20-32C AIRFOIL (2032c-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: 20-32C AIRFOIL (2032c-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.79 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-2032c-il-1000000.txt Download as CSV file: xf-2032c-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2050 0.09104 0.08953 -0.0264 0.9274 0.0092
-7.250 -0.1979 0.08834 0.08674 -0.0277 0.8965 0.0093
-7.000 -0.1861 0.08530 0.08360 -0.0304 0.8699 0.0093
-6.250 -0.1456 0.07584 0.07388 -0.0372 0.8040 0.0099
-6.000 -0.1270 0.07311 0.07106 -0.0406 0.7831 0.0103
-5.750 -0.1060 0.07008 0.06794 -0.0446 0.7631 0.0108
-5.500 -0.0828 0.06677 0.06454 -0.0493 0.7436 0.0113
-5.250 -0.0533 0.06294 0.06061 -0.0557 0.7254 0.0123
-5.000 -0.0153 0.05859 0.05615 -0.0647 0.7088 0.0126
-4.750 0.0168 0.05463 0.05208 -0.0707 0.6924 0.0127
-4.500 0.0507 0.05039 0.04773 -0.0768 0.6762 0.0127
-4.250 0.0780 0.04604 0.04327 -0.0816 0.6599 0.0133
-4.000 0.1061 0.04403 0.04116 -0.0844 0.6416 0.0141
-3.750 0.1530 0.04026 0.03720 -0.0914 0.6247 0.0168
-3.500 0.1927 0.03636 0.03312 -0.0966 0.6091 0.0169
-3.250 0.2332 0.03207 0.02862 -0.1016 0.5943 0.0170
-3.000 0.3053 0.01399 0.00917 -0.1160 0.5879 0.0166
-2.750 0.3366 0.01245 0.00721 -0.1170 0.5717 0.0181
-2.500 0.3639 0.01297 0.00774 -0.1168 0.5537 0.0190
-2.250 0.3927 0.01272 0.00732 -0.1170 0.5362 0.0205
-2.000 0.4224 0.01219 0.00655 -0.1172 0.5192 0.0220
-1.750 0.4527 0.01111 0.00515 -0.1178 0.5035 0.0240
-1.500 0.4811 0.01105 0.00502 -0.1179 0.4877 0.0257
-1.250 0.5099 0.01082 0.00467 -0.1180 0.4723 0.0271
-1.000 0.5389 0.01049 0.00418 -0.1181 0.4570 0.0285
-0.750 0.5675 0.01037 0.00393 -0.1182 0.4416 0.0299
-0.500 0.5956 0.01056 0.00403 -0.1181 0.4267 0.0309
-0.250 0.6249 0.00996 0.00327 -0.1183 0.4134 0.0316
0.000 0.6539 0.00955 0.00274 -0.1185 0.4009 0.0323
0.250 0.6828 0.00931 0.00242 -0.1187 0.3886 0.0341
0.500 0.7113 0.00924 0.00227 -0.1188 0.3765 0.0355
0.750 0.7398 0.00922 0.00217 -0.1189 0.3647 0.0369
1.000 0.7682 0.00922 0.00211 -0.1189 0.3537 0.0380
1.250 0.7964 0.00926 0.00208 -0.1189 0.3438 0.0390
1.750 0.8528 0.00937 0.00207 -0.1190 0.3264 0.0418
2.000 0.8809 0.00943 0.00210 -0.1190 0.3187 0.0524
2.250 0.9097 0.00925 0.00226 -0.1193 0.3121 0.2240
2.500 0.9378 0.00926 0.00242 -0.1195 0.3050 0.3250
2.750 0.9613 0.00817 0.00262 -0.1189 0.3002 1.0000
3.000 0.9890 0.00833 0.00271 -0.1189 0.2945 1.0000
3.250 1.0167 0.00849 0.00282 -0.1188 0.2897 1.0000
3.500 1.0445 0.00862 0.00292 -0.1188 0.2857 1.0000
3.750 1.0721 0.00878 0.00305 -0.1188 0.2815 1.0000
4.000 1.0993 0.00899 0.00321 -0.1187 0.2767 1.0000
4.250 1.1271 0.00909 0.00331 -0.1187 0.2722 1.0000
4.500 1.1542 0.00929 0.00344 -0.1186 0.2648 1.0000
4.750 1.1815 0.00944 0.00359 -0.1186 0.2598 1.0000
5.000 1.2088 0.00959 0.00373 -0.1185 0.2550 1.0000
5.250 1.2356 0.00982 0.00390 -0.1185 0.2478 1.0000
5.500 1.2628 0.00996 0.00405 -0.1184 0.2412 1.0000
5.750 1.2894 0.01019 0.00423 -0.1183 0.2327 1.0000
6.000 1.3154 0.01048 0.00442 -0.1182 0.2142 1.0000
6.250 1.3360 0.01160 0.00505 -0.1174 0.1481 1.0000
6.500 1.3471 0.01417 0.00692 -0.1154 0.0164 1.0000
6.750 1.3720 0.01456 0.00738 -0.1150 0.0146 1.0000
7.000 1.3962 0.01505 0.00793 -0.1145 0.0126 1.0000
7.250 1.4194 0.01565 0.00862 -0.1139 0.0111 1.0000
7.500 1.4433 0.01612 0.00914 -0.1133 0.0105 1.0000
7.750 1.4663 0.01668 0.00976 -0.1127 0.0098 1.0000
8.000 1.4886 0.01729 0.01044 -0.1120 0.0092 1.0000
8.250 1.5100 0.01799 0.01119 -0.1111 0.0086 1.0000
8.500 1.5289 0.01894 0.01223 -0.1100 0.0079 1.0000
8.750 1.5411 0.02053 0.01400 -0.1079 0.0073 1.0000
9.000 1.5613 0.02115 0.01468 -0.1069 0.0070 1.0000
9.250 1.5778 0.02208 0.01569 -0.1055 0.0067 1.0000
9.500 1.5916 0.02315 0.01686 -0.1037 0.0065 1.0000
9.750 1.6029 0.02433 0.01812 -0.1016 0.0062 1.0000
10.000 1.6102 0.02558 0.01946 -0.0990 0.0060 1.0000
10.250 1.6121 0.02689 0.02087 -0.0956 0.0059 1.0000
10.500 1.6129 0.02846 0.02253 -0.0927 0.0057 1.0000
10.750 1.6135 0.03029 0.02447 -0.0903 0.0055 1.0000
11.000 1.6126 0.03251 0.02678 -0.0885 0.0054 1.0000
11.250 1.6099 0.03522 0.02959 -0.0873 0.0053 1.0000
11.500 1.6043 0.03857 0.03304 -0.0866 0.0052 1.0000
11.750 1.5959 0.04259 0.03718 -0.0865 0.0051 1.0000
12.000 1.5852 0.04715 0.04185 -0.0867 0.0050 1.0000
12.250 1.5713 0.05224 0.04705 -0.0871 0.0049 1.0000
12.500 1.5545 0.05755 0.05246 -0.0872 0.0048 1.0000
12.750 1.5367 0.06222 0.05718 -0.0856 0.0047 1.0000
13.000 1.5334 0.06601 0.06108 -0.0860 0.0047 1.0000
13.250 1.5314 0.06990 0.06508 -0.0870 0.0046 1.0000
13.500 1.5292 0.07382 0.06910 -0.0878 0.0045 1.0000
13.750 1.5260 0.07758 0.07295 -0.0881 0.0044 1.0000
14.000 1.5237 0.08098 0.07642 -0.0878 0.0043 1.0000
14.250 1.5230 0.08414 0.07965 -0.0874 0.0043 1.0000
14.500 1.5235 0.08696 0.08254 -0.0866 0.0042 1.0000
14.750 1.5245 0.08972 0.08539 -0.0858 0.0042 1.0000
15.000 1.5256 0.09255 0.08830 -0.0850 0.0041 1.0000
15.250 1.5261 0.09560 0.09146 -0.0845 0.0041 1.0000
15.500 1.5262 0.09872 0.09468 -0.0839 0.0041 1.0000
15.750 1.5244 0.10232 0.09840 -0.0840 0.0040 1.0000
16.000 1.5219 0.10615 0.10235 -0.0842 0.0040 1.0000
16.250 1.5182 0.11030 0.10663 -0.0848 0.0039 1.0000
16.500 1.5121 0.11498 0.11145 -0.0857 0.0040 1.0000
16.750 1.5036 0.12022 0.11685 -0.0873 0.0040 1.0000
17.000 1.4933 0.12591 0.12268 -0.0892 0.0041 1.0000
17.250 1.4812 0.13208 0.12901 -0.0916 0.0043 1.0000
17.750 1.4614 0.14336 0.14052 -0.0922 0.0047 1.0000
18.000 1.4485 0.15018 0.14748 -0.0969 0.0047 1.0000
18.250 1.4363 0.15715 0.15457 -0.1018 0.0047 1.0000
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Polar data table (+)
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