20-32C AIRFOIL (2032c-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: 20-32C AIRFOIL (2032c-il) Reynolds number: 100,000 Max Cl/Cd: 58.2 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-2032c-il-100000-n5.txt Download as CSV file: xf-2032c-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2153 0.11228 0.10808 -0.0272 1.0000 0.0286
-7.750 -0.2204 0.11119 0.10711 -0.0261 1.0000 0.0287
-7.500 -0.2249 0.10997 0.10600 -0.0251 1.0000 0.0287
-7.250 -0.2094 0.10687 0.10293 -0.0295 0.9937 0.0287
-7.000 -0.1809 0.10253 0.09858 -0.0370 0.9836 0.0288
-6.750 -0.1513 0.09808 0.09411 -0.0443 0.9737 0.0289
-6.500 -0.1334 0.09154 0.08762 -0.0459 0.9665 0.0293
-6.250 -0.1164 0.08629 0.08237 -0.0458 0.9568 0.0300
-6.000 -0.0939 0.08217 0.07821 -0.0492 0.9446 0.0308
-5.750 -0.0693 0.07838 0.07441 -0.0537 0.9310 0.0316
-5.500 -0.0440 0.07479 0.07079 -0.0584 0.9164 0.0327
-5.250 -0.0180 0.07140 0.06735 -0.0632 0.9010 0.0347
-5.000 0.0165 0.06824 0.06411 -0.0711 0.8846 0.0388
-4.750 0.0732 0.06543 0.06108 -0.0859 0.8678 0.0405
-4.500 0.1078 0.06178 0.05729 -0.0917 0.8513 0.0406
-4.250 0.1153 0.05703 0.05256 -0.0898 0.8353 0.0419
-4.000 0.1347 0.05394 0.04941 -0.0903 0.8182 0.0435
-3.750 0.1635 0.05093 0.04626 -0.0935 0.8008 0.0459
-3.500 0.2337 0.04802 0.04284 -0.1071 0.7832 0.0539
-3.250 0.2371 0.04453 0.03947 -0.1036 0.7665 0.0578
-3.000 0.2924 0.03915 0.03363 -0.1118 0.7509 0.0395
-2.750 0.3270 0.03573 0.02996 -0.1151 0.7339 0.0380
-2.500 0.3773 0.03155 0.02516 -0.1207 0.7179 0.0405
-2.000 0.4465 0.02576 0.01860 -0.1254 0.6843 0.0435
-1.750 0.4786 0.02424 0.01667 -0.1265 0.6673 0.0486
-1.500 0.5135 0.02212 0.01389 -0.1278 0.6509 0.0498
-1.250 0.5457 0.02096 0.01206 -0.1282 0.6342 0.0541
-1.000 0.5755 0.01969 0.01041 -0.1285 0.6174 0.0555
-0.750 0.6044 0.01888 0.00927 -0.1285 0.6004 0.0567
-0.500 0.6326 0.01829 0.00843 -0.1283 0.5835 0.0585
-0.250 0.6602 0.01785 0.00776 -0.1280 0.5670 0.0609
0.000 0.6876 0.01761 0.00728 -0.1278 0.5508 0.0658
0.250 0.7148 0.01737 0.00690 -0.1275 0.5349 0.0712
0.500 0.7418 0.01720 0.00657 -0.1272 0.5194 0.0743
0.750 0.7689 0.01713 0.00630 -0.1268 0.5043 0.0789
1.000 0.7960 0.01709 0.00610 -0.1265 0.4898 0.0875
1.250 0.8232 0.01701 0.00602 -0.1263 0.4761 0.1258
1.500 0.8502 0.01691 0.00615 -0.1263 0.4630 0.2742
2.000 0.8976 0.01619 0.00624 -0.1246 0.4393 1.0000
2.250 0.9239 0.01651 0.00635 -0.1242 0.4281 1.0000
2.500 0.9502 0.01683 0.00652 -0.1240 0.4173 1.0000
2.750 0.9764 0.01718 0.00671 -0.1237 0.4080 1.0000
3.000 1.0023 0.01754 0.00692 -0.1233 0.3991 1.0000
3.250 1.0284 0.01789 0.00719 -0.1231 0.3901 1.0000
3.500 1.0540 0.01828 0.00744 -0.1227 0.3826 1.0000
3.750 1.0799 0.01864 0.00777 -0.1225 0.3744 1.0000
4.000 1.1054 0.01906 0.00809 -0.1221 0.3683 1.0000
4.250 1.1312 0.01945 0.00850 -0.1219 0.3614 1.0000
4.500 1.1565 0.01988 0.00886 -0.1215 0.3555 1.0000
4.750 1.1819 0.02031 0.00932 -0.1212 0.3496 1.0000
5.000 1.2071 0.02074 0.00977 -0.1209 0.3437 1.0000
5.250 1.2321 0.02122 0.01018 -0.1205 0.3390 1.0000
5.500 1.2573 0.02168 0.01075 -0.1202 0.3336 1.0000
5.750 1.2822 0.02216 0.01132 -0.1199 0.3290 1.0000
6.000 1.3070 0.02268 0.01183 -0.1195 0.3251 1.0000
6.250 1.3316 0.02320 0.01248 -0.1191 0.3205 1.0000
6.500 1.3560 0.02372 0.01315 -0.1187 0.3157 1.0000
6.750 1.3779 0.02408 0.01356 -0.1179 0.3056 1.0000
7.000 1.3974 0.02432 0.01386 -0.1169 0.2890 1.0000
7.250 1.4176 0.02470 0.01432 -0.1159 0.2754 1.0000
7.500 1.4374 0.02514 0.01483 -0.1149 0.2599 1.0000
7.750 1.4569 0.02565 0.01548 -0.1139 0.2439 1.0000
8.000 1.4732 0.02637 0.01613 -0.1125 0.2105 1.0000
8.250 1.4859 0.02760 0.01711 -0.1109 0.1604 1.0000
8.750 1.4699 0.03412 0.02271 -0.1036 0.0236 1.0000
9.000 1.4751 0.03566 0.02445 -0.1009 0.0217 1.0000
9.250 1.4789 0.03736 0.02639 -0.0984 0.0207 1.0000
9.500 1.4801 0.03936 0.02865 -0.0961 0.0197 1.0000
9.750 1.4784 0.04176 0.03131 -0.0940 0.0187 1.0000
10.000 1.4736 0.04467 0.03447 -0.0924 0.0178 1.0000
10.500 1.4559 0.05225 0.04264 -0.0911 0.0166 1.0000
10.750 1.4431 0.05709 0.04773 -0.0914 0.0164 1.0000
11.000 1.4283 0.06261 0.05349 -0.0925 0.0163 1.0000
11.250 1.4110 0.06888 0.06000 -0.0942 0.0162 1.0000
11.500 1.3920 0.07574 0.06709 -0.0963 0.0162 1.0000
11.750 1.3725 0.08287 0.07442 -0.0985 0.0163 1.0000
12.000 1.3532 0.09011 0.08186 -0.1008 0.0163 1.0000
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Polar data table (+)
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