20-32C AIRFOIL (2032c-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: 20-32C AIRFOIL (2032c-il) Reynolds number: 100,000 Max Cl/Cd: 54.9 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-2032c-il-100000.txt Download as CSV file: xf-2032c-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: 20-32C 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
------ -------- --------- --------- -------- -------- --------
-6.750 -0.2228 0.09488 0.09094 -0.0196 1.0000 0.0464
-6.500 -0.2283 0.09353 0.08970 -0.0179 1.0000 0.0473
-6.250 -0.2377 0.09261 0.08889 -0.0157 1.0000 0.0481
-6.000 -0.2490 0.09191 0.08831 -0.0135 1.0000 0.0489
-5.750 -0.2600 0.09123 0.08773 -0.0116 1.0000 0.0497
-5.500 -0.2083 0.08847 0.08491 -0.0292 0.9901 0.0544
-5.250 -0.1599 0.08256 0.07895 -0.0422 0.9810 0.0560
-5.000 -0.1375 0.07703 0.07342 -0.0421 0.9731 0.0585
-4.750 -0.0942 0.07244 0.06878 -0.0504 0.9630 0.0633
-4.500 -0.0098 0.06760 0.06371 -0.0736 0.9525 0.0695
-4.250 0.0133 0.06241 0.05857 -0.0732 0.9439 0.0730
-4.000 0.0920 0.05827 0.05415 -0.0915 0.9320 0.0838
-3.750 0.1108 0.05388 0.04984 -0.0899 0.9207 0.0898
-3.500 0.1645 0.04981 0.04558 -0.0994 0.9074 0.1005
-3.250 0.2145 0.04655 0.04209 -0.1070 0.8922 0.1135
-3.000 0.2384 0.04354 0.03907 -0.1068 0.8756 0.1219
-2.750 0.2849 0.04100 0.03619 -0.1129 0.8583 0.1423
-2.500 0.3105 0.03830 0.03341 -0.1132 0.8410 0.1580
-2.250 0.3379 0.03600 0.03097 -0.1137 0.8219 0.1741
-1.750 0.3942 0.03216 0.02679 -0.1146 0.7833 0.2232
-1.500 0.4207 0.03040 0.02486 -0.1146 0.7631 0.2611
-0.750 0.5597 0.02209 0.01399 -0.1227 0.7068 0.1110
-0.500 0.5892 0.02076 0.01232 -0.1224 0.6861 0.1075
-0.250 0.6184 0.01981 0.01092 -0.1219 0.6670 0.1062
0.000 0.6466 0.01919 0.00997 -0.1213 0.6464 0.1089
0.250 0.6739 0.01868 0.00922 -0.1206 0.6265 0.1154
0.500 0.7011 0.01829 0.00862 -0.1200 0.6083 0.1206
0.750 0.7280 0.01796 0.00816 -0.1193 0.5889 0.1290
1.000 0.7550 0.01772 0.00783 -0.1187 0.5708 0.1490
1.250 0.7778 0.01581 0.00753 -0.1172 0.5551 1.0000
1.500 0.8048 0.01616 0.00742 -0.1167 0.5388 1.0000
1.750 0.8316 0.01654 0.00748 -0.1162 0.5235 1.0000
2.000 0.8584 0.01694 0.00762 -0.1158 0.5092 1.0000
2.250 0.8851 0.01736 0.00784 -0.1155 0.4959 1.0000
2.500 0.9117 0.01780 0.00810 -0.1152 0.4835 1.0000
2.750 0.9384 0.01825 0.00840 -0.1149 0.4722 1.0000
3.000 0.9652 0.01872 0.00864 -0.1147 0.4625 1.0000
3.250 0.9916 0.01920 0.00907 -0.1144 0.4522 1.0000
3.500 1.0181 0.01973 0.00953 -0.1142 0.4434 1.0000
3.750 1.0449 0.02023 0.00991 -0.1140 0.4356 1.0000
4.000 1.0708 0.02079 0.01050 -0.1138 0.4270 1.0000
4.250 1.0977 0.02133 0.01087 -0.1136 0.4204 1.0000
4.500 1.1232 0.02195 0.01161 -0.1134 0.4128 1.0000
4.750 1.1499 0.02253 0.01214 -0.1132 0.4070 1.0000
5.000 1.1752 0.02324 0.01294 -0.1130 0.4006 1.0000
5.250 1.2011 0.02384 0.01356 -0.1127 0.3945 1.0000
5.500 1.2271 0.02455 0.01426 -0.1126 0.3892 1.0000
5.750 1.2515 0.02531 0.01520 -0.1123 0.3833 1.0000
6.000 1.2776 0.02601 0.01594 -0.1121 0.3788 1.0000
6.250 1.3023 0.02691 0.01697 -0.1118 0.3741 1.0000
6.500 1.3259 0.02772 0.01798 -0.1114 0.3683 1.0000
6.750 1.3506 0.02794 0.01816 -0.1108 0.3592 1.0000
7.000 1.3756 0.02789 0.01806 -0.1102 0.3488 1.0000
7.250 1.3974 0.02777 0.01799 -0.1092 0.3358 1.0000
7.500 1.4188 0.02779 0.01811 -0.1082 0.3239 1.0000
7.750 1.4410 0.02796 0.01837 -0.1073 0.3140 1.0000
8.000 1.4619 0.02782 0.01831 -0.1062 0.3013 1.0000
8.250 1.4800 0.02759 0.01820 -0.1046 0.2857 1.0000
8.500 1.4987 0.02764 0.01840 -0.1032 0.2727 1.0000
8.750 1.5133 0.02757 0.01846 -0.1013 0.2514 1.0000
9.000 1.5289 0.02785 0.01890 -0.0996 0.2273 1.0000
9.250 1.5434 0.02853 0.01960 -0.0979 0.1934 1.0000
9.500 1.5403 0.03103 0.02143 -0.0949 0.1009 1.0000
9.750 1.5250 0.03474 0.02475 -0.0908 0.0510 1.0000
10.000 1.5209 0.03703 0.02715 -0.0875 0.0459 1.0000
10.250 1.5160 0.03957 0.02987 -0.0848 0.0430 1.0000
10.500 1.5086 0.04258 0.03307 -0.0827 0.0411 1.0000
10.750 1.5022 0.04577 0.03653 -0.0814 0.0398 1.0000
11.000 1.4927 0.04964 0.04066 -0.0809 0.0388 1.0000
11.250 1.4801 0.05430 0.04557 -0.0812 0.0381 1.0000
11.500 1.4647 0.05979 0.05130 -0.0823 0.0376 1.0000
11.750 1.4465 0.06611 0.05786 -0.0842 0.0374 1.0000
12.000 1.4263 0.07306 0.06504 -0.0865 0.0375 1.0000
12.250 1.4053 0.08038 0.07257 -0.0889 0.0377 1.0000
12.500 1.3847 0.08771 0.08009 -0.0914 0.0379 1.0000
12.750 1.3650 0.09494 0.08750 -0.0937 0.0379 1.0000
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Polar data table (+)
Polar graphs
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