Cambered plate C=6% T=5% R=2.11 (cp-060-050-gn) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| 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: 51.37 at α=12° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cp-060-050-gn-1000000.txt Download as CSV file: xf-cp-060-050-gn-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.750 -0.2337 0.10086 0.09881 -0.0594 0.9871 0.0504
-6.500 -0.2166 0.09800 0.09596 -0.0622 0.9854 0.0509
-6.250 -0.2328 0.08920 0.08712 -0.0722 0.9832 0.0535
-6.000 -0.2112 0.08676 0.08468 -0.0738 0.9822 0.0537
-5.750 -0.1881 0.08466 0.08259 -0.0756 0.9812 0.0538
-5.500 -0.1726 0.08220 0.08014 -0.0774 0.9783 0.0539
-5.250 -0.1562 0.08021 0.07817 -0.0786 0.9744 0.0542
-5.000 -0.1379 0.07777 0.07574 -0.0811 0.9714 0.0545
-4.750 -0.1183 0.07516 0.07313 -0.0842 0.9687 0.0550
-4.500 -0.1409 0.06333 0.06123 -0.1024 0.9587 0.0578
-4.250 -0.1126 0.06087 0.05876 -0.1058 0.9551 0.0580
-4.000 -0.0819 0.05873 0.05662 -0.1095 0.9500 0.0581
-3.750 -0.0571 0.05680 0.05468 -0.1121 0.9415 0.0583
-3.500 -0.0282 0.05462 0.05245 -0.1161 0.9292 0.0586
-3.250 -0.0056 0.05224 0.05001 -0.1194 0.9134 0.0590
-3.000 0.0108 0.05018 0.04785 -0.1209 0.8919 0.0596
-2.750 -0.0139 0.03944 0.03677 -0.1258 0.8918 0.0625
-2.500 0.0037 0.03847 0.03573 -0.1249 0.8719 0.0627
-2.250 0.0193 0.03763 0.03475 -0.1234 0.8402 0.0628
-2.000 0.0278 0.03698 0.03381 -0.1202 0.7756 0.0630
-1.750 0.0262 0.03685 0.03311 -0.1150 0.6467 0.0631
-1.500 0.0013 0.03889 0.03335 -0.1057 0.1273 0.0632
-1.250 0.0159 0.03551 0.02955 -0.1050 0.0819 0.0668
-1.000 0.0364 0.03685 0.03106 -0.1035 0.0737 0.0640
-0.750 0.0427 0.02995 0.02367 -0.1023 0.0735 0.0675
-0.500 0.0641 0.02946 0.02316 -0.1013 0.0710 0.0677
-0.250 0.0856 0.02886 0.02253 -0.1003 0.0696 0.0679
0.000 0.1072 0.02824 0.02187 -0.0992 0.0683 0.0682
0.250 0.1287 0.02756 0.02114 -0.0981 0.0673 0.0685
0.500 0.1500 0.02683 0.02034 -0.0969 0.0662 0.0691
0.750 0.1639 0.02288 0.01588 -0.0944 0.0657 0.0728
1.000 0.1864 0.02255 0.01555 -0.0932 0.0650 0.0730
1.250 0.2097 0.02226 0.01525 -0.0922 0.0646 0.0733
1.500 0.2328 0.02199 0.01497 -0.0911 0.0642 0.0737
1.750 0.2555 0.02154 0.01448 -0.0898 0.0637 0.0743
2.000 0.2781 0.02103 0.01390 -0.0885 0.0633 0.0754
2.250 0.2956 0.01798 0.01034 -0.0859 0.0629 0.0736
2.500 0.3194 0.01786 0.01020 -0.0847 0.0622 0.0741
2.750 0.3441 0.01874 0.01120 -0.0838 0.0616 0.0792
3.000 0.3670 0.01855 0.01098 -0.0825 0.0611 0.0797
3.250 0.3895 0.01836 0.01075 -0.0810 0.0607 0.0806
3.500 0.4107 0.01741 0.00959 -0.0791 0.0603 0.0797
3.750 0.4311 0.01573 0.00757 -0.0767 0.0600 0.0744
4.000 0.4516 0.01578 0.00758 -0.0748 0.0595 0.0747
4.250 0.4719 0.01593 0.00770 -0.0729 0.0592 0.0753
4.500 0.4948 0.01588 0.00762 -0.0713 0.0591 0.0759
4.750 0.5175 0.01583 0.00754 -0.0698 0.0589 0.0762
5.000 0.5400 0.01582 0.00752 -0.0682 0.0587 0.0765
5.250 0.5628 0.01584 0.00751 -0.0666 0.0583 0.0769
5.500 0.5854 0.01589 0.00755 -0.0650 0.0579 0.0772
5.750 0.6074 0.01604 0.00768 -0.0634 0.0577 0.0775
6.000 0.6290 0.01613 0.00776 -0.0616 0.0574 0.0778
6.250 0.6498 0.01607 0.00772 -0.0597 0.0571 0.0782
6.500 0.6710 0.01618 0.00784 -0.0579 0.0568 0.0788
6.750 0.6927 0.01635 0.00803 -0.0562 0.0565 0.0794
7.000 0.7147 0.01653 0.00822 -0.0546 0.0562 0.0798
7.250 0.7369 0.01673 0.00842 -0.0530 0.0559 0.0801
7.500 0.7594 0.01695 0.00865 -0.0514 0.0556 0.0805
7.750 0.7818 0.01717 0.00888 -0.0499 0.0553 0.0809
8.000 0.8051 0.01745 0.00916 -0.0485 0.0550 0.0814
8.250 0.8293 0.01778 0.00948 -0.0474 0.0547 0.0818
8.500 0.8566 0.01827 0.00995 -0.0469 0.0544 0.0824
8.750 0.8967 0.01952 0.01118 -0.0491 0.0537 0.0832
9.000 0.9176 0.01967 0.01138 -0.0472 0.0536 0.0835
9.250 0.9399 0.01990 0.01165 -0.0456 0.0533 0.0843
9.500 0.9626 0.02020 0.01199 -0.0441 0.0531 0.0850
9.750 0.9863 0.02060 0.01244 -0.0429 0.0529 0.0858
10.000 1.0098 0.02102 0.01291 -0.0416 0.0525 0.0867
10.250 1.0337 0.02150 0.01344 -0.0404 0.0522 0.0875
10.500 1.0577 0.02201 0.01400 -0.0392 0.0520 0.0886
10.750 1.0804 0.02249 0.01452 -0.0378 0.0516 0.0897
11.000 1.1039 0.02305 0.01513 -0.0366 0.0513 0.0916
11.250 1.1262 0.02357 0.01570 -0.0352 0.0510 0.0939
11.500 1.1475 0.02405 0.01622 -0.0336 0.0508 0.0980
11.750 1.1685 0.02451 0.01674 -0.0319 0.0505 0.1120
12.000 1.2282 0.02391 0.01781 -0.0389 0.0500 1.0000
12.250 1.2482 0.02443 0.01832 -0.0371 0.0498 1.0000
12.500 1.2683 0.02500 0.01888 -0.0354 0.0496 1.0000
12.750 1.2895 0.02578 0.01966 -0.0339 0.0494 1.0000
13.000 1.3142 0.02729 0.02121 -0.0334 0.0490 1.0000
13.250 1.3312 0.02898 0.02305 -0.0316 0.0486 1.0000
13.500 1.3448 0.02956 0.02371 -0.0288 0.0485 1.0000
13.750 1.3567 0.03029 0.02454 -0.0258 0.0483 1.0000
14.000 1.3661 0.03109 0.02544 -0.0225 0.0481 1.0000
14.250 1.3751 0.03217 0.02665 -0.0192 0.0478 1.0000
14.500 1.3823 0.03334 0.02795 -0.0158 0.0475 1.0000
14.750 1.3890 0.03468 0.02943 -0.0126 0.0472 1.0000
15.000 1.3946 0.03595 0.03083 -0.0093 0.0469 1.0000
15.250 1.3998 0.03710 0.03207 -0.0061 0.0466 1.0000
15.500 1.4060 0.03805 0.03309 -0.0031 0.0463 1.0000
15.750 1.4104 0.03924 0.03437 -0.0001 0.0461 1.0000
16.000 1.4164 0.04015 0.03534 0.0027 0.0459 1.0000
16.250 1.4189 0.04151 0.03679 0.0056 0.0458 1.0000
16.500 1.4219 0.04280 0.03815 0.0083 0.0456 1.0000
16.750 1.4247 0.04411 0.03952 0.0108 0.0455 1.0000
17.000 1.4282 0.04535 0.04082 0.0132 0.0454 1.0000
17.250 1.4298 0.04684 0.04238 0.0154 0.0453 1.0000
17.500 1.4296 0.04857 0.04418 0.0176 0.0452 1.0000
17.750 1.4282 0.05043 0.04612 0.0196 0.0451 1.0000
18.000 1.4261 0.05237 0.04813 0.0213 0.0450 1.0000
18.250 1.4222 0.05457 0.05042 0.0229 0.0449 1.0000
18.500 1.4203 0.05663 0.05255 0.0242 0.0448 1.0000
18.750 1.4128 0.05941 0.05542 0.0252 0.0447 1.0000
19.000 1.4045 0.06239 0.05848 0.0258 0.0446 1.0000
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Polar data table (+)
Polar graphs
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