Cambered plate C=6% T=5% R=2.11 (cp-060-050-gn) Xfoil prediction polar at RE=1,000,000 Ncrit=1
| 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: 64.18 at α=11.5° Description: Mach=0 Ncrit=1 Source: Xfoil prediction Download polar: xf-cp-060-050-gn-1000000-n1.txt Download as CSV file: xf-cp-060-050-gn-1000000-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 = 1.000 e 6 Ncrit = 1.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.5882 0.20612 0.20376 -0.0110 0.9999 0.0187
-17.250 -0.5799 0.20321 0.20085 -0.0130 0.9998 0.0191
-8.750 -0.7614 0.01921 0.01453 -0.1268 0.8812 0.0473
-8.500 -0.7434 0.01809 0.01326 -0.1258 0.8747 0.0476
-8.250 -0.7230 0.01727 0.01232 -0.1250 0.8689 0.0479
-8.000 -0.7015 0.01661 0.01154 -0.1242 0.8634 0.0482
-7.750 -0.6791 0.01601 0.01085 -0.1235 0.8578 0.0484
-7.500 -0.6561 0.01546 0.01022 -0.1228 0.8521 0.0486
-7.250 -0.6328 0.01497 0.00965 -0.1221 0.8468 0.0489
-7.000 -0.6092 0.01451 0.00910 -0.1214 0.8415 0.0492
-6.750 -0.5849 0.01410 0.00862 -0.1208 0.8358 0.0494
-6.500 -0.5594 0.01387 0.00837 -0.1203 0.8308 0.0496
-6.250 -0.5344 0.01362 0.00807 -0.1198 0.8252 0.0498
-6.000 -0.5090 0.01337 0.00777 -0.1192 0.8198 0.0500
-5.750 -0.4834 0.01312 0.00749 -0.1187 0.8140 0.0501
-5.500 -0.4579 0.01287 0.00720 -0.1181 0.8081 0.0503
-5.250 -0.4325 0.01266 0.00694 -0.1175 0.8023 0.0505
-5.000 -0.4067 0.01240 0.00664 -0.1170 0.7967 0.0507
-4.750 -0.3812 0.01219 0.00639 -0.1164 0.7889 0.0509
-4.500 -0.3572 0.01203 0.00615 -0.1154 0.7709 0.0512
-4.250 -0.3359 0.01197 0.00592 -0.1138 0.7354 0.0514
-4.000 -0.3157 0.01197 0.00572 -0.1120 0.6889 0.0517
-3.750 -0.3137 0.01293 0.00576 -0.1067 0.4377 0.0520
-3.500 -0.3052 0.01385 0.00577 -0.1029 0.0658 0.0522
-3.250 -0.2796 0.01369 0.00555 -0.1023 0.0572 0.0525
-3.000 -0.2540 0.01352 0.00533 -0.1016 0.0542 0.0527
-2.750 -0.2282 0.01337 0.00514 -0.1009 0.0528 0.0529
-2.500 -0.2024 0.01321 0.00494 -0.1002 0.0515 0.0530
-2.250 -0.1766 0.01307 0.00476 -0.0995 0.0504 0.0532
-2.000 -0.1508 0.01294 0.00459 -0.0988 0.0495 0.0534
-1.750 -0.1249 0.01283 0.00445 -0.0981 0.0490 0.0535
-1.500 -0.0988 0.01276 0.00435 -0.0973 0.0485 0.0537
-1.250 -0.0728 0.01268 0.00425 -0.0966 0.0482 0.0539
-1.000 -0.0468 0.01262 0.00416 -0.0959 0.0478 0.0541
-0.750 -0.0209 0.01256 0.00408 -0.0951 0.0474 0.0543
-0.500 0.0051 0.01250 0.00400 -0.0943 0.0470 0.0546
-0.250 0.0309 0.01245 0.00393 -0.0935 0.0464 0.0550
0.000 0.0567 0.01240 0.00385 -0.0927 0.0458 0.0553
0.250 0.0825 0.01235 0.00378 -0.0918 0.0455 0.0556
0.500 0.1081 0.01230 0.00370 -0.0910 0.0452 0.0559
0.750 0.1337 0.01225 0.00364 -0.0900 0.0449 0.0561
1.000 0.1592 0.01221 0.00358 -0.0891 0.0448 0.0563
1.250 0.1846 0.01218 0.00352 -0.0882 0.0446 0.0565
1.500 0.2100 0.01216 0.00348 -0.0872 0.0444 0.0567
1.750 0.2353 0.01214 0.00344 -0.0862 0.0442 0.0569
2.000 0.2605 0.01213 0.00342 -0.0852 0.0441 0.0571
2.250 0.2857 0.01213 0.00340 -0.0842 0.0440 0.0572
2.500 0.3108 0.01213 0.00339 -0.0831 0.0439 0.0574
2.750 0.3358 0.01214 0.00339 -0.0820 0.0438 0.0575
3.000 0.3607 0.01216 0.00340 -0.0809 0.0437 0.0577
3.250 0.3856 0.01220 0.00344 -0.0798 0.0436 0.0580
3.500 0.4104 0.01224 0.00348 -0.0787 0.0435 0.0583
3.750 0.4350 0.01229 0.00352 -0.0775 0.0434 0.0585
4.000 0.4595 0.01234 0.00357 -0.0763 0.0433 0.0587
4.250 0.4838 0.01239 0.00362 -0.0750 0.0432 0.0588
4.500 0.5080 0.01245 0.00368 -0.0738 0.0431 0.0591
4.750 0.5320 0.01252 0.00375 -0.0724 0.0430 0.0593
5.000 0.5558 0.01259 0.00382 -0.0711 0.0429 0.0594
5.250 0.5795 0.01267 0.00390 -0.0697 0.0427 0.0597
5.500 0.6030 0.01275 0.00399 -0.0683 0.0424 0.0599
5.750 0.6263 0.01285 0.00408 -0.0668 0.0422 0.0602
6.000 0.6492 0.01294 0.00418 -0.0653 0.0419 0.0606
6.250 0.6713 0.01304 0.00428 -0.0636 0.0418 0.0609
6.500 0.6928 0.01313 0.00438 -0.0617 0.0416 0.0610
6.750 0.7141 0.01324 0.00450 -0.0598 0.0414 0.0613
7.000 0.7353 0.01335 0.00462 -0.0580 0.0413 0.0613
7.250 0.7566 0.01348 0.00475 -0.0561 0.0412 0.0615
7.500 0.7778 0.01361 0.00490 -0.0542 0.0410 0.0616
7.750 0.7989 0.01377 0.00506 -0.0524 0.0409 0.0618
8.000 0.8200 0.01394 0.00524 -0.0505 0.0407 0.0619
8.250 0.8412 0.01411 0.00542 -0.0487 0.0406 0.0619
8.500 0.8622 0.01430 0.00562 -0.0468 0.0405 0.0621
8.750 0.8834 0.01447 0.00579 -0.0450 0.0401 0.0622
9.000 0.9040 0.01467 0.00601 -0.0431 0.0400 0.0623
9.250 0.9247 0.01487 0.00623 -0.0412 0.0399 0.0625
9.500 0.9453 0.01508 0.00645 -0.0393 0.0397 0.0626
9.750 0.9655 0.01531 0.00670 -0.0373 0.0396 0.0629
10.000 0.9855 0.01555 0.00696 -0.0354 0.0395 0.0632
10.250 1.0053 0.01580 0.00723 -0.0334 0.0394 0.0635
10.500 1.0250 0.01605 0.00751 -0.0314 0.0394 0.0641
10.750 1.0446 0.01631 0.00779 -0.0294 0.0392 0.0645
11.000 1.0638 0.01659 0.00810 -0.0274 0.0392 0.0650
11.250 1.0828 0.01688 0.00841 -0.0254 0.0391 0.0651
11.500 1.1020 0.01717 0.00873 -0.0234 0.0390 0.0655
11.750 1.1206 0.01749 0.00907 -0.0213 0.0388 0.0658
12.000 1.1390 0.01781 0.00942 -0.0193 0.0388 0.0663
12.250 1.1574 0.01814 0.00979 -0.0172 0.0386 0.0663
12.500 1.1755 0.01849 0.01017 -0.0152 0.0385 0.0671
12.750 1.1933 0.01886 0.01056 -0.0131 0.0384 0.0675
13.000 1.2109 0.01924 0.01097 -0.0110 0.0382 0.0680
13.250 1.2285 0.01962 0.01140 -0.0090 0.0381 0.0695
13.500 1.2459 0.02002 0.01182 -0.0069 0.0379 0.0704
13.750 1.2630 0.02042 0.01226 -0.0049 0.0375 0.0714
14.250 1.2967 0.02131 0.01322 -0.0008 0.0373 0.0752
14.500 1.3132 0.02174 0.01370 0.0012 0.0369 0.0990
15.250 1.4319 0.02254 0.01611 -0.0069 0.0363 1.0000
15.500 1.4483 0.02314 0.01673 -0.0051 0.0362 1.0000
15.750 1.4643 0.02374 0.01736 -0.0032 0.0361 1.0000
16.000 1.4804 0.02436 0.01799 -0.0014 0.0360 1.0000
16.250 1.4962 0.02500 0.01866 0.0004 0.0358 1.0000
16.500 1.5113 0.02569 0.01937 0.0023 0.0358 1.0000
16.750 1.5256 0.02645 0.02016 0.0041 0.0356 1.0000
17.000 1.5399 0.02722 0.02097 0.0059 0.0355 1.0000
17.250 1.5533 0.02806 0.02185 0.0078 0.0355 1.0000
17.500 1.5667 0.02890 0.02273 0.0095 0.0354 1.0000
17.750 1.5793 0.02982 0.02369 0.0113 0.0352 1.0000
18.000 1.5920 0.03073 0.02464 0.0130 0.0350 1.0000
18.250 1.6044 0.03169 0.02565 0.0147 0.0348 1.0000
18.500 1.6161 0.03272 0.02671 0.0164 0.0345 1.0000
18.750 1.6275 0.03378 0.02782 0.0180 0.0344 1.0000
19.000 1.6379 0.03493 0.02903 0.0196 0.0342 1.0000
19.250 1.6483 0.03612 0.03027 0.0211 0.0341 1.0000
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Polar data table (+)
Polar graphs
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