NASA SC(2)-0406 AIRFOIL (sc20406-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0406 AIRFOIL (sc20406-il) Reynolds number: 100,000 Max Cl/Cd: 37.15 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20406-il-100000.txt Download as CSV file: xf-sc20406-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0406 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5493 0.08747 0.08284 -0.0001 1.0000 0.1071
-8.500 -0.5672 0.08273 0.07818 -0.0050 1.0000 0.1105
-8.250 -0.5935 0.07704 0.07255 -0.0133 1.0000 0.1113
-8.000 -0.6639 0.08414 0.07943 -0.0016 1.0000 0.1042
-7.500 -0.6602 0.07231 0.06746 -0.0155 1.0000 0.1143
-7.250 -0.6480 0.06864 0.06378 -0.0158 1.0000 0.1206
-7.000 -0.6396 0.06339 0.05838 -0.0201 1.0000 0.1291
-6.750 -0.6275 0.05890 0.05369 -0.0234 1.0000 0.1416
-6.500 -0.6123 0.05496 0.04962 -0.0250 1.0000 0.1553
-6.250 -0.5954 0.05130 0.04585 -0.0256 1.0000 0.1702
-6.000 -0.5469 0.03809 0.03070 -0.0322 1.0000 0.0694
-5.750 -0.5217 0.03330 0.02552 -0.0328 1.0000 0.0644
-5.500 -0.4938 0.02995 0.02165 -0.0332 1.0000 0.0650
-5.250 -0.4647 0.02662 0.01775 -0.0332 1.0000 0.0636
-5.000 -0.4358 0.02391 0.01458 -0.0329 1.0000 0.0640
-4.750 -0.4074 0.02175 0.01208 -0.0324 1.0000 0.0675
-4.500 -0.3804 0.01984 0.01008 -0.0321 1.0000 0.0778
-4.250 -0.3535 0.01818 0.00839 -0.0316 1.0000 0.0949
-4.000 -0.3274 0.01663 0.00696 -0.0314 1.0000 0.1186
-3.750 -0.3008 0.01526 0.00576 -0.0312 1.0000 0.1498
-3.500 -0.2758 0.01200 0.00462 -0.0320 1.0000 0.4988
-3.250 -0.2641 0.01178 0.00511 -0.0262 1.0000 0.7328
-3.000 -0.2496 0.01189 0.00523 -0.0217 1.0000 0.7939
-2.750 -0.2377 0.01192 0.00520 -0.0168 1.0000 0.8358
-2.500 -0.2280 0.01182 0.00508 -0.0114 1.0000 0.8721
-2.250 -0.2178 0.01158 0.00480 -0.0064 1.0000 0.9080
-2.000 -0.1977 0.01120 0.00436 -0.0030 1.0000 0.9583
-1.750 -0.1019 0.01112 0.00393 -0.0158 1.0000 1.0000
-1.500 -0.0879 0.01083 0.00360 -0.0144 1.0000 1.0000
-1.250 -0.0759 0.01058 0.00332 -0.0125 1.0000 1.0000
-1.000 -0.0591 0.01041 0.00312 -0.0115 1.0000 1.0000
-0.750 -0.0355 0.01032 0.00298 -0.0117 1.0000 1.0000
-0.500 -0.0087 0.01029 0.00290 -0.0124 1.0000 1.0000
-0.250 0.0194 0.01030 0.00288 -0.0132 1.0000 1.0000
0.000 0.0479 0.01034 0.00291 -0.0140 1.0000 1.0000
0.250 0.0765 0.01040 0.00298 -0.0148 1.0000 1.0000
0.500 0.1049 0.01049 0.00312 -0.0155 1.0000 1.0000
0.750 0.1332 0.01061 0.00328 -0.0162 1.0000 1.0000
1.000 0.1613 0.01075 0.00349 -0.0168 1.0000 1.0000
1.250 0.1891 0.01091 0.00376 -0.0174 1.0000 1.0000
1.500 0.2167 0.01110 0.00407 -0.0179 1.0000 1.0000
1.750 0.2440 0.01133 0.00448 -0.0184 1.0000 1.0000
2.000 0.2710 0.01158 0.00492 -0.0189 1.0000 1.0000
2.250 0.3033 0.01185 0.00543 -0.0204 0.9963 1.0000
2.500 0.4068 0.01095 0.00491 -0.0304 0.7760 1.0000
2.750 0.4147 0.01480 0.00555 -0.0252 0.1711 1.0000
3.000 0.4400 0.01630 0.00677 -0.0247 0.1287 1.0000
3.250 0.4662 0.01781 0.00812 -0.0243 0.1024 1.0000
3.500 0.4929 0.01951 0.00965 -0.0241 0.0813 1.0000
3.750 0.5217 0.02130 0.01164 -0.0237 0.0707 1.0000
4.000 0.5501 0.02338 0.01394 -0.0233 0.0628 1.0000
4.250 0.5792 0.02585 0.01683 -0.0228 0.0610 1.0000
4.500 0.6075 0.02892 0.02041 -0.0221 0.0620 1.0000
4.750 0.6341 0.03269 0.02462 -0.0216 0.0650 1.0000
5.000 0.6613 0.03809 0.03073 -0.0206 0.0789 1.0000
5.500 0.7225 0.05282 0.04751 -0.0216 0.1647 1.0000
5.750 0.7364 0.05635 0.05130 -0.0224 0.1422 1.0000
7.000 0.7888 0.07903 0.07472 -0.0302 0.1026 1.0000
7.250 0.7956 0.08341 0.07917 -0.0319 0.0977 1.0000
7.500 0.8182 0.08839 0.08387 -0.0260 0.0942 1.0000
7.750 0.8047 0.09367 0.08943 -0.0338 0.0929 1.0000
8.000 0.7913 0.09954 0.09535 -0.0443 0.0905 1.0000
8.250 0.7868 0.10453 0.10030 -0.0493 0.0876 1.0000
8.500 0.7880 0.10886 0.10460 -0.0513 0.0847 1.0000
8.750 0.6758 0.10449 0.10043 -0.0320 0.0934 1.0000
9.000 0.6565 0.10909 0.10497 -0.0372 0.0927 1.0000
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Polar data table (+)
Polar graphs
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