NASA/LANGLEY RC-SC2 AIRFOIL (rcsc2-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC-SC2 AIRFOIL (rcsc2-il) Reynolds number: 100,000 Max Cl/Cd: 37.93 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rcsc2-il-100000.txt Download as CSV file: xf-rcsc2-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC-SC2 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5690 0.10859 0.10296 -0.0210 1.0000 0.1303
-9.750 -0.5475 0.10609 0.10045 -0.0181 1.0000 0.1342
-9.500 -0.5482 0.10275 0.09714 -0.0192 1.0000 0.1397
-9.250 -0.6056 0.09673 0.09128 -0.0303 1.0000 0.1437
-9.000 -0.5658 0.09405 0.08858 -0.0234 1.0000 0.1475
-8.750 -0.5557 0.09139 0.08593 -0.0221 1.0000 0.1521
-8.500 -0.5865 0.08658 0.08123 -0.0268 1.0000 0.1578
-8.250 -0.6619 0.08332 0.07789 -0.0277 1.0000 0.1598
-8.000 -0.6160 0.07897 0.07372 -0.0253 1.0000 0.1640
-7.750 -0.6125 0.07636 0.07113 -0.0234 1.0000 0.1685
-7.250 -0.6462 0.06936 0.06409 -0.0207 1.0000 0.1805
-7.000 -0.6414 0.06679 0.06153 -0.0185 1.0000 0.1858
-6.750 -0.6568 0.06347 0.05810 -0.0166 1.0000 0.1960
-6.500 -0.6875 0.04670 0.03949 -0.0151 1.0000 0.0975
-6.250 -0.6828 0.04111 0.03310 -0.0116 1.0000 0.0846
-6.000 -0.6691 0.03794 0.02973 -0.0097 1.0000 0.0826
-5.750 -0.6543 0.03505 0.02651 -0.0076 1.0000 0.0807
-5.500 -0.6375 0.03252 0.02359 -0.0056 1.0000 0.0797
-5.250 -0.6187 0.03061 0.02136 -0.0039 1.0000 0.0807
-5.000 -0.5984 0.02890 0.01934 -0.0024 1.0000 0.0821
-4.750 -0.5766 0.02727 0.01741 -0.0010 1.0000 0.0832
-4.500 -0.5535 0.02580 0.01567 0.0003 1.0000 0.0845
-4.250 -0.5296 0.02450 0.01413 0.0014 1.0000 0.0862
-4.000 -0.5057 0.02299 0.01275 0.0021 1.0000 0.0904
-3.750 -0.4823 0.02213 0.01184 0.0031 1.0000 0.0964
-3.500 -0.4581 0.02098 0.01074 0.0039 1.0000 0.1028
-3.250 -0.4346 0.02018 0.00995 0.0049 1.0000 0.1130
-3.000 -0.4123 0.01915 0.00912 0.0060 1.0000 0.1301
-2.750 -0.3909 0.01803 0.00832 0.0072 1.0000 0.1649
-2.500 -0.3711 0.01617 0.00750 0.0083 1.0000 0.3045
-2.250 -0.3581 0.01434 0.00803 0.0135 1.0000 0.7899
-2.000 -0.3024 0.01547 0.00922 0.0121 1.0000 0.9369
-1.750 -0.1688 0.01662 0.00991 -0.0068 1.0000 0.9841
-1.500 -0.0857 0.01661 0.00966 -0.0180 1.0000 1.0000
-1.250 -0.0815 0.01639 0.00938 -0.0146 1.0000 1.0000
-1.000 -0.0770 0.01620 0.00914 -0.0111 1.0000 1.0000
-0.750 -0.0720 0.01606 0.00895 -0.0076 1.0000 1.0000
-0.500 -0.0662 0.01596 0.00881 -0.0042 1.0000 1.0000
-0.250 -0.0594 0.01591 0.00871 -0.0010 1.0000 1.0000
0.000 -0.0512 0.01590 0.00865 0.0021 1.0000 1.0000
0.250 -0.0416 0.01593 0.00865 0.0049 1.0000 1.0000
0.500 -0.0307 0.01602 0.00869 0.0074 1.0000 1.0000
0.750 -0.0185 0.01615 0.00880 0.0097 1.0000 1.0000
1.000 -0.0048 0.01633 0.00896 0.0116 1.0000 1.0000
1.250 0.0101 0.01656 0.00918 0.0133 1.0000 1.0000
1.500 0.0260 0.01685 0.00947 0.0147 1.0000 1.0000
1.750 0.0571 0.01729 0.00993 0.0131 0.9961 1.0000
2.000 0.1273 0.01786 0.01060 0.0042 0.9797 1.0000
2.250 0.1942 0.01817 0.01103 -0.0036 0.9628 1.0000
2.500 0.2715 0.01800 0.01106 -0.0126 0.9411 1.0000
2.750 0.3603 0.01707 0.01040 -0.0227 0.9126 1.0000
3.000 0.4324 0.01574 0.00934 -0.0289 0.8780 1.0000
3.250 0.4780 0.01463 0.00840 -0.0298 0.8248 1.0000
3.500 0.5367 0.01415 0.00683 -0.0314 0.5312 1.0000
3.750 0.5429 0.01605 0.00726 -0.0271 0.3118 1.0000
4.000 0.5559 0.01734 0.00790 -0.0245 0.2268 1.0000
4.250 0.5719 0.01836 0.00855 -0.0223 0.1814 1.0000
4.500 0.5890 0.01937 0.00934 -0.0203 0.1505 1.0000
4.750 0.6068 0.02047 0.01017 -0.0184 0.1280 1.0000
5.000 0.6267 0.02160 0.01118 -0.0168 0.1114 1.0000
5.250 0.6483 0.02268 0.01221 -0.0154 0.1008 1.0000
5.500 0.6710 0.02392 0.01351 -0.0142 0.0931 1.0000
5.750 0.6931 0.02510 0.01458 -0.0132 0.0871 1.0000
6.000 0.7170 0.02676 0.01637 -0.0121 0.0837 1.0000
6.250 0.7394 0.02831 0.01817 -0.0108 0.0813 1.0000
6.500 0.7607 0.03003 0.02012 -0.0093 0.0796 1.0000
6.750 0.7804 0.03189 0.02221 -0.0076 0.0783 1.0000
7.000 0.7990 0.03372 0.02423 -0.0059 0.0770 1.0000
7.250 0.8173 0.03561 0.02622 -0.0045 0.0754 1.0000
7.500 0.8331 0.03828 0.02905 -0.0028 0.0742 1.0000
7.750 0.8462 0.04108 0.03215 -0.0006 0.0740 1.0000
8.000 0.8462 0.04447 0.03649 0.0042 0.0770 1.0000
8.250 0.8430 0.04957 0.04221 0.0080 0.0811 1.0000
8.500 0.8476 0.05363 0.04648 0.0103 0.0836 1.0000
8.750 0.8358 0.06191 0.05529 0.0133 0.0976 1.0000
9.000 0.7707 0.08467 0.07910 0.0114 0.1735 1.0000
9.250 0.6722 0.09113 0.08566 0.0043 0.1645 1.0000
9.500 0.6800 0.09444 0.08896 0.0047 0.1612 1.0000
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Polar data table (+)
Polar graphs
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