20-32C AIRFOIL (2032c-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: 20-32C AIRFOIL (2032c-il) Reynolds number: 500,000 Max Cl/Cd: 103.72 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-2032c-il-500000.txt Download as CSV file: xf-2032c-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2463 0.10598 0.10395 -0.0187 1.0000 0.0126
-8.250 -0.2404 0.10344 0.10144 -0.0209 1.0000 0.0127
-8.000 -0.2356 0.10095 0.09898 -0.0227 1.0000 0.0127
-7.750 -0.2269 0.09632 0.09438 -0.0220 1.0000 0.0129
-7.500 -0.2203 0.09357 0.09166 -0.0217 1.0000 0.0131
-7.250 -0.2122 0.09108 0.08920 -0.0226 0.9970 0.0135
-7.000 -0.1886 0.08744 0.08556 -0.0278 0.9834 0.0142
-6.750 -0.1658 0.08378 0.08188 -0.0330 0.9651 0.0149
-6.500 -0.1454 0.08028 0.07835 -0.0376 0.9431 0.0156
-6.250 -0.1270 0.07711 0.07513 -0.0416 0.9183 0.0163
-6.000 -0.1017 0.07398 0.07191 -0.0489 0.8936 0.0168
-5.750 -0.0751 0.07050 0.06832 -0.0558 0.8709 0.0169
-5.500 -0.0495 0.06691 0.06462 -0.0610 0.8500 0.0170
-5.250 -0.0106 0.04524 0.04283 -0.0576 0.7764 0.0175
-5.000 0.0056 0.04221 0.03972 -0.0590 0.7593 0.0179
-4.750 0.0257 0.03914 0.03656 -0.0618 0.7425 0.0186
-4.500 0.0497 0.03582 0.03314 -0.0658 0.7263 0.0195
-4.250 0.0888 0.03196 0.02913 -0.0742 0.7114 0.0222
-4.000 0.1286 0.02838 0.02537 -0.0814 0.6965 0.0227
-3.750 0.1629 0.02468 0.02150 -0.0865 0.6823 0.0228
-3.500 0.1875 0.01944 0.01614 -0.0907 0.6686 0.0237
-3.250 0.2138 0.01738 0.01394 -0.0927 0.6523 0.0245
-3.000 0.2436 0.01537 0.01178 -0.0952 0.6364 0.0260
-2.750 0.2873 0.01336 0.00946 -0.0995 0.6219 0.0306
-2.500 0.3256 0.01080 0.00655 -0.1030 0.6080 0.0310
-2.250 0.3571 0.00768 0.00316 -0.1068 0.5945 0.0337
-1.000 0.5335 0.01322 0.00655 -0.1174 0.5306 0.0398
-0.750 0.5625 0.01294 0.00604 -0.1174 0.5135 0.0416
-0.500 0.5919 0.01229 0.00515 -0.1175 0.4972 0.0418
-0.250 0.6206 0.01191 0.00459 -0.1176 0.4811 0.0421
0.000 0.6496 0.01121 0.00370 -0.1178 0.4652 0.0435
0.250 0.6782 0.01087 0.00324 -0.1178 0.4495 0.0447
0.500 0.7065 0.01071 0.00299 -0.1179 0.4343 0.0463
1.000 0.7629 0.01065 0.00275 -0.1179 0.4065 0.0499
1.250 0.7910 0.01068 0.00271 -0.1179 0.3938 0.0527
1.500 0.8190 0.01072 0.00268 -0.1179 0.3819 0.0574
1.750 0.8473 0.01067 0.00274 -0.1180 0.3708 0.1209
2.000 0.8755 0.01051 0.00295 -0.1183 0.3605 0.3209
2.250 0.8975 0.00943 0.00309 -0.1173 0.3517 1.0000
2.500 0.9250 0.00963 0.00319 -0.1172 0.3437 1.0000
2.750 0.9524 0.00984 0.00331 -0.1171 0.3361 1.0000
3.000 0.9798 0.01003 0.00344 -0.1170 0.3296 1.0000
3.250 1.0071 0.01024 0.00358 -0.1169 0.3232 1.0000
3.500 1.0342 0.01047 0.00374 -0.1168 0.3174 1.0000
3.750 1.0615 0.01065 0.00390 -0.1167 0.3118 1.0000
4.000 1.0882 0.01091 0.00409 -0.1165 0.3067 1.0000
4.250 1.1153 0.01112 0.00429 -0.1164 0.3024 1.0000
4.500 1.1423 0.01131 0.00448 -0.1163 0.2981 1.0000
4.750 1.1688 0.01158 0.00470 -0.1162 0.2928 1.0000
5.000 1.1958 0.01174 0.00487 -0.1161 0.2858 1.0000
5.250 1.2221 0.01198 0.00506 -0.1159 0.2786 1.0000
5.500 1.2488 0.01217 0.00526 -0.1158 0.2728 1.0000
5.750 1.2752 0.01238 0.00548 -0.1156 0.2663 1.0000
6.000 1.3016 0.01258 0.00567 -0.1155 0.2582 1.0000
6.250 1.3276 0.01282 0.00586 -0.1153 0.2467 1.0000
6.500 1.3536 0.01305 0.00605 -0.1152 0.2307 1.0000
6.750 1.3769 0.01365 0.00638 -0.1147 0.1902 1.0000
7.000 1.3803 0.01705 0.00875 -0.1120 0.0236 1.0000
7.250 1.4031 0.01768 0.00941 -0.1113 0.0188 1.0000
7.500 1.4260 0.01826 0.01013 -0.1106 0.0166 1.0000
7.750 1.4481 0.01889 0.01088 -0.1098 0.0156 1.0000
8.000 1.4689 0.01966 0.01178 -0.1088 0.0145 1.0000
8.250 1.4881 0.02057 0.01282 -0.1077 0.0137 1.0000
8.500 1.5051 0.02165 0.01403 -0.1062 0.0130 1.0000
8.750 1.5191 0.02295 0.01547 -0.1045 0.0125 1.0000
9.000 1.5287 0.02451 0.01718 -0.1022 0.0121 1.0000
9.250 1.5310 0.02646 0.01931 -0.0990 0.0117 1.0000
9.500 1.5210 0.02874 0.02175 -0.0943 0.0114 1.0000
9.750 1.5191 0.03063 0.02377 -0.0913 0.0110 1.0000
10.000 1.5253 0.03214 0.02538 -0.0895 0.0107 1.0000
10.250 1.5234 0.03454 0.02790 -0.0876 0.0106 1.0000
10.500 1.5201 0.03739 0.03088 -0.0863 0.0105 1.0000
10.750 1.5160 0.04063 0.03424 -0.0856 0.0104 1.0000
11.000 1.5110 0.04423 0.03796 -0.0853 0.0103 1.0000
11.250 1.5055 0.04804 0.04188 -0.0852 0.0102 1.0000
11.500 1.4998 0.05195 0.04590 -0.0852 0.0102 1.0000
11.750 1.4945 0.05580 0.04984 -0.0850 0.0101 1.0000
12.000 1.4897 0.05948 0.05361 -0.0846 0.0101 1.0000
12.250 1.4865 0.06283 0.05703 -0.0839 0.0102 1.0000
12.500 1.4858 0.06558 0.05985 -0.0824 0.0103 1.0000
13.000 1.2393 0.08370 0.07882 -0.0716 0.0106 1.0000
13.250 1.2352 0.08718 0.08236 -0.0710 0.0106 1.0000
13.500 1.2344 0.09002 0.08525 -0.0701 0.0105 1.0000
13.750 1.2390 0.09163 0.08689 -0.0684 0.0105 1.0000
14.000 1.2698 0.08859 0.08375 -0.0633 0.0119 1.0000
14.750 1.3000 0.09104 0.08667 -0.0547 0.0156 1.0000
15.000 1.2817 0.09430 0.09007 -0.0545 0.0155 1.0000
15.250 1.2680 0.09772 0.09363 -0.0549 0.0152 1.0000
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Polar data table (+)
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