Cambered plate C=6% T=5% R=2.11 (cp-060-050-gn) Xfoil prediction polar at RE=100,000 Ncrit=1
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Airfoil: Cambered plate C=6% T=5% R=2.11 (cp-060-050-gn) Reynolds number: 100,000 Max Cl/Cd: 27.96 at α=10° Description: Mach=0 Ncrit=1 Source: Xfoil prediction Download polar: xf-cp-060-050-gn-100000-n1.txt Download as CSV file: xf-cp-060-050-gn-100000-n1.csv |
XFOIL Version 6.96
Calculated polar for: Cambered plate C=6% T=5% R=2.11
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 1.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.750 -0.2571 0.10591 0.09922 -0.0524 0.9485 0.0403
-6.500 -0.2498 0.10315 0.09647 -0.0536 0.9438 0.0406
-6.250 -0.2415 0.10031 0.09366 -0.0551 0.9396 0.0409
-6.000 -0.2338 0.09724 0.09059 -0.0569 0.9353 0.0415
-5.750 -0.2272 0.09462 0.08800 -0.0579 0.9296 0.0421
-5.500 -0.2184 0.09202 0.08543 -0.0593 0.9246 0.0426
-5.250 -0.2085 0.08924 0.08266 -0.0612 0.9200 0.0433
-5.000 -0.2021 0.08663 0.08008 -0.0623 0.9137 0.0436
-4.750 -0.1946 0.08392 0.07739 -0.0638 0.9076 0.0439
-4.500 -0.1853 0.08103 0.07451 -0.0659 0.9023 0.0442
-4.250 -0.1813 0.07831 0.07182 -0.0671 0.8948 0.0447
-4.000 -0.1782 0.07513 0.06864 -0.0691 0.8872 0.0455
-3.750 -0.1727 0.07266 0.06621 -0.0705 0.8799 0.0460
-3.500 -0.1709 0.07016 0.06373 -0.0714 0.8707 0.0465
-3.250 -0.1621 0.06715 0.06071 -0.0739 0.8639 0.0469
-3.000 -0.1578 0.06444 0.05799 -0.0751 0.8551 0.0473
-2.750 -0.1486 0.06150 0.05502 -0.0770 0.8477 0.0476
-2.500 -0.1384 0.05854 0.05202 -0.0788 0.8407 0.0480
-2.250 -0.1300 0.05543 0.04884 -0.0801 0.8325 0.0489
-2.000 -0.1157 0.05244 0.04577 -0.0818 0.8260 0.0497
-1.750 -0.1008 0.05014 0.04341 -0.0825 0.8194 0.0503
-1.500 -0.0847 0.04777 0.04095 -0.0830 0.8099 0.0508
-1.250 -0.0643 0.04528 0.03832 -0.0840 0.7960 0.0512
-1.000 -0.0389 0.04268 0.03552 -0.0856 0.7712 0.0516
-0.750 -0.0052 0.03951 0.03191 -0.0887 0.7226 0.0529
-0.500 0.0091 0.03923 0.02959 -0.0871 0.3297 0.0538
0.000 0.0398 0.03756 0.02675 -0.0846 0.0732 0.0547
0.250 0.0597 0.03608 0.02509 -0.0837 0.0698 0.0551
0.500 0.0802 0.03464 0.02347 -0.0828 0.0672 0.0555
0.750 0.1010 0.03301 0.02160 -0.0818 0.0654 0.0567
1.250 0.1443 0.03041 0.01860 -0.0796 0.0628 0.0584
1.500 0.1665 0.02952 0.01756 -0.0784 0.0615 0.0588
1.750 0.1889 0.02869 0.01656 -0.0772 0.0602 0.0592
2.000 0.2115 0.02792 0.01562 -0.0760 0.0590 0.0597
2.250 0.2345 0.02708 0.01459 -0.0748 0.0578 0.0608
2.500 0.2577 0.02613 0.01339 -0.0735 0.0569 0.0621
2.750 0.2808 0.02577 0.01295 -0.0722 0.0561 0.0626
3.000 0.3037 0.02547 0.01258 -0.0709 0.0557 0.0629
3.250 0.3266 0.02520 0.01224 -0.0696 0.0552 0.0632
3.500 0.3493 0.02497 0.01195 -0.0682 0.0548 0.0635
3.750 0.3719 0.02479 0.01172 -0.0668 0.0545 0.0640
4.000 0.3943 0.02464 0.01152 -0.0654 0.0542 0.0648
4.250 0.4165 0.02452 0.01134 -0.0639 0.0539 0.0657
4.500 0.4384 0.02443 0.01120 -0.0623 0.0536 0.0664
4.750 0.4601 0.02439 0.01114 -0.0607 0.0531 0.0668
5.000 0.4814 0.02440 0.01117 -0.0591 0.0526 0.0671
5.250 0.5024 0.02448 0.01126 -0.0574 0.0520 0.0673
5.500 0.5232 0.02459 0.01139 -0.0557 0.0514 0.0676
5.750 0.5437 0.02473 0.01155 -0.0539 0.0509 0.0678
6.000 0.5638 0.02489 0.01172 -0.0521 0.0503 0.0682
6.250 0.5836 0.02509 0.01194 -0.0502 0.0500 0.0687
6.500 0.6035 0.02533 0.01218 -0.0484 0.0497 0.0695
6.750 0.6235 0.02560 0.01245 -0.0466 0.0495 0.0705
7.000 0.6436 0.02590 0.01274 -0.0448 0.0493 0.0712
7.250 0.6635 0.02623 0.01306 -0.0429 0.0491 0.0718
7.500 0.6840 0.02660 0.01343 -0.0413 0.0489 0.0722
7.750 0.7052 0.02701 0.01383 -0.0397 0.0487 0.0725
8.000 0.7268 0.02749 0.01432 -0.0383 0.0485 0.0728
8.250 0.7488 0.02799 0.01484 -0.0369 0.0482 0.0732
8.500 0.7713 0.02853 0.01540 -0.0356 0.0479 0.0736
8.750 0.7941 0.02911 0.01600 -0.0344 0.0474 0.0741
9.000 0.8171 0.02972 0.01665 -0.0332 0.0470 0.0751
9.250 0.8401 0.03035 0.01731 -0.0321 0.0464 0.0765
9.500 0.8628 0.03102 0.01802 -0.0309 0.0460 0.0779
9.750 0.8854 0.03172 0.01877 -0.0297 0.0456 0.0794
10.000 0.9077 0.03246 0.01957 -0.0286 0.0454 0.0806
10.250 0.9296 0.03325 0.02040 -0.0273 0.0451 0.0818
10.500 0.9510 0.03407 0.02129 -0.0260 0.0449 0.0837
10.750 0.9715 0.03491 0.02222 -0.0246 0.0447 0.0861
11.000 0.9911 0.03578 0.02316 -0.0231 0.0445 0.0889
11.250 1.0095 0.03665 0.02412 -0.0215 0.0442 0.0928
11.500 1.0285 0.03773 0.02533 -0.0200 0.0439 0.0984
11.750 1.0485 0.03905 0.02704 -0.0189 0.0432 0.1767
12.500 1.1032 0.04272 0.03267 -0.0158 0.0417 1.0000
12.750 1.1114 0.04436 0.03446 -0.0132 0.0415 1.0000
13.000 1.1172 0.04611 0.03639 -0.0106 0.0412 1.0000
13.250 1.1205 0.04796 0.03841 -0.0078 0.0410 1.0000
13.500 1.1214 0.04995 0.04058 -0.0051 0.0408 1.0000
13.750 1.1194 0.05213 0.04294 -0.0024 0.0405 1.0000
14.000 1.1152 0.05445 0.04545 0.0002 0.0403 1.0000
14.250 1.1083 0.05702 0.04820 0.0025 0.0401 1.0000
14.500 1.0988 0.05984 0.05122 0.0045 0.0398 1.0000
14.750 1.0760 0.06435 0.05603 0.0060 0.0395 1.0000
15.000 1.0384 0.07091 0.06297 0.0060 0.0391 1.0000
15.250 0.9738 0.08220 0.07476 0.0016 0.0386 1.0000
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Polar data table (+)
Polar graphs
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