Cambered plate C=6% T=5% R=2.11 (cp-060-050-gn) Xfoil prediction polar at RE=200,000 Ncrit=1
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Airfoil: Cambered plate C=6% T=5% R=2.11 (cp-060-050-gn) Reynolds number: 200,000 Max Cl/Cd: 35.68 at α=10.5° Description: Mach=0 Ncrit=1 Source: Xfoil prediction Download polar: xf-cp-060-050-gn-200000-n1.txt Download as CSV file: xf-cp-060-050-gn-200000-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 = 0.200 e 6 Ncrit = 1.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.2483 0.10078 0.09588 -0.0610 0.9433 0.0361
-6.750 -0.2388 0.09771 0.09282 -0.0630 0.9397 0.0369
-6.250 -0.2223 0.09114 0.08624 -0.0674 0.9312 0.0382
-6.000 -0.2111 0.08841 0.08352 -0.0694 0.9266 0.0385
-5.750 -0.1983 0.08557 0.08069 -0.0719 0.9225 0.0388
-5.500 -0.1847 0.08270 0.07782 -0.0747 0.9183 0.0391
-5.250 -0.1745 0.07982 0.07495 -0.0769 0.9124 0.0397
-5.000 -0.1634 0.07670 0.07183 -0.0797 0.9064 0.0404
-4.750 -0.1523 0.07333 0.06845 -0.0831 0.9005 0.0411
-4.500 -0.1467 0.07002 0.06513 -0.0856 0.8923 0.0417
-4.250 -0.1355 0.06701 0.06212 -0.0888 0.8838 0.0420
-4.000 -0.1297 0.06413 0.05923 -0.0912 0.8709 0.0423
-3.750 -0.1198 0.06107 0.05612 -0.0944 0.8578 0.0427
-3.500 -0.1071 0.05770 0.05266 -0.0983 0.8381 0.0435
-3.250 -0.0959 0.05410 0.04891 -0.1017 0.8125 0.0443
-3.000 -0.0874 0.05049 0.04512 -0.1041 0.7898 0.0451
-2.750 -0.0757 0.04746 0.04184 -0.1055 0.7497 0.0456
-2.500 -0.0728 0.04624 0.03981 -0.1032 0.5980 0.0459
-2.250 -0.0902 0.04713 0.03916 -0.0967 0.1778 0.0460
-1.750 -0.0663 0.04319 0.03474 -0.0956 0.0680 0.0472
-1.500 -0.0516 0.04071 0.03209 -0.0953 0.0651 0.0482
-1.250 -0.0363 0.03807 0.02926 -0.0948 0.0632 0.0490
-1.000 -0.0193 0.03586 0.02687 -0.0941 0.0615 0.0495
-0.750 -0.0002 0.03440 0.02528 -0.0932 0.0595 0.0498
-0.500 0.0193 0.03290 0.02364 -0.0922 0.0580 0.0504
-0.250 0.0390 0.03129 0.02185 -0.0911 0.0567 0.0512
0.000 0.0583 0.02938 0.01971 -0.0900 0.0556 0.0523
0.250 0.0781 0.02752 0.01759 -0.0887 0.0549 0.0531
0.750 0.1209 0.02519 0.01491 -0.0862 0.0538 0.0541
1.000 0.1430 0.02426 0.01382 -0.0849 0.0533 0.0549
1.250 0.1651 0.02317 0.01253 -0.0836 0.0529 0.0560
1.500 0.1875 0.02220 0.01135 -0.0822 0.0525 0.0568
1.750 0.2103 0.02139 0.01036 -0.0809 0.0522 0.0574
2.500 0.2798 0.02036 0.00908 -0.0771 0.0511 0.0588
2.750 0.3028 0.02012 0.00876 -0.0757 0.0506 0.0595
3.000 0.3258 0.01988 0.00845 -0.0743 0.0501 0.0602
3.250 0.3486 0.01969 0.00819 -0.0729 0.0496 0.0607
3.500 0.3713 0.01954 0.00799 -0.0715 0.0491 0.0611
3.750 0.3937 0.01944 0.00783 -0.0700 0.0487 0.0614
4.000 0.4160 0.01936 0.00773 -0.0685 0.0483 0.0618
4.250 0.4381 0.01932 0.00766 -0.0669 0.0481 0.0622
4.500 0.4599 0.01938 0.00774 -0.0653 0.0478 0.0626
4.750 0.4816 0.01946 0.00782 -0.0637 0.0476 0.0629
5.000 0.5029 0.01955 0.00792 -0.0620 0.0474 0.0634
5.250 0.5238 0.01965 0.00803 -0.0602 0.0472 0.0638
5.500 0.5441 0.01976 0.00815 -0.0583 0.0470 0.0642
5.750 0.5640 0.01988 0.00828 -0.0564 0.0468 0.0644
6.000 0.5839 0.02002 0.00843 -0.0544 0.0466 0.0647
6.250 0.6036 0.02019 0.00861 -0.0525 0.0464 0.0649
6.500 0.6233 0.02038 0.00882 -0.0505 0.0462 0.0652
6.750 0.6430 0.02060 0.00904 -0.0486 0.0460 0.0655
7.000 0.6629 0.02083 0.00929 -0.0467 0.0458 0.0657
7.250 0.6829 0.02109 0.00956 -0.0448 0.0455 0.0660
7.500 0.7030 0.02137 0.00985 -0.0430 0.0452 0.0664
7.750 0.7232 0.02166 0.01015 -0.0412 0.0449 0.0670
8.000 0.7433 0.02198 0.01049 -0.0394 0.0447 0.0676
8.250 0.7635 0.02230 0.01083 -0.0376 0.0444 0.0680
8.500 0.7836 0.02264 0.01119 -0.0358 0.0442 0.0687
8.750 0.8036 0.02302 0.01158 -0.0341 0.0440 0.0691
9.000 0.8236 0.02345 0.01205 -0.0323 0.0439 0.0694
9.250 0.8439 0.02390 0.01253 -0.0306 0.0436 0.0698
9.500 0.8641 0.02437 0.01304 -0.0290 0.0435 0.0701
9.750 0.8845 0.02488 0.01358 -0.0273 0.0433 0.0706
10.000 0.9050 0.02540 0.01414 -0.0257 0.0430 0.0710
10.250 0.9255 0.02595 0.01474 -0.0242 0.0427 0.0715
10.500 0.9461 0.02652 0.01537 -0.0226 0.0425 0.0720
10.750 0.9669 0.02712 0.01603 -0.0212 0.0420 0.0728
11.000 0.9874 0.02774 0.01671 -0.0197 0.0416 0.0743
11.250 1.0077 0.02839 0.01743 -0.0181 0.0413 0.0757
11.500 1.0274 0.02904 0.01814 -0.0166 0.0410 0.0776
11.750 1.0467 0.02974 0.01891 -0.0150 0.0407 0.0794
12.000 1.0656 0.03046 0.01971 -0.0133 0.0406 0.0812
12.250 1.0837 0.03119 0.02052 -0.0116 0.0404 0.0845
12.500 1.1012 0.03196 0.02137 -0.0099 0.0402 0.0892
13.250 1.1801 0.03386 0.02505 -0.0106 0.0396 1.0000
13.500 1.1951 0.03519 0.02652 -0.0088 0.0392 1.0000
13.750 1.2087 0.03675 0.02825 -0.0069 0.0387 1.0000
14.000 1.2199 0.03834 0.03000 -0.0048 0.0381 1.0000
14.250 1.2289 0.03991 0.03172 -0.0026 0.0378 1.0000
14.500 1.2356 0.04163 0.03362 -0.0003 0.0374 1.0000
14.750 1.2402 0.04341 0.03555 0.0021 0.0371 1.0000
15.000 1.2425 0.04535 0.03766 0.0045 0.0369 1.0000
15.250 1.2426 0.04742 0.03990 0.0068 0.0367 1.0000
15.500 1.2399 0.04977 0.04243 0.0091 0.0365 1.0000
15.750 1.2348 0.05231 0.04514 0.0111 0.0363 1.0000
16.000 1.2273 0.05513 0.04815 0.0129 0.0361 1.0000
16.250 1.2158 0.05844 0.05165 0.0143 0.0360 1.0000
16.500 1.2004 0.06232 0.05574 0.0151 0.0358 1.0000
16.750 1.1521 0.07074 0.06457 0.0138 0.0354 1.0000
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Polar data table (+)
Polar graphs
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