 0.8361 0.04033 0.03034 -0.0269 0.1704 1.0000
6.500 0.8570 0.04313 0.03366 -0.0265 0.1659 1.0000
6.750 0.8789 0.04601 0.03685 -0.0264 0.1614 1.0000
7.000 0.9034 0.04951 0.04036 -0.0272 0.1567 1.0000
7.250 0.9170 0.05334 0.04477 -0.0264 0.1560 1.0000
7.500 0.9297 0.05769 0.04956 -0.0260 0.1563 1.0000
7.750 0.9398 0.06229 0.05456 -0.0257 0.1567 1.0000
8.000 0.9470 0.06709 0.05975 -0.0254 0.1576 1.0000
8.250 0.9049 0.07484 0.06844 -0.0243 0.1698 1.0000
8.500 0.9266 0.08059 0.07423 -0.0256 0.1738 1.0000
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Polar data table (+)
Polar graphs
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