NASA SC(2)-0402 AIRFOIL (sc20402-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0402 AIRFOIL (sc20402-il) Reynolds number: 50,000 Max Cl/Cd: 14.19 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20402-il-50000.txt Download as CSV file: xf-sc20402-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0402 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.7209 0.12319 0.11672 0.0305 1.0000 0.1320
-8.750 -0.7055 0.11683 0.11034 0.0332 1.0000 0.1425
-8.500 -0.7142 0.11537 0.10900 0.0279 1.0000 0.1450
-8.250 -0.7014 0.10977 0.10339 0.0300 1.0000 0.1563
-8.000 -0.6949 0.10539 0.09905 0.0299 1.0000 0.1644
-7.750 -0.6991 0.10319 0.09695 0.0218 1.0000 0.1712
-7.500 -0.6910 0.09872 0.09250 0.0216 1.0000 0.1839
-7.250 -0.6842 0.09465 0.08845 0.0190 1.0000 0.1971
-7.000 -0.6751 0.08998 0.08382 0.0200 1.0000 0.2125
-6.750 -0.6657 0.08596 0.07979 0.0208 1.0000 0.2336
-6.500 -0.5724 0.07025 0.06400 0.0219 1.0000 0.2962
-6.250 -0.6507 0.07822 0.07157 0.0174 1.0000 0.2895
-6.000 -0.6402 0.07440 0.06781 0.0238 1.0000 0.3232
-5.750 -0.6338 0.07119 0.06466 0.0272 1.0000 0.3700
-5.500 -0.6255 0.06819 0.06172 0.0349 1.0000 0.4246
-4.750 -0.4442 0.04900 0.04212 0.0572 1.0000 0.9106
-4.500 -0.4718 0.04889 0.04217 0.0620 1.0000 0.8664
-4.250 -0.3936 0.03751 0.02778 -0.0298 1.0000 0.1313
-4.000 -0.3580 0.03359 0.02330 -0.0305 1.0000 0.1004
-3.750 -0.3209 0.03103 0.01977 -0.0306 1.0000 0.0806
-3.500 -0.2913 0.02801 0.01648 -0.0306 1.0000 0.0755
-3.250 -0.2611 0.02571 0.01376 -0.0303 1.0000 0.0750
-3.000 -0.2318 0.02383 0.01149 -0.0297 1.0000 0.0777
-2.750 -0.2040 0.02220 0.00958 -0.0285 1.0000 0.0802
-2.500 -0.1790 0.02038 0.00772 -0.0269 1.0000 0.0825
-2.250 -0.1521 0.01898 0.00619 -0.0259 1.0000 0.0853
-1.750 -0.1123 0.01291 0.00332 -0.0194 1.0000 1.0000
-1.500 -0.0835 0.01288 0.00232 -0.0187 1.0000 1.0000
-1.250 -0.0559 0.01284 0.00184 -0.0186 1.0000 1.0000
-1.000 -0.0286 0.01282 0.00152 -0.0186 1.0000 1.0000
-0.750 -0.0015 0.01280 0.00132 -0.0186 1.0000 1.0000
-0.500 0.0256 0.01280 0.00123 -0.0185 1.0000 1.0000
-0.250 0.0525 0.01282 0.00122 -0.0184 1.0000 1.0000
0.000 0.0793 0.01284 0.00132 -0.0183 1.0000 1.0000
0.250 0.1061 0.01288 0.00152 -0.0182 1.0000 1.0000
0.500 0.1329 0.01293 0.00182 -0.0180 1.0000 1.0000
0.750 0.1598 0.01299 0.00228 -0.0177 1.0000 1.0000
1.000 0.2114 0.01512 0.00362 -0.0198 0.3233 1.0000
1.250 0.2379 0.01837 0.00553 -0.0193 0.0885 1.0000
1.500 0.2660 0.01973 0.00705 -0.0186 0.0827 1.0000
1.750 0.2954 0.02145 0.00889 -0.0178 0.0805 1.0000
2.000 0.3256 0.02326 0.01090 -0.0171 0.0780 1.0000
2.250 0.3557 0.02507 0.01307 -0.0164 0.0746 1.0000
2.500 0.3857 0.02723 0.01562 -0.0159 0.0737 1.0000
2.750 0.4156 0.02992 0.01868 -0.0154 0.0777 1.0000
3.000 0.4474 0.03265 0.02201 -0.0147 0.0906 1.0000
3.250 0.4820 0.03564 0.02578 -0.0142 0.1155 1.0000
3.500 0.5223 0.03947 0.03052 -0.0147 0.1694 1.0000
3.750 0.6271 0.05112 0.04522 -0.1006 0.7892 1.0000
4.000 0.5857 0.05208 0.04599 -0.0983 0.8578 1.0000
4.250 0.6393 0.05816 0.05215 -0.1034 0.7989 1.0000
5.250 0.7425 0.07359 0.06749 -0.0511 0.3294 1.0000
5.500 0.7505 0.07764 0.07147 -0.0468 0.2893 1.0000
5.750 0.6677 0.07062 0.06492 -0.0474 0.2961 1.0000
6.000 0.6725 0.07513 0.06939 -0.0465 0.2688 1.0000
6.250 0.7748 0.09071 0.08509 -0.0468 0.2098 1.0000
6.500 0.7797 0.09456 0.08896 -0.0518 0.1939 1.0000
6.750 0.7859 0.09890 0.09327 -0.0538 0.1808 1.0000
7.000 0.7932 0.10354 0.09790 -0.0544 0.1695 1.0000
7.250 0.8023 0.10867 0.10301 -0.0530 0.1578 1.0000
7.500 0.7965 0.11130 0.10557 -0.0611 0.1529 1.0000
7.750 0.8063 0.11664 0.11090 -0.0597 0.1442 1.0000
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Polar data table (+)
Polar graphs
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