Cambered plate C=6% T=5% R=2.11 (cp-060-050-gn) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: Cambered plate C=6% T=5% R=2.11 (cp-060-050-gn) Reynolds number: 1,000,000 Max Cl/Cd: 60.06 at α=13° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cp-060-050-gn-1000000-n5.txt Download as CSV file: xf-cp-060-050-gn-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.500 -0.2896 0.07437 0.07209 -0.0822 0.9719 0.0456
-6.000 -0.2557 0.06957 0.06729 -0.0880 0.9626 0.0459
-5.000 -0.3731 0.01564 0.01096 -0.1226 0.9181 0.0578
-4.750 -0.3488 0.01538 0.01070 -0.1218 0.9125 0.0580
-4.500 -0.3217 0.01516 0.01044 -0.1215 0.9048 0.0581
-4.250 -0.2958 0.01490 0.01015 -0.1209 0.8967 0.0582
-4.000 -0.2699 0.01469 0.00989 -0.1203 0.8871 0.0584
-3.750 -0.2441 0.01445 0.00961 -0.1197 0.8777 0.0585
-3.500 -0.2186 0.01422 0.00932 -0.1190 0.8662 0.0586
-3.250 -0.1931 0.01397 0.00903 -0.1184 0.8578 0.0588
-3.000 -0.1680 0.01374 0.00873 -0.1176 0.8457 0.0590
-2.750 -0.1433 0.01353 0.00845 -0.1166 0.8306 0.0592
-2.500 -0.1194 0.01327 0.00809 -0.1156 0.8131 0.0594
-2.250 -0.0965 0.01302 0.00772 -0.1143 0.7906 0.0597
-2.000 -0.0752 0.01284 0.00737 -0.1126 0.7605 0.0600
-1.750 -0.0567 0.01274 0.00703 -0.1103 0.7112 0.0603
-1.500 -0.0427 0.01286 0.00677 -0.1072 0.6279 0.0607
-1.250 -0.0554 0.01471 0.00707 -0.0993 0.1857 0.0609
-0.750 -0.0112 0.01455 0.00645 -0.0965 0.0664 0.0616
-0.500 0.0140 0.01434 0.00616 -0.0956 0.0634 0.0619
-0.250 0.0392 0.01418 0.00593 -0.0947 0.0614 0.0621
0.000 0.0643 0.01400 0.00569 -0.0938 0.0598 0.0623
0.250 0.0892 0.01378 0.00544 -0.0928 0.0589 0.0626
0.500 0.1145 0.01366 0.00531 -0.0919 0.0580 0.0628
0.750 0.1398 0.01357 0.00520 -0.0910 0.0573 0.0630
1.000 0.1651 0.01350 0.00512 -0.0900 0.0566 0.0632
1.250 0.1904 0.01346 0.00506 -0.0891 0.0560 0.0635
1.500 0.2155 0.01341 0.00500 -0.0881 0.0555 0.0637
1.750 0.2405 0.01340 0.00496 -0.0870 0.0550 0.0640
2.000 0.2653 0.01338 0.00493 -0.0860 0.0545 0.0644
2.250 0.2897 0.01338 0.00491 -0.0848 0.0539 0.0647
2.500 0.3144 0.01335 0.00485 -0.0837 0.0537 0.0650
2.750 0.3389 0.01331 0.00480 -0.0825 0.0535 0.0654
3.000 0.3634 0.01328 0.00475 -0.0813 0.0532 0.0657
3.250 0.3876 0.01328 0.00474 -0.0801 0.0530 0.0660
3.500 0.4118 0.01327 0.00472 -0.0788 0.0527 0.0663
3.750 0.4359 0.01328 0.00472 -0.0776 0.0523 0.0665
4.000 0.4598 0.01331 0.00473 -0.0762 0.0519 0.0667
4.250 0.4835 0.01335 0.00477 -0.0749 0.0516 0.0669
4.500 0.5069 0.01338 0.00479 -0.0735 0.0513 0.0671
4.750 0.5297 0.01337 0.00479 -0.0720 0.0511 0.0675
5.000 0.5527 0.01343 0.00486 -0.0704 0.0508 0.0679
5.250 0.5756 0.01351 0.00495 -0.0689 0.0506 0.0682
5.500 0.5981 0.01361 0.00505 -0.0673 0.0503 0.0685
5.750 0.6202 0.01371 0.00516 -0.0657 0.0501 0.0688
6.000 0.6416 0.01382 0.00527 -0.0639 0.0499 0.0691
6.250 0.6621 0.01393 0.00539 -0.0618 0.0497 0.0694
6.500 0.6818 0.01407 0.00553 -0.0597 0.0494 0.0697
6.750 0.7011 0.01425 0.00572 -0.0575 0.0492 0.0701
7.000 0.7193 0.01451 0.00598 -0.0551 0.0488 0.0704
7.250 0.7399 0.01465 0.00613 -0.0531 0.0487 0.0707
7.500 0.7603 0.01483 0.00632 -0.0512 0.0485 0.0711
7.750 0.7809 0.01502 0.00652 -0.0492 0.0484 0.0715
8.000 0.8014 0.01524 0.00675 -0.0473 0.0483 0.0718
8.250 0.8219 0.01545 0.00698 -0.0454 0.0481 0.0720
8.500 0.8418 0.01567 0.00722 -0.0434 0.0480 0.0724
8.750 0.8620 0.01590 0.00747 -0.0414 0.0478 0.0729
9.000 0.8819 0.01617 0.00776 -0.0394 0.0476 0.0732
9.250 0.9020 0.01642 0.00804 -0.0375 0.0474 0.0737
9.500 0.9218 0.01671 0.00835 -0.0355 0.0473 0.0742
9.750 0.9415 0.01700 0.00867 -0.0335 0.0471 0.0748
10.000 0.9614 0.01728 0.00897 -0.0316 0.0468 0.0753
10.250 0.9811 0.01760 0.00931 -0.0297 0.0467 0.0759
10.500 1.0005 0.01793 0.00966 -0.0277 0.0465 0.0766
10.750 1.0200 0.01823 0.00998 -0.0258 0.0463 0.0773
11.000 1.0392 0.01855 0.01033 -0.0238 0.0461 0.0782
11.250 1.0585 0.01888 0.01068 -0.0219 0.0459 0.0792
11.500 1.0776 0.01920 0.01102 -0.0200 0.0457 0.0813
11.750 1.0963 0.01952 0.01137 -0.0180 0.0455 0.0833
12.000 1.1148 0.01988 0.01176 -0.0160 0.0453 0.0863
12.500 1.1512 0.02065 0.01260 -0.0120 0.0450 0.1081
13.000 1.2457 0.02074 0.01438 -0.0205 0.0445 1.0000
13.250 1.2634 0.02137 0.01502 -0.0186 0.0443 1.0000
13.500 1.2808 0.02210 0.01576 -0.0167 0.0441 1.0000
13.750 1.2985 0.02261 0.01630 -0.0148 0.0440 1.0000
14.000 1.3161 0.02315 0.01687 -0.0129 0.0439 1.0000
14.250 1.3332 0.02372 0.01747 -0.0110 0.0438 1.0000
14.500 1.3500 0.02429 0.01807 -0.0091 0.0437 1.0000
14.750 1.3665 0.02492 0.01874 -0.0072 0.0436 1.0000
15.000 1.3825 0.02556 0.01943 -0.0053 0.0434 1.0000
15.250 1.3980 0.02624 0.02015 -0.0034 0.0432 1.0000
15.500 1.4133 0.02692 0.02088 -0.0015 0.0431 1.0000
15.750 1.4281 0.02764 0.02163 0.0004 0.0429 1.0000
16.000 1.4423 0.02840 0.02244 0.0023 0.0427 1.0000
16.250 1.4561 0.02922 0.02331 0.0042 0.0425 1.0000
16.500 1.4692 0.03010 0.02424 0.0061 0.0423 1.0000
16.750 1.4819 0.03098 0.02518 0.0080 0.0422 1.0000
17.000 1.4942 0.03191 0.02615 0.0099 0.0420 1.0000
17.250 1.5055 0.03293 0.02723 0.0117 0.0419 1.0000
17.500 1.5167 0.03397 0.02833 0.0135 0.0417 1.0000
17.750 1.5270 0.03505 0.02946 0.0153 0.0416 1.0000
18.000 1.5373 0.03614 0.03059 0.0170 0.0414 1.0000
18.250 1.5466 0.03734 0.03185 0.0187 0.0413 1.0000
18.500 1.5558 0.03857 0.03314 0.0203 0.0412 1.0000
18.750 1.5638 0.03990 0.03453 0.0218 0.0411 1.0000
19.000 1.5718 0.04128 0.03596 0.0233 0.0410 1.0000
19.250 1.5787 0.04280 0.03753 0.0246 0.0409 1.0000
19.500 1.5854 0.04437 0.03916 0.0259 0.0408 1.0000
19.750 1.5919 0.04597 0.04082 0.0271 0.0407 1.0000
20.000 1.5970 0.04777 0.04268 0.0281 0.0406 1.0000
20.250 1.6027 0.04956 0.04452 0.0291 0.0405 1.0000
20.500 1.6071 0.05153 0.04656 0.0299 0.0404 1.0000
20.750 1.6113 0.05359 0.04867 0.0305 0.0403 1.0000
21.000 1.6139 0.05587 0.05102 0.0311 0.0402 1.0000
21.250 1.6164 0.05820 0.05341 0.0314 0.0401 1.0000
21.500 1.6167 0.06088 0.05616 0.0316 0.0400 1.0000
21.750 1.6152 0.06384 0.05920 0.0316 0.0399 1.0000
22.000 1.6106 0.06725 0.06270 0.0313 0.0398 1.0000
22.250 1.6051 0.07091 0.06648 0.0306 0.0397 1.0000
22.500 1.5970 0.07502 0.07072 0.0296 0.0396 1.0000
22.750 1.5876 0.07946 0.07529 0.0282 0.0395 1.0000
23.000 1.5745 0.08457 0.08055 0.0263 0.0394 1.0000
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Polar data table (+)
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