PT40 (pt40-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: PT40 (pt40-il) Reynolds number: 500,000 Max Cl/Cd: 78.83 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-pt40-il-500000.txt Download as CSV file: xf-pt40-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3397 0.09183 0.08918 -0.0297 1.0000 0.0501
-8.000 -0.4119 0.08258 0.08000 -0.0372 1.0000 0.0522
-7.750 -0.4168 0.08077 0.07825 -0.0343 1.0000 0.0523
-7.500 -0.4230 0.07900 0.07652 -0.0320 1.0000 0.0524
-7.250 -0.4090 0.07657 0.07411 -0.0331 0.9986 0.0526
-7.000 -0.3843 0.07355 0.07108 -0.0368 0.9959 0.0529
-6.750 -0.3656 0.05609 0.05312 -0.0643 0.9857 0.0572
-6.500 -0.3384 0.05360 0.05068 -0.0663 0.9836 0.0574
-6.250 -0.3114 0.05152 0.04862 -0.0683 0.9803 0.0577
-6.000 -0.2845 0.04945 0.04655 -0.0704 0.9756 0.0580
-5.750 -0.2542 0.04714 0.04420 -0.0734 0.9727 0.0585
-5.500 -0.2312 0.03834 0.03473 -0.0804 0.9646 0.0630
-5.250 -0.2015 0.03665 0.03308 -0.0819 0.9599 0.0633
-5.000 -0.1729 0.03510 0.03154 -0.0832 0.9541 0.0637
-4.750 -0.1461 0.03354 0.02993 -0.0839 0.9455 0.0643
-4.500 -0.1234 0.02942 0.02509 -0.0847 0.9337 0.0690
-4.250 -0.0957 0.02762 0.02332 -0.0854 0.9252 0.0694
-4.000 -0.0758 0.02204 0.01705 -0.0847 0.9122 0.0633
-3.750 -0.0496 0.02066 0.01562 -0.0844 0.8997 0.0612
-3.500 -0.0242 0.01854 0.01319 -0.0839 0.8877 0.0603
-3.250 0.0017 0.01699 0.01135 -0.0833 0.8751 0.0603
-3.000 0.0282 0.01600 0.01015 -0.0828 0.8623 0.0611
-2.750 0.0552 0.01514 0.00906 -0.0822 0.8505 0.0618
-2.500 0.0823 0.01446 0.00819 -0.0816 0.8382 0.0623
-2.250 0.1093 0.01377 0.00734 -0.0811 0.8260 0.0629
-2.000 0.1360 0.01319 0.00670 -0.0806 0.8114 0.0636
-1.750 0.1627 0.01287 0.00634 -0.0799 0.7945 0.0644
-1.500 0.1896 0.01259 0.00602 -0.0793 0.7780 0.0653
-1.250 0.2166 0.01233 0.00569 -0.0787 0.7621 0.0665
-1.000 0.2437 0.01208 0.00533 -0.0781 0.7469 0.0677
-0.750 0.2712 0.01188 0.00503 -0.0776 0.7330 0.0685
-0.500 0.2981 0.01139 0.00454 -0.0771 0.7197 0.0696
-0.250 0.3251 0.01118 0.00431 -0.0766 0.7063 0.0707
0.000 0.3524 0.01101 0.00413 -0.0761 0.6918 0.0720
0.250 0.3798 0.01087 0.00397 -0.0756 0.6774 0.0736
0.500 0.4071 0.01081 0.00384 -0.0751 0.6622 0.0751
0.750 0.4335 0.01055 0.00356 -0.0745 0.6464 0.0767
1.000 0.4605 0.01043 0.00344 -0.0740 0.6291 0.0783
1.250 0.4874 0.01036 0.00335 -0.0734 0.6105 0.0802
1.500 0.5143 0.01036 0.00328 -0.0729 0.5915 0.0823
1.750 0.5407 0.01025 0.00315 -0.0723 0.5712 0.0848
2.000 0.5670 0.01027 0.00312 -0.0717 0.5489 0.0875
2.250 0.5932 0.01035 0.00310 -0.0710 0.5255 0.0902
2.500 0.6194 0.01035 0.00307 -0.0704 0.5008 0.0939
2.750 0.6452 0.01047 0.00310 -0.0697 0.4715 0.0986
3.000 0.6704 0.01061 0.00313 -0.0690 0.4353 0.1047
3.250 0.6941 0.01091 0.00323 -0.0680 0.3838 0.1143
3.500 0.7141 0.01031 0.00348 -0.0671 0.3272 0.5322
3.750 0.7427 0.00977 0.00381 -0.0669 0.2803 1.0000
4.000 0.7664 0.01016 0.00402 -0.0659 0.2547 1.0000
4.250 0.7909 0.01049 0.00421 -0.0651 0.2366 1.0000
4.500 0.8155 0.01083 0.00442 -0.0643 0.2220 1.0000
4.750 0.8409 0.01109 0.00461 -0.0636 0.2105 1.0000
5.000 0.8661 0.01136 0.00481 -0.0629 0.2005 1.0000
5.250 0.8909 0.01167 0.00503 -0.0621 0.1910 1.0000
5.500 0.9165 0.01191 0.00523 -0.0615 0.1833 1.0000
5.750 0.9412 0.01222 0.00547 -0.0607 0.1752 1.0000
6.000 0.9669 0.01245 0.00568 -0.0601 0.1690 1.0000
6.250 0.9917 0.01274 0.00591 -0.0594 0.1621 1.0000
6.500 1.0169 0.01300 0.00615 -0.0587 0.1559 1.0000
6.750 1.0417 0.01329 0.00639 -0.0580 0.1490 1.0000
7.000 1.0666 0.01355 0.00664 -0.0573 0.1425 1.0000
7.250 1.0908 0.01388 0.00690 -0.0565 0.1351 1.0000
7.500 1.1155 0.01415 0.00716 -0.0558 0.1270 1.0000
7.750 1.1394 0.01450 0.00744 -0.0550 0.1165 1.0000
8.000 1.1619 0.01495 0.00779 -0.0540 0.1007 1.0000
8.250 1.1814 0.01564 0.00829 -0.0526 0.0766 1.0000
8.500 1.2002 0.01638 0.00890 -0.0511 0.0634 1.0000
8.750 1.2199 0.01702 0.00948 -0.0497 0.0581 1.0000
9.000 1.2393 0.01765 0.01008 -0.0483 0.0548 1.0000
9.250 1.2590 0.01822 0.01066 -0.0469 0.0526 1.0000
9.500 1.2780 0.01880 0.01125 -0.0454 0.0508 1.0000
9.750 1.2945 0.01953 0.01196 -0.0436 0.0494 1.0000
10.000 1.3106 0.02016 0.01263 -0.0416 0.0484 1.0000
10.250 1.3264 0.02077 0.01327 -0.0397 0.0475 1.0000
10.500 1.3412 0.02144 0.01397 -0.0376 0.0466 1.0000
10.750 1.3551 0.02217 0.01473 -0.0356 0.0459 1.0000
11.000 1.3670 0.02305 0.01562 -0.0334 0.0452 1.0000
11.250 1.3759 0.02413 0.01672 -0.0309 0.0445 1.0000
11.500 1.3860 0.02518 0.01781 -0.0288 0.0440 1.0000
11.750 1.3988 0.02608 0.01878 -0.0271 0.0436 1.0000
12.000 1.4103 0.02709 0.01985 -0.0253 0.0432 1.0000
12.250 1.4210 0.02820 0.02102 -0.0236 0.0427 1.0000
12.500 1.4310 0.02940 0.02228 -0.0220 0.0422 1.0000
12.750 1.4404 0.03069 0.02362 -0.0205 0.0418 1.0000
13.000 1.4489 0.03210 0.02507 -0.0191 0.0414 1.0000
13.250 1.4565 0.03363 0.02665 -0.0178 0.0409 1.0000
13.500 1.4629 0.03533 0.02838 -0.0166 0.0406 1.0000
13.750 1.4678 0.03720 0.03029 -0.0154 0.0403 1.0000
14.000 1.4713 0.03927 0.03239 -0.0141 0.0399 1.0000
14.250 1.4769 0.04118 0.03436 -0.0131 0.0397 1.0000
14.500 1.4835 0.04303 0.03630 -0.0124 0.0395 1.0000
14.750 1.4894 0.04500 0.03836 -0.0117 0.0393 1.0000
15.000 1.4944 0.04709 0.04053 -0.0111 0.0390 1.0000
15.250 1.4987 0.04928 0.04281 -0.0106 0.0388 1.0000
15.500 1.5025 0.05157 0.04518 -0.0102 0.0386 1.0000
15.750 1.5058 0.05394 0.04764 -0.0099 0.0384 1.0000
16.000 1.5085 0.05644 0.05022 -0.0097 0.0382 1.0000
16.250 1.5105 0.05906 0.05292 -0.0096 0.0380 1.0000
16.500 1.5121 0.06177 0.05572 -0.0097 0.0377 1.0000
16.750 1.5135 0.06457 0.05860 -0.0098 0.0376 1.0000
17.000 1.5144 0.06747 0.06158 -0.0100 0.0374 1.0000
17.250 1.5147 0.07050 0.06469 -0.0104 0.0372 1.0000
17.500 1.5147 0.07360 0.06787 -0.0109 0.0370 1.0000
17.750 1.5148 0.07675 0.07109 -0.0115 0.0367 1.0000
18.000 1.5147 0.07993 0.07433 -0.0122 0.0365 1.0000
18.250 1.5153 0.08301 0.07747 -0.0128 0.0363 1.0000
18.500 1.5162 0.08599 0.08050 -0.0132 0.0361 1.0000
18.750 1.5180 0.08881 0.08337 -0.0135 0.0360 1.0000
19.000 1.5199 0.09155 0.08616 -0.0136 0.0358 1.0000
19.250 1.5185 0.09487 0.08956 -0.0141 0.0356 1.0000
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