NASA SC(2)-0610 AIRFOIL (sc20610-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: NASA SC(2)-0610 AIRFOIL (sc20610-il) Reynolds number: 1,000,000 Max Cl/Cd: 74.25 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20610-il-1000000.txt Download as CSV file: xf-sc20610-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0610 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.250 0.4575 0.00647 0.00203 -0.1046 0.6165 0.6993
0.500 0.4804 0.00739 0.00229 -0.1037 0.4539 0.7025
0.750 0.5052 0.00814 0.00251 -0.1033 0.3270 0.7052
1.000 0.5309 0.00870 0.00269 -0.1030 0.2297 0.7080
1.250 0.5573 0.00916 0.00288 -0.1028 0.1605 0.7099
1.500 0.5842 0.00954 0.00307 -0.1027 0.1172 0.7119
1.750 0.6117 0.00983 0.00324 -0.1026 0.0908 0.7141
2.000 0.6393 0.01010 0.00342 -0.1025 0.0742 0.7163
2.250 0.6673 0.01031 0.00359 -0.1024 0.0653 0.7186
2.500 0.6951 0.01056 0.00379 -0.1024 0.0578 0.7206
2.750 0.7232 0.01075 0.00395 -0.1023 0.0533 0.7224
3.000 0.7506 0.01099 0.00418 -0.1022 0.0480 0.7246
3.250 0.7785 0.01115 0.00436 -0.1021 0.0451 0.7266
3.500 0.8057 0.01143 0.00461 -0.1019 0.0408 0.7287
3.750 0.8332 0.01164 0.00484 -0.1018 0.0382 0.7311
4.000 0.8605 0.01188 0.00506 -0.1016 0.0351 0.7334
4.250 0.8876 0.01219 0.00537 -0.1014 0.0320 0.7356
4.500 0.9150 0.01243 0.00560 -0.1012 0.0293 0.7376
4.750 0.9416 0.01281 0.00597 -0.1009 0.0266 0.7395
5.000 0.9686 0.01305 0.00624 -0.1007 0.0249 0.7418
5.250 0.9950 0.01340 0.00658 -0.1003 0.0233 0.7439
5.500 1.0205 0.01390 0.00712 -0.0998 0.0219 0.7459
5.750 1.0469 0.01423 0.00750 -0.0994 0.0212 0.7482
6.000 1.0730 0.01460 0.00790 -0.0990 0.0204 0.7506
6.250 1.0989 0.01499 0.00832 -0.0986 0.0197 0.7530
6.500 1.1244 0.01546 0.00880 -0.0981 0.0191 0.7551
6.750 1.1483 0.01614 0.00954 -0.0973 0.0184 0.7573
7.000 1.1715 0.01694 0.01042 -0.0964 0.0179 0.7595
7.250 1.1964 0.01740 0.01095 -0.0958 0.0177 0.7616
7.500 1.2211 0.01791 0.01153 -0.0952 0.0174 0.7639
7.750 1.2456 0.01841 0.01210 -0.0945 0.0170 0.7662
8.000 1.2697 0.01898 0.01272 -0.0938 0.0166 0.7686
8.250 1.2933 0.01959 0.01339 -0.0930 0.0163 0.7707
8.500 1.3166 0.02022 0.01409 -0.0922 0.0159 0.7729
8.750 1.3393 0.02087 0.01482 -0.0913 0.0157 0.7752
9.000 1.3613 0.02159 0.01561 -0.0903 0.0154 0.7773
9.250 1.3821 0.02248 0.01658 -0.0892 0.0151 0.7796
9.500 1.4006 0.02372 0.01793 -0.0877 0.0148 0.7819
9.750 1.4139 0.02584 0.02026 -0.0855 0.0145 0.7842
10.000 1.4306 0.02727 0.02185 -0.0837 0.0144 0.7863
10.250 1.4488 0.02827 0.02299 -0.0823 0.0143 0.7885
10.500 1.4658 0.02935 0.02421 -0.0806 0.0142 0.7907
10.750 1.4811 0.03056 0.02558 -0.0787 0.0141 0.7929
11.000 1.4943 0.03194 0.02712 -0.0766 0.0140 0.7952
11.250 1.5055 0.03343 0.02878 -0.0743 0.0139 0.7977
11.500 1.5150 0.03492 0.03043 -0.0718 0.0138 0.8001
11.750 1.5224 0.03643 0.03209 -0.0690 0.0136 0.8022
12.000 1.5252 0.03795 0.03377 -0.0656 0.0134 0.8049
12.250 1.5215 0.03949 0.03547 -0.0612 0.0133 0.8074
12.500 1.5177 0.04138 0.03753 -0.0573 0.0132 0.8099
12.750 1.5120 0.04358 0.03989 -0.0538 0.0131 0.8124
13.000 1.5017 0.04639 0.04288 -0.0506 0.0131 0.8148
13.250 1.4906 0.04950 0.04617 -0.0480 0.0130 0.8168
13.500 1.4758 0.05331 0.05017 -0.0463 0.0129 0.8191
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Polar data table (+)
Polar graphs
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