PT40 (pt40-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: PT40 (pt40-il) Reynolds number: 200,000 Max Cl/Cd: 57.47 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-pt40-il-200000-n5.txt Download as CSV file: xf-pt40-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: PT40
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3460 0.10684 0.10251 -0.0265 1.0000 0.0554
-9.000 -0.3490 0.10305 0.09874 -0.0288 1.0000 0.0567
-8.750 -0.3556 0.09886 0.09457 -0.0315 1.0000 0.0570
-8.250 -0.3542 0.09140 0.08716 -0.0322 1.0000 0.0517
-8.000 -0.3508 0.08897 0.08478 -0.0317 1.0000 0.0510
-7.750 -0.3544 0.08597 0.08183 -0.0317 1.0000 0.0504
-7.500 -0.3639 0.08287 0.07879 -0.0315 1.0000 0.0498
-7.250 -0.3824 0.08001 0.07602 -0.0302 1.0000 0.0494
-7.000 -0.3964 0.07578 0.07183 -0.0322 0.9983 0.0490
-6.750 -0.3763 0.06951 0.06550 -0.0419 0.9913 0.0494
-6.500 -0.3553 0.06279 0.05866 -0.0514 0.9835 0.0500
-6.250 -0.3363 0.05563 0.05131 -0.0595 0.9741 0.0501
-6.000 -0.3159 0.04875 0.04415 -0.0660 0.9654 0.0503
-5.750 -0.2940 0.04117 0.03609 -0.0716 0.9578 0.0512
-5.500 -0.2785 0.03330 0.02743 -0.0744 0.9471 0.0524
-5.250 -0.2464 0.03184 0.02589 -0.0761 0.9423 0.0527
-5.000 -0.2210 0.03026 0.02418 -0.0764 0.9322 0.0532
-4.750 -0.1894 0.02837 0.02209 -0.0780 0.9264 0.0538
-4.500 -0.1632 0.02674 0.02025 -0.0782 0.9159 0.0547
-4.250 -0.1325 0.02445 0.01756 -0.0792 0.9090 0.0561
-4.000 -0.1058 0.02224 0.01486 -0.0792 0.8984 0.0570
-3.750 -0.0742 0.02119 0.01369 -0.0800 0.8905 0.0576
-3.500 -0.0454 0.02049 0.01295 -0.0800 0.8797 0.0581
-3.250 -0.0147 0.01980 0.01217 -0.0804 0.8703 0.0588
-3.000 0.0140 0.01916 0.01144 -0.0803 0.8591 0.0598
-2.750 0.0431 0.01843 0.01055 -0.0803 0.8488 0.0611
-2.500 0.0717 0.01766 0.00954 -0.0800 0.8376 0.0623
-2.250 0.0998 0.01706 0.00885 -0.0797 0.8266 0.0630
-2.000 0.1280 0.01662 0.00839 -0.0795 0.8157 0.0638
-1.750 0.1556 0.01623 0.00797 -0.0791 0.8044 0.0646
-1.500 0.1837 0.01587 0.00755 -0.0788 0.7936 0.0659
-1.250 0.2110 0.01553 0.00715 -0.0783 0.7817 0.0674
-1.000 0.2384 0.01519 0.00668 -0.0776 0.7671 0.0688
-0.750 0.2649 0.01487 0.00635 -0.0769 0.7485 0.0698
-0.500 0.2910 0.01463 0.00605 -0.0761 0.7270 0.0709
-0.250 0.3172 0.01440 0.00576 -0.0753 0.7066 0.0723
0.000 0.3437 0.01422 0.00550 -0.0746 0.6884 0.0741
0.250 0.3703 0.01402 0.00528 -0.0739 0.6720 0.0759
0.500 0.3967 0.01384 0.00513 -0.0733 0.6556 0.0776
0.750 0.4231 0.01370 0.00497 -0.0727 0.6383 0.0794
1.000 0.4495 0.01359 0.00482 -0.0720 0.6203 0.0814
1.250 0.4756 0.01350 0.00470 -0.0713 0.6010 0.0838
1.500 0.5016 0.01344 0.00462 -0.0706 0.5805 0.0866
1.750 0.5275 0.01343 0.00455 -0.0698 0.5587 0.0896
2.000 0.5531 0.01343 0.00450 -0.0691 0.5356 0.0925
2.250 0.5785 0.01349 0.00449 -0.0683 0.5110 0.0969
2.500 0.6035 0.01358 0.00449 -0.0674 0.4843 0.1022
2.750 0.6283 0.01370 0.00453 -0.0666 0.4536 0.1091
3.000 0.6525 0.01386 0.00459 -0.0657 0.4196 0.1208
3.250 0.6754 0.01383 0.00473 -0.0647 0.3806 0.2179
3.750 0.7259 0.01288 0.00526 -0.0633 0.3049 1.0000
4.000 0.7487 0.01331 0.00550 -0.0622 0.2805 1.0000
4.250 0.7719 0.01372 0.00575 -0.0612 0.2617 1.0000
4.500 0.7954 0.01411 0.00601 -0.0602 0.2461 1.0000
4.750 0.8189 0.01450 0.00629 -0.0592 0.2322 1.0000
5.000 0.8422 0.01491 0.00658 -0.0583 0.2194 1.0000
5.250 0.8656 0.01531 0.00687 -0.0573 0.2071 1.0000
5.500 0.8896 0.01566 0.00716 -0.0565 0.1965 1.0000
5.750 0.9129 0.01606 0.00748 -0.0556 0.1873 1.0000
6.000 0.9367 0.01641 0.00778 -0.0547 0.1781 1.0000
6.250 0.9601 0.01679 0.00811 -0.0538 0.1697 1.0000
6.500 0.9833 0.01718 0.00844 -0.0529 0.1615 1.0000
6.750 1.0069 0.01754 0.00878 -0.0520 0.1547 1.0000
7.000 1.0296 0.01795 0.00915 -0.0510 0.1478 1.0000
7.250 1.0528 0.01832 0.00952 -0.0501 0.1407 1.0000
7.500 1.0750 0.01876 0.00990 -0.0491 0.1334 1.0000
7.750 1.0974 0.01916 0.01031 -0.0481 0.1254 1.0000
8.000 1.1194 0.01960 0.01073 -0.0471 0.1172 1.0000
8.250 1.1406 0.02009 0.01118 -0.0459 0.1078 1.0000
8.500 1.1609 0.02063 0.01168 -0.0447 0.0969 1.0000
8.750 1.1799 0.02126 0.01223 -0.0433 0.0851 1.0000
9.000 1.1978 0.02197 0.01286 -0.0418 0.0743 1.0000
9.250 1.2145 0.02273 0.01356 -0.0402 0.0668 1.0000
9.500 1.2299 0.02349 0.01430 -0.0383 0.0619 1.0000
9.750 1.2439 0.02429 0.01508 -0.0363 0.0587 1.0000
10.000 1.2580 0.02508 0.01590 -0.0343 0.0562 1.0000
10.250 1.2706 0.02599 0.01682 -0.0322 0.0544 1.0000
10.500 1.2835 0.02687 0.01775 -0.0303 0.0529 1.0000
10.750 1.2957 0.02781 0.01874 -0.0284 0.0515 1.0000
11.000 1.3066 0.02886 0.01984 -0.0265 0.0504 1.0000
11.250 1.3159 0.03005 0.02106 -0.0246 0.0495 1.0000
11.500 1.3247 0.03131 0.02236 -0.0228 0.0486 1.0000
11.750 1.3343 0.03256 0.02370 -0.0212 0.0477 1.0000
12.000 1.3428 0.03394 0.02515 -0.0196 0.0469 1.0000
12.250 1.3503 0.03544 0.02672 -0.0182 0.0462 1.0000
12.500 1.3568 0.03709 0.02844 -0.0170 0.0455 1.0000
12.750 1.3620 0.03892 0.03031 -0.0158 0.0449 1.0000
13.000 1.3657 0.04094 0.03238 -0.0148 0.0444 1.0000
13.250 1.3700 0.04299 0.03450 -0.0139 0.0440 1.0000
13.500 1.3748 0.04506 0.03667 -0.0132 0.0436 1.0000
13.750 1.3788 0.04726 0.03898 -0.0126 0.0431 1.0000
14.000 1.3820 0.04961 0.04142 -0.0121 0.0427 1.0000
14.250 1.3845 0.05208 0.04398 -0.0118 0.0424 1.0000
14.500 1.3862 0.05468 0.04667 -0.0116 0.0420 1.0000
14.750 1.3875 0.05740 0.04947 -0.0115 0.0417 1.0000
15.000 1.3881 0.06024 0.05241 -0.0116 0.0414 1.0000
15.250 1.3883 0.06318 0.05543 -0.0117 0.0411 1.0000
15.500 1.3884 0.06621 0.05853 -0.0120 0.0408 1.0000
15.750 1.3884 0.06930 0.06169 -0.0124 0.0405 1.0000
16.000 1.3884 0.07242 0.06487 -0.0128 0.0403 1.0000
16.250 1.3888 0.07549 0.06799 -0.0132 0.0400 1.0000
16.500 1.3900 0.07847 0.07099 -0.0136 0.0398 1.0000
16.750 1.3868 0.08234 0.07502 -0.0147 0.0395 1.0000
17.000 1.3825 0.08645 0.07928 -0.0161 0.0393 1.0000
17.250 1.3775 0.09074 0.08372 -0.0176 0.0390 1.0000
17.500 1.3717 0.09524 0.08837 -0.0194 0.0388 1.0000
17.750 1.3653 0.09995 0.09322 -0.0213 0.0385 1.0000
18.000 1.3581 0.10487 0.09830 -0.0235 0.0383 1.0000
18.250 1.3501 0.11001 0.10358 -0.0260 0.0381 1.0000
18.500 1.3415 0.11538 0.10910 -0.0287 0.0379 1.0000
18.750 1.3319 0.12105 0.11492 -0.0317 0.0377 1.0000
19.000 1.3209 0.12715 0.12117 -0.0351 0.0375 1.0000
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