Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn) Reynolds number: 500,000 Max Cl/Cd: 42.79 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cp-100-050-gn-500000.txt Download as CSV file: xf-cp-100-050-gn-500000.csv |
XFOIL Version 6.96
Calculated polar for: Cambered plate C=10% T=5% R=1.3
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 0.0171 0.10357 0.10063 -0.1252 0.9536 0.0356
-8.250 0.0308 0.10112 0.09819 -0.1271 0.9514 0.0360
-8.000 0.0471 0.09844 0.09550 -0.1298 0.9500 0.0366
-7.750 0.0644 0.09559 0.09264 -0.1329 0.9489 0.0374
-7.500 0.0823 0.09257 0.08961 -0.1374 0.9477 0.0382
-7.250 0.0990 0.08990 0.08692 -0.1442 0.9464 0.0383
-7.000 0.1206 0.08631 0.08332 -0.1460 0.9460 0.0385
-6.750 0.1433 0.08335 0.08036 -0.1490 0.9454 0.0387
-6.500 0.1500 0.08173 0.07875 -0.1484 0.9404 0.0389
-6.250 0.1636 0.07968 0.07671 -0.1497 0.9367 0.0393
-6.000 0.1843 0.07720 0.07422 -0.1530 0.9348 0.0399
-5.750 0.2068 0.07454 0.07155 -0.1571 0.9330 0.0407
-5.500 0.2304 0.07179 0.06877 -0.1633 0.9306 0.0418
-5.250 0.2197 0.07134 0.06832 -0.1626 0.9200 0.0419
-5.000 0.2398 0.06822 0.06520 -0.1651 0.9177 0.0421
-4.750 0.2623 0.06548 0.06245 -0.1669 0.9160 0.0422
-4.500 0.2866 0.06304 0.06000 -0.1698 0.9142 0.0425
-4.250 0.2860 0.06207 0.05905 -0.1669 0.9071 0.0427
-4.000 0.3025 0.06022 0.05720 -0.1684 0.9029 0.0432
-3.750 0.3262 0.05806 0.05502 -0.1718 0.8999 0.0439
-3.500 0.3541 0.05567 0.05259 -0.1767 0.8971 0.0452
-3.250 0.3655 0.05447 0.05132 -0.1813 0.8877 0.0458
-3.000 0.3874 0.05177 0.04861 -0.1835 0.8845 0.0459
-2.750 0.4088 0.04947 0.04630 -0.1840 0.8821 0.0461
-2.500 0.4261 0.04776 0.04460 -0.1841 0.8776 0.0463
-2.250 0.4389 0.04634 0.04318 -0.1832 0.8709 0.0467
-2.000 0.4674 0.04438 0.04118 -0.1860 0.8660 0.0474
-1.750 0.4906 0.04260 0.03935 -0.1876 0.8591 0.0483
-1.500 0.5385 0.03979 0.03634 -0.1973 0.8525 0.0501
-1.250 0.5619 0.03764 0.03415 -0.1979 0.8461 0.0503
-1.000 0.5720 0.03640 0.03295 -0.1953 0.8384 0.0505
-0.750 0.5954 0.03491 0.03141 -0.1958 0.8304 0.0509
-0.500 0.6150 0.03367 0.03016 -0.1954 0.8226 0.0516
-0.250 0.6400 0.03223 0.02866 -0.1962 0.8142 0.0526
0.000 0.6853 0.02955 0.02574 -0.2019 0.8067 0.0550
0.250 0.7025 0.02834 0.02447 -0.2005 0.7926 0.0552
0.500 0.7170 0.02737 0.02345 -0.1983 0.7751 0.0555
0.750 0.7275 0.02657 0.02257 -0.1950 0.7493 0.0560
1.000 0.7287 0.02613 0.02186 -0.1895 0.6990 0.0565
1.250 0.7146 0.02606 0.02146 -0.1807 0.6372 0.0570
1.500 0.6913 0.02653 0.02147 -0.1703 0.5487 0.0572
1.750 0.6640 0.02774 0.02199 -0.1598 0.4083 0.0573
2.000 0.6370 0.02964 0.02295 -0.1501 0.1754 0.0575
2.250 0.6617 0.02861 0.02126 -0.1499 0.0599 0.0603
2.500 0.6793 0.02807 0.02072 -0.1485 0.0542 0.0606
2.750 0.6983 0.02766 0.02029 -0.1473 0.0513 0.0611
3.000 0.7198 0.02721 0.01982 -0.1465 0.0500 0.0619
3.250 0.7432 0.02669 0.01923 -0.1459 0.0490 0.0637
3.500 0.7728 0.02550 0.01781 -0.1460 0.0480 0.0666
3.750 0.7907 0.02536 0.01766 -0.1444 0.0468 0.0674
4.000 0.8092 0.02523 0.01748 -0.1429 0.0459 0.0686
4.250 0.8338 0.02451 0.01648 -0.1418 0.0453 0.0731
4.500 0.8480 0.02464 0.01665 -0.1395 0.0448 0.0737
4.750 0.8644 0.02472 0.01672 -0.1376 0.0446 0.0747
5.000 0.8822 0.02476 0.01672 -0.1358 0.0443 0.0769
5.250 0.9015 0.02458 0.01637 -0.1340 0.0441 0.0814
5.500 0.9166 0.02483 0.01665 -0.1319 0.0438 0.0829
5.750 0.9346 0.02506 0.01669 -0.1298 0.0435 0.0895
6.000 0.9493 0.02524 0.01690 -0.1276 0.0433 0.0906
6.250 0.9641 0.02561 0.01730 -0.1255 0.0431 0.0926
6.500 0.9804 0.02604 0.01761 -0.1233 0.0427 0.1001
6.750 0.9957 0.02636 0.01796 -0.1213 0.0423 0.1020
7.000 1.0116 0.02689 0.01847 -0.1193 0.0419 0.1065
7.250 1.0285 0.02727 0.01880 -0.1175 0.0415 0.1136
7.500 1.0455 0.02789 0.01937 -0.1156 0.0411 0.1245
7.750 1.0635 0.02830 0.01982 -0.1141 0.0409 0.1295
8.000 1.0833 0.02879 0.02029 -0.1127 0.0407 0.1419
8.250 1.1103 0.02819 0.01914 -0.1106 0.0406 0.0734
8.500 1.1337 0.02869 0.01964 -0.1097 0.0404 0.0738
8.750 1.1596 0.02922 0.02018 -0.1090 0.0403 0.0748
9.000 1.1892 0.02975 0.02070 -0.1089 0.0403 0.0754
9.250 1.2223 0.03031 0.02127 -0.1094 0.0401 0.0759
9.500 1.2579 0.03096 0.02192 -0.1102 0.0400 0.0770
9.750 1.3101 0.03195 0.02285 -0.1139 0.0394 0.0788
10.000 1.3422 0.03276 0.02377 -0.1141 0.0398 0.0811
10.250 1.5624 0.04571 0.03836 -0.1484 0.0515 1.0000
10.500 1.5062 0.03520 0.02852 -0.1326 0.0507 1.0000
10.750 1.4998 0.03538 0.02896 -0.1260 0.0490 1.0000
11.000 1.5113 0.03697 0.03067 -0.1233 0.0479 1.0000
11.250 1.5251 0.03877 0.03253 -0.1212 0.0470 1.0000
11.500 1.5411 0.04075 0.03455 -0.1196 0.0465 1.0000
11.750 1.5606 0.04304 0.03685 -0.1188 0.0459 1.0000
13.000 1.5129 0.05525 0.05014 -0.0917 0.0422 1.0000
13.250 1.5020 0.05786 0.05291 -0.0871 0.0417 1.0000
13.500 1.4906 0.06069 0.05590 -0.0829 0.0413 1.0000
13.750 1.4783 0.06373 0.05909 -0.0789 0.0410 1.0000
14.000 1.4651 0.06697 0.06247 -0.0753 0.0407 1.0000
14.250 1.4510 0.07043 0.06607 -0.0720 0.0405 1.0000
14.500 1.4356 0.07408 0.06986 -0.0690 0.0403 1.0000
14.750 1.4195 0.07790 0.07381 -0.0664 0.0401 1.0000
15.000 1.3986 0.08209 0.07816 -0.0640 0.0400 1.0000
15.250 1.3747 0.08640 0.08263 -0.0621 0.0399 1.0000
15.500 1.3101 0.09212 0.08871 -0.0602 0.0400 1.0000
15.750 1.2658 0.09783 0.09467 -0.0603 0.0400 1.0000
16.000 1.2153 0.10529 0.10240 -0.0623 0.0401 1.0000
16.250 1.1711 0.11326 0.11059 -0.0657 0.0400 1.0000
16.500 1.0610 0.13498 0.13278 -0.0806 0.0405 1.0000
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Polar data table (+)
Polar graphs
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