PT40 (pt40-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: PT40 (pt40-il) Reynolds number: 1,000,000 Max Cl/Cd: 95 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-pt40-il-1000000.txt Download as CSV file: xf-pt40-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3687 0.08808 0.08617 -0.0319 1.0000 0.0402
-8.250 -0.3671 0.08582 0.08393 -0.0317 1.0000 0.0405
-8.000 -0.5591 0.02015 0.01584 -0.0786 0.9841 0.0431
-7.750 -0.5281 0.01804 0.01345 -0.0804 0.9828 0.0436
-7.500 -0.4985 0.01728 0.01265 -0.0809 0.9790 0.0439
-7.250 -0.4655 0.01679 0.01214 -0.0820 0.9761 0.0442
-7.000 -0.4321 0.01633 0.01167 -0.0831 0.9734 0.0445
-6.750 -0.3986 0.01587 0.01118 -0.0842 0.9709 0.0448
-6.500 -0.3708 0.01553 0.01082 -0.0840 0.9640 0.0452
-6.250 -0.3402 0.01507 0.01031 -0.0844 0.9585 0.0456
-6.000 -0.3128 0.01444 0.00959 -0.0842 0.9500 0.0461
-5.750 -0.2834 0.01378 0.00882 -0.0843 0.9420 0.0466
-5.500 -0.2563 0.01324 0.00817 -0.0839 0.9299 0.0471
-5.250 -0.2286 0.01285 0.00767 -0.0836 0.9171 0.0474
-5.000 -0.2019 0.01215 0.00685 -0.0831 0.9034 0.0479
-4.750 -0.1750 0.01170 0.00635 -0.0827 0.8888 0.0483
-4.250 -0.1203 0.01127 0.00583 -0.0818 0.8598 0.0491
-4.000 -0.0928 0.01108 0.00558 -0.0814 0.8466 0.0496
-3.750 -0.0654 0.01092 0.00535 -0.0810 0.8331 0.0502
-3.500 -0.0377 0.01072 0.00511 -0.0806 0.8208 0.0508
-3.250 -0.0100 0.01051 0.00482 -0.0802 0.8093 0.0514
-3.000 0.0177 0.01033 0.00457 -0.0799 0.7973 0.0519
-2.750 0.0452 0.01007 0.00424 -0.0794 0.7840 0.0524
-2.500 0.0718 0.00974 0.00387 -0.0789 0.7677 0.0531
-2.000 0.1268 0.00951 0.00356 -0.0781 0.7349 0.0543
-1.750 0.1544 0.00940 0.00341 -0.0777 0.7192 0.0551
-1.500 0.1821 0.00930 0.00326 -0.0773 0.7045 0.0558
-1.250 0.2100 0.00924 0.00314 -0.0769 0.6908 0.0567
-1.000 0.2380 0.00913 0.00299 -0.0766 0.6774 0.0574
-0.750 0.2652 0.00891 0.00275 -0.0762 0.6639 0.0584
-0.500 0.2930 0.00885 0.00266 -0.0758 0.6486 0.0593
-0.250 0.3209 0.00879 0.00258 -0.0755 0.6326 0.0603
0.000 0.3487 0.00875 0.00250 -0.0752 0.6168 0.0613
0.250 0.3764 0.00875 0.00244 -0.0748 0.5988 0.0623
0.500 0.4037 0.00867 0.00231 -0.0744 0.5797 0.0635
0.750 0.4311 0.00867 0.00227 -0.0740 0.5611 0.0650
1.000 0.4586 0.00870 0.00225 -0.0736 0.5411 0.0664
1.250 0.4860 0.00876 0.00223 -0.0732 0.5198 0.0677
1.500 0.5133 0.00881 0.00222 -0.0728 0.4980 0.0689
1.750 0.5404 0.00883 0.00218 -0.0723 0.4752 0.0710
2.000 0.5672 0.00896 0.00222 -0.0719 0.4481 0.0729
2.250 0.5935 0.00915 0.00228 -0.0713 0.4117 0.0749
2.500 0.6185 0.00942 0.00234 -0.0706 0.3599 0.0775
2.750 0.6427 0.00982 0.00249 -0.0698 0.3033 0.0802
3.000 0.6681 0.01011 0.00263 -0.0691 0.2676 0.0830
3.250 0.6940 0.01033 0.00275 -0.0685 0.2418 0.0884
3.500 0.7204 0.01050 0.00286 -0.0681 0.2233 0.0959
3.750 0.7472 0.01059 0.00297 -0.0676 0.2105 0.1177
4.000 0.7744 0.00878 0.00330 -0.0679 0.1995 0.9987
4.250 0.8009 0.00901 0.00343 -0.0674 0.1886 1.0000
4.500 0.8272 0.00919 0.00355 -0.0668 0.1807 1.0000
4.750 0.8533 0.00940 0.00370 -0.0662 0.1724 1.0000
5.000 0.8795 0.00960 0.00383 -0.0657 0.1649 1.0000
5.250 0.9057 0.00981 0.00399 -0.0651 0.1573 1.0000
5.500 0.9318 0.01003 0.00415 -0.0646 0.1502 1.0000
5.750 0.9580 0.01024 0.00431 -0.0640 0.1443 1.0000
6.000 0.9840 0.01045 0.00448 -0.0635 0.1381 1.0000
6.250 1.0100 0.01068 0.00467 -0.0629 0.1320 1.0000
6.500 1.0356 0.01093 0.00486 -0.0623 0.1249 1.0000
6.750 1.0612 0.01117 0.00506 -0.0617 0.1176 1.0000
7.000 1.0862 0.01146 0.00529 -0.0611 0.1083 1.0000
7.250 1.1100 0.01186 0.00557 -0.0602 0.0942 1.0000
7.500 1.1311 0.01248 0.00601 -0.0590 0.0688 1.0000
7.750 1.1519 0.01313 0.00652 -0.0577 0.0529 1.0000
8.000 1.1747 0.01359 0.00693 -0.0567 0.0479 1.0000
8.250 1.1976 0.01403 0.00733 -0.0557 0.0450 1.0000
8.500 1.2210 0.01441 0.00771 -0.0548 0.0433 1.0000
8.750 1.2442 0.01479 0.00808 -0.0539 0.0419 1.0000
9.000 1.2664 0.01523 0.00852 -0.0528 0.0407 1.0000
9.250 1.2880 0.01571 0.00900 -0.0517 0.0396 1.0000
9.500 1.3107 0.01607 0.00938 -0.0507 0.0390 1.0000
9.750 1.3327 0.01647 0.00980 -0.0496 0.0383 1.0000
10.000 1.3540 0.01690 0.01024 -0.0485 0.0376 1.0000
10.250 1.3744 0.01737 0.01072 -0.0472 0.0370 1.0000
10.500 1.3934 0.01792 0.01127 -0.0457 0.0364 1.0000
10.750 1.4091 0.01857 0.01195 -0.0438 0.0358 1.0000
11.000 1.4252 0.01912 0.01253 -0.0418 0.0354 1.0000
11.250 1.4422 0.01961 0.01306 -0.0400 0.0351 1.0000
11.500 1.4585 0.02015 0.01364 -0.0382 0.0348 1.0000
11.750 1.4742 0.02074 0.01426 -0.0364 0.0345 1.0000
12.000 1.4893 0.02136 0.01492 -0.0346 0.0341 1.0000
12.250 1.5038 0.02204 0.01563 -0.0328 0.0337 1.0000
12.500 1.5174 0.02279 0.01641 -0.0309 0.0334 1.0000
12.750 1.5301 0.02362 0.01728 -0.0291 0.0331 1.0000
13.000 1.5415 0.02455 0.01825 -0.0273 0.0328 1.0000
13.250 1.5515 0.02563 0.01937 -0.0255 0.0326 1.0000
13.500 1.5592 0.02690 0.02070 -0.0236 0.0323 1.0000
13.750 1.5644 0.02844 0.02229 -0.0218 0.0320 1.0000
14.000 1.5657 0.03037 0.02430 -0.0199 0.0317 1.0000
14.250 1.5741 0.03181 0.02580 -0.0187 0.0316 1.0000
14.500 1.5826 0.03331 0.02736 -0.0176 0.0315 1.0000
14.750 1.5899 0.03496 0.02908 -0.0167 0.0314 1.0000
15.000 1.5963 0.03675 0.03094 -0.0158 0.0312 1.0000
15.250 1.6015 0.03871 0.03298 -0.0151 0.0311 1.0000
15.500 1.6056 0.04085 0.03520 -0.0145 0.0309 1.0000
15.750 1.6085 0.04317 0.03759 -0.0140 0.0308 1.0000
16.000 1.6102 0.04568 0.04018 -0.0137 0.0306 1.0000
16.250 1.6110 0.04838 0.04296 -0.0135 0.0305 1.0000
16.500 1.6105 0.05128 0.04594 -0.0135 0.0304 1.0000
16.750 1.6091 0.05439 0.04914 -0.0137 0.0302 1.0000
17.000 1.6069 0.05771 0.05254 -0.0141 0.0301 1.0000
17.250 1.6039 0.06121 0.05613 -0.0147 0.0300 1.0000
17.500 1.6001 0.06489 0.05989 -0.0154 0.0298 1.0000
17.750 1.5955 0.06878 0.06386 -0.0164 0.0297 1.0000
18.000 1.5900 0.07287 0.06804 -0.0174 0.0296 1.0000
18.250 1.5837 0.07714 0.07239 -0.0187 0.0294 1.0000
18.500 1.5763 0.08159 0.07693 -0.0201 0.0293 1.0000
18.750 1.5684 0.08619 0.08162 -0.0216 0.0292 1.0000
19.000 1.5602 0.09090 0.08640 -0.0232 0.0291 1.0000
19.250 1.5518 0.09565 0.09124 -0.0249 0.0290 1.0000
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