Cambered plate C=6% T=5% R=2.11 (cp-060-050-gn) Xfoil prediction polar at RE=500,000 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: 500,000 Max Cl/Cd: 50.01 at α=11° Description: Mach=0 Ncrit=1 Source: Xfoil prediction Download polar: xf-cp-060-050-gn-500000-n1.txt Download as CSV file: xf-cp-060-050-gn-500000-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 = 0.500 e 6 Ncrit = 1.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2762 0.10122 0.09794 -0.0679 0.9513 0.0336
-7.750 -0.2676 0.09775 0.09446 -0.0703 0.9474 0.0342
-7.500 -0.2596 0.09383 0.09052 -0.0734 0.9435 0.0348
-7.250 -0.2453 0.09090 0.08759 -0.0763 0.9400 0.0351
-7.000 -0.2290 0.08795 0.08463 -0.0797 0.9368 0.0355
-6.750 -0.2137 0.08479 0.08147 -0.0832 0.9322 0.0361
-6.500 -0.1947 0.08102 0.07767 -0.0884 0.9260 0.0368
-6.250 -0.1368 0.07386 0.07020 -0.1062 0.8755 0.0379
-6.000 -0.1259 0.07083 0.06704 -0.1092 0.8474 0.0384
-5.750 -0.1204 0.06864 0.06467 -0.1099 0.8073 0.0387
-5.500 -0.1369 0.06856 0.06366 -0.1044 0.5971 0.0388
-5.250 -0.1497 0.06774 0.06203 -0.1015 0.3615 0.0394
-5.000 -0.1608 0.06629 0.05998 -0.0997 0.0890 0.0399
-4.750 -0.1721 0.06339 0.05716 -0.0997 0.1060 0.0403
-4.500 -0.1867 0.05967 0.05348 -0.1009 0.1259 0.0409
-4.250 -0.1969 0.05524 0.04897 -0.1028 0.1032 0.0416
-4.000 -0.1956 0.05209 0.04571 -0.1036 0.0678 0.0420
-3.750 -0.1878 0.04951 0.04307 -0.1041 0.0628 0.0425
-3.500 -0.1798 0.04662 0.04009 -0.1045 0.0605 0.0433
-3.250 -0.1737 0.04293 0.03626 -0.1048 0.0596 0.0442
-3.000 -0.1712 0.03793 0.03101 -0.1048 0.0579 0.0454
-2.750 -0.1564 0.03562 0.02857 -0.1042 0.0566 0.0458
-2.500 -0.1400 0.03355 0.02636 -0.1034 0.0553 0.0463
-2.250 -0.1461 0.02497 0.01701 -0.1012 0.0553 0.0494
-2.000 -0.1256 0.02368 0.01558 -0.1001 0.0541 0.0497
-1.750 -0.1054 0.02224 0.01395 -0.0990 0.0534 0.0503
-1.500 -0.0867 0.02029 0.01172 -0.0976 0.0526 0.0516
-1.250 -0.0679 0.01823 0.00933 -0.0961 0.0520 0.0528
-1.000 -0.0458 0.01714 0.00802 -0.0950 0.0514 0.0534
-0.750 -0.0211 0.01687 0.00768 -0.0941 0.0507 0.0537
-0.500 0.0037 0.01662 0.00738 -0.0932 0.0502 0.0539
-0.250 0.0285 0.01638 0.00707 -0.0923 0.0497 0.0542
0.000 0.0533 0.01615 0.00678 -0.0913 0.0493 0.0546
0.250 0.0780 0.01592 0.00649 -0.0904 0.0490 0.0551
0.500 0.1027 0.01569 0.00620 -0.0894 0.0486 0.0557
0.750 0.1273 0.01548 0.00593 -0.0884 0.0481 0.0560
1.000 0.1520 0.01530 0.00570 -0.0874 0.0478 0.0563
1.250 0.1766 0.01512 0.00548 -0.0863 0.0473 0.0567
1.500 0.2011 0.01499 0.00530 -0.0852 0.0468 0.0569
1.750 0.2256 0.01487 0.00514 -0.0841 0.0465 0.0572
2.000 0.2500 0.01477 0.00501 -0.0830 0.0463 0.0575
2.250 0.2743 0.01470 0.00491 -0.0818 0.0460 0.0577
2.500 0.2986 0.01468 0.00487 -0.0807 0.0458 0.0579
2.750 0.3229 0.01468 0.00486 -0.0795 0.0456 0.0582
3.000 0.3470 0.01468 0.00485 -0.0783 0.0454 0.0585
3.250 0.3709 0.01470 0.00485 -0.0770 0.0452 0.0589
3.500 0.3947 0.01471 0.00485 -0.0757 0.0450 0.0593
3.750 0.4183 0.01473 0.00486 -0.0744 0.0448 0.0594
4.000 0.4417 0.01476 0.00488 -0.0730 0.0447 0.0597
4.250 0.4649 0.01480 0.00491 -0.0716 0.0445 0.0599
4.500 0.4880 0.01485 0.00495 -0.0701 0.0444 0.0602
4.750 0.5108 0.01491 0.00501 -0.0686 0.0443 0.0604
5.000 0.5335 0.01499 0.00508 -0.0671 0.0441 0.0607
5.250 0.5559 0.01508 0.00516 -0.0655 0.0441 0.0611
5.500 0.5778 0.01517 0.00526 -0.0638 0.0439 0.0615
5.750 0.5989 0.01527 0.00536 -0.0620 0.0438 0.0617
6.000 0.6198 0.01538 0.00548 -0.0601 0.0436 0.0620
6.250 0.6406 0.01549 0.00560 -0.0582 0.0434 0.0621
6.500 0.6613 0.01563 0.00575 -0.0563 0.0431 0.0623
6.750 0.6819 0.01578 0.00592 -0.0543 0.0429 0.0625
7.000 0.7023 0.01595 0.00611 -0.0524 0.0427 0.0626
7.250 0.7228 0.01614 0.00631 -0.0505 0.0426 0.0628
7.500 0.7434 0.01634 0.00654 -0.0486 0.0424 0.0629
7.750 0.7638 0.01656 0.00678 -0.0467 0.0423 0.0632
8.000 0.7840 0.01679 0.00703 -0.0448 0.0421 0.0633
8.250 0.8042 0.01703 0.00729 -0.0428 0.0419 0.0635
8.500 0.8242 0.01730 0.00757 -0.0409 0.0418 0.0638
8.750 0.8442 0.01756 0.00786 -0.0390 0.0416 0.0640
9.000 0.8639 0.01784 0.00816 -0.0370 0.0415 0.0642
9.250 0.8836 0.01813 0.00847 -0.0351 0.0413 0.0646
9.500 0.9034 0.01842 0.00878 -0.0332 0.0410 0.0651
9.750 0.9229 0.01872 0.00911 -0.0313 0.0408 0.0657
10.000 0.9425 0.01901 0.00943 -0.0294 0.0405 0.0662
10.250 0.9618 0.01934 0.00978 -0.0274 0.0403 0.0665
10.500 0.9808 0.01968 0.01014 -0.0255 0.0402 0.0667
10.750 1.0000 0.02001 0.01050 -0.0236 0.0400 0.0671
11.000 1.0187 0.02037 0.01089 -0.0216 0.0399 0.0675
11.250 1.0373 0.02075 0.01130 -0.0197 0.0398 0.0677
11.500 1.0558 0.02114 0.01171 -0.0178 0.0397 0.0682
11.750 1.0736 0.02159 0.01221 -0.0158 0.0396 0.0688
12.000 1.0914 0.02204 0.01270 -0.0138 0.0395 0.0694
12.250 1.1090 0.02251 0.01321 -0.0118 0.0394 0.0698
12.500 1.1265 0.02300 0.01375 -0.0099 0.0392 0.0709
12.750 1.1436 0.02352 0.01432 -0.0079 0.0391 0.0716
13.000 1.1605 0.02407 0.01492 -0.0059 0.0389 0.0726
13.250 1.1774 0.02461 0.01551 -0.0040 0.0388 0.0761
13.500 1.1940 0.02518 0.01615 -0.0020 0.0387 0.0796
13.750 1.2102 0.02580 0.01683 -0.0001 0.0384 0.0849
14.000 1.2735 0.02560 0.01827 -0.0078 0.0380 1.0000
14.250 1.2894 0.02628 0.01898 -0.0059 0.0378 1.0000
14.500 1.3054 0.02696 0.01970 -0.0041 0.0374 1.0000
14.750 1.3208 0.02769 0.02047 -0.0022 0.0373 1.0000
15.000 1.3357 0.02845 0.02127 -0.0003 0.0371 1.0000
15.250 1.3504 0.02921 0.02208 0.0015 0.0369 1.0000
15.500 1.3645 0.03005 0.02297 0.0034 0.0368 1.0000
15.750 1.3780 0.03091 0.02388 0.0052 0.0367 1.0000
16.000 1.3915 0.03179 0.02480 0.0071 0.0365 1.0000
16.250 1.4041 0.03272 0.02578 0.0089 0.0364 1.0000
16.500 1.4162 0.03370 0.02682 0.0107 0.0363 1.0000
16.750 1.4280 0.03473 0.02791 0.0124 0.0361 1.0000
17.000 1.4390 0.03580 0.02903 0.0141 0.0360 1.0000
17.250 1.4495 0.03694 0.03024 0.0158 0.0359 1.0000
17.500 1.4593 0.03815 0.03151 0.0175 0.0358 1.0000
17.750 1.4687 0.03940 0.03283 0.0191 0.0357 1.0000
18.000 1.4765 0.04085 0.03436 0.0206 0.0356 1.0000
18.250 1.4834 0.04241 0.03601 0.0221 0.0355 1.0000
18.500 1.4882 0.04422 0.03794 0.0236 0.0351 1.0000
18.750 1.4928 0.04607 0.03989 0.0249 0.0350 1.0000
19.000 1.4955 0.04814 0.04208 0.0261 0.0347 1.0000
19.250 1.4981 0.05025 0.04429 0.0272 0.0346 1.0000
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Polar data table (+)
Polar graphs
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