PT40 (pt40-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: PT40 (pt40-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.17 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-pt40-il-1000000-n5.txt Download as CSV file: xf-pt40-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -1.1801 0.03396 0.03062 -0.0883 1.0000 0.0336
-14.500 -1.1801 0.03186 0.02838 -0.0867 1.0000 0.0338
-14.250 -1.1755 0.03018 0.02657 -0.0850 1.0000 0.0339
-14.000 -1.1676 0.02873 0.02500 -0.0832 1.0000 0.0341
-13.750 -1.1576 0.02743 0.02359 -0.0814 1.0000 0.0342
-13.500 -1.1460 0.02626 0.02230 -0.0797 1.0000 0.0344
-13.250 -1.1331 0.02518 0.02112 -0.0780 1.0000 0.0346
-13.000 -1.1190 0.02418 0.02001 -0.0763 1.0000 0.0347
-12.750 -1.1039 0.02325 0.01899 -0.0746 1.0000 0.0349
-12.500 -1.0823 0.02232 0.01795 -0.0742 0.9995 0.0351
-12.250 -1.0551 0.02144 0.01696 -0.0747 0.9984 0.0353
-12.000 -1.0273 0.02066 0.01607 -0.0753 0.9972 0.0354
-11.750 -0.9991 0.01989 0.01521 -0.0759 0.9960 0.0356
-11.500 -0.9703 0.01914 0.01441 -0.0766 0.9948 0.0359
-11.250 -0.9404 0.01853 0.01375 -0.0774 0.9938 0.0361
-11.000 -0.9113 0.01800 0.01318 -0.0779 0.9926 0.0363
-10.750 -0.8831 0.01751 0.01266 -0.0781 0.9906 0.0365
-10.500 -0.8537 0.01704 0.01216 -0.0785 0.9886 0.0367
-10.250 -0.8235 0.01658 0.01166 -0.0791 0.9868 0.0369
-10.000 -0.7926 0.01613 0.01117 -0.0798 0.9853 0.0371
-9.750 -0.7609 0.01568 0.01068 -0.0807 0.9839 0.0373
-9.500 -0.7287 0.01524 0.01019 -0.0816 0.9827 0.0376
-9.250 -0.7009 0.01482 0.00973 -0.0816 0.9793 0.0378
-9.000 -0.6720 0.01440 0.00927 -0.0818 0.9757 0.0381
-8.750 -0.6413 0.01400 0.00882 -0.0823 0.9726 0.0384
-8.500 -0.6100 0.01361 0.00839 -0.0829 0.9696 0.0387
-8.250 -0.5826 0.01326 0.00799 -0.0827 0.9629 0.0390
-8.000 -0.5514 0.01288 0.00755 -0.0832 0.9575 0.0392
-7.750 -0.5228 0.01252 0.00715 -0.0832 0.9486 0.0393
-7.500 -0.4934 0.01212 0.00672 -0.0834 0.9390 0.0397
-7.250 -0.4646 0.01182 0.00638 -0.0833 0.9265 0.0400
-7.000 -0.4367 0.01158 0.00609 -0.0831 0.9113 0.0402
-6.750 -0.4091 0.01137 0.00583 -0.0827 0.8954 0.0405
-6.500 -0.3819 0.01118 0.00557 -0.0823 0.8791 0.0408
-6.250 -0.3546 0.01100 0.00533 -0.0818 0.8637 0.0411
-6.000 -0.3274 0.01084 0.00509 -0.0814 0.8488 0.0414
-5.750 -0.3001 0.01067 0.00486 -0.0810 0.8347 0.0418
-5.500 -0.2725 0.01049 0.00462 -0.0806 0.8217 0.0421
-5.250 -0.2450 0.01034 0.00441 -0.0802 0.8093 0.0425
-5.000 -0.2173 0.01020 0.00420 -0.0799 0.7976 0.0429
-4.750 -0.1895 0.01006 0.00401 -0.0796 0.7867 0.0432
-4.500 -0.1619 0.00988 0.00378 -0.0792 0.7751 0.0436
-4.250 -0.1339 0.00971 0.00360 -0.0790 0.7656 0.0440
-4.000 -0.1059 0.00959 0.00345 -0.0787 0.7552 0.0444
-3.750 -0.0778 0.00948 0.00332 -0.0784 0.7455 0.0448
-3.500 -0.0497 0.00937 0.00318 -0.0781 0.7352 0.0452
-3.250 -0.0215 0.00927 0.00305 -0.0779 0.7262 0.0457
-3.000 0.0067 0.00917 0.00292 -0.0776 0.7161 0.0462
-2.750 0.0347 0.00909 0.00280 -0.0773 0.7034 0.0467
-2.500 0.0622 0.00904 0.00267 -0.0769 0.6837 0.0472
-2.250 0.0897 0.00901 0.00256 -0.0765 0.6609 0.0476
-2.000 0.1171 0.00896 0.00245 -0.0761 0.6384 0.0484
-1.750 0.1445 0.00896 0.00238 -0.0757 0.6133 0.0490
-1.500 0.1720 0.00898 0.00232 -0.0753 0.5891 0.0497
-1.250 0.1997 0.00898 0.00225 -0.0749 0.5697 0.0503
-1.000 0.2275 0.00898 0.00219 -0.0746 0.5510 0.0510
-0.750 0.2554 0.00899 0.00214 -0.0743 0.5334 0.0517
-0.500 0.2832 0.00900 0.00210 -0.0740 0.5156 0.0522
-0.250 0.3109 0.00901 0.00205 -0.0736 0.4964 0.0531
0.000 0.3386 0.00904 0.00204 -0.0733 0.4784 0.0540
0.250 0.3662 0.00910 0.00204 -0.0730 0.4576 0.0551
0.500 0.3936 0.00919 0.00205 -0.0726 0.4326 0.0561
0.750 0.4207 0.00930 0.00206 -0.0722 0.4066 0.0569
1.000 0.4476 0.00943 0.00208 -0.0717 0.3741 0.0580
1.250 0.4737 0.00965 0.00215 -0.0712 0.3343 0.0591
1.500 0.4999 0.00987 0.00223 -0.0707 0.2980 0.0603
1.750 0.5266 0.01005 0.00231 -0.0702 0.2724 0.0617
2.000 0.5536 0.01020 0.00239 -0.0698 0.2519 0.0631
2.250 0.5805 0.01033 0.00247 -0.0694 0.2335 0.0649
2.500 0.6074 0.01049 0.00256 -0.0690 0.2157 0.0667
2.750 0.6343 0.01065 0.00265 -0.0685 0.1995 0.0685
3.000 0.6613 0.01078 0.00275 -0.0681 0.1876 0.0712
3.250 0.6884 0.01091 0.00285 -0.0677 0.1771 0.0744
3.500 0.7156 0.01102 0.00295 -0.0674 0.1683 0.0783
4.000 0.7698 0.01125 0.00317 -0.0666 0.1541 0.0919
4.250 0.7965 0.01137 0.00330 -0.0662 0.1465 0.1119
4.500 0.8164 0.00983 0.00360 -0.0651 0.1418 0.8381
4.750 0.8490 0.00979 0.00378 -0.0657 0.1342 1.0000
5.000 0.8754 0.00998 0.00392 -0.0652 0.1275 1.0000
5.250 0.9013 0.01021 0.00408 -0.0646 0.1197 1.0000
5.500 0.9270 0.01046 0.00426 -0.0640 0.1115 1.0000
5.750 0.9528 0.01070 0.00444 -0.0634 0.1038 1.0000
6.000 0.9782 0.01097 0.00464 -0.0627 0.0953 1.0000
6.250 1.0031 0.01129 0.00487 -0.0620 0.0845 1.0000
6.500 1.0268 0.01171 0.00518 -0.0612 0.0684 1.0000
6.750 1.0497 0.01220 0.00555 -0.0602 0.0534 1.0000
7.000 1.0738 0.01258 0.00587 -0.0593 0.0467 1.0000
7.250 1.0982 0.01292 0.00617 -0.0586 0.0430 1.0000
7.500 1.1226 0.01325 0.00647 -0.0578 0.0406 1.0000
7.750 1.1471 0.01356 0.00676 -0.0571 0.0389 1.0000
8.000 1.1714 0.01387 0.00706 -0.0563 0.0374 1.0000
8.250 1.1952 0.01422 0.00739 -0.0555 0.0360 1.0000
8.500 1.2192 0.01454 0.00771 -0.0547 0.0351 1.0000
8.750 1.2430 0.01486 0.00802 -0.0539 0.0342 1.0000
9.000 1.2664 0.01520 0.00836 -0.0530 0.0335 1.0000
9.250 1.2893 0.01556 0.00872 -0.0521 0.0328 1.0000
9.500 1.3117 0.01596 0.00911 -0.0511 0.0322 1.0000
9.750 1.3337 0.01636 0.00951 -0.0500 0.0316 1.0000
10.000 1.3559 0.01672 0.00989 -0.0490 0.0313 1.0000
10.250 1.3776 0.01710 0.01028 -0.0479 0.0309 1.0000
10.500 1.3987 0.01750 0.01070 -0.0468 0.0305 1.0000
10.750 1.4190 0.01792 0.01114 -0.0455 0.0301 1.0000
11.000 1.4377 0.01836 0.01159 -0.0439 0.0297 1.0000
11.250 1.4552 0.01882 0.01207 -0.0422 0.0294 1.0000
11.500 1.4722 0.01931 0.01258 -0.0404 0.0291 1.0000
11.750 1.4885 0.01986 0.01315 -0.0387 0.0288 1.0000
12.000 1.5040 0.02045 0.01377 -0.0368 0.0285 1.0000
12.250 1.5185 0.02112 0.01447 -0.0349 0.0282 1.0000
12.500 1.5334 0.02178 0.01515 -0.0332 0.0280 1.0000
12.750 1.5485 0.02242 0.01584 -0.0315 0.0278 1.0000
13.000 1.5630 0.02312 0.01658 -0.0299 0.0276 1.0000
13.250 1.5770 0.02387 0.01737 -0.0283 0.0274 1.0000
13.500 1.5903 0.02469 0.01824 -0.0267 0.0272 1.0000
13.750 1.6029 0.02559 0.01918 -0.0251 0.0270 1.0000
14.000 1.6147 0.02656 0.02021 -0.0236 0.0268 1.0000
14.250 1.6259 0.02763 0.02132 -0.0222 0.0266 1.0000
14.500 1.6364 0.02879 0.02254 -0.0209 0.0265 1.0000
14.750 1.6461 0.03005 0.02385 -0.0196 0.0263 1.0000
15.000 1.6550 0.03143 0.02529 -0.0184 0.0261 1.0000
15.250 1.6630 0.03294 0.02686 -0.0173 0.0260 1.0000
15.500 1.6699 0.03460 0.02857 -0.0163 0.0258 1.0000
15.750 1.6757 0.03641 0.03045 -0.0155 0.0257 1.0000
16.000 1.6805 0.03839 0.03250 -0.0147 0.0256 1.0000
16.250 1.6838 0.04057 0.03475 -0.0141 0.0254 1.0000
16.500 1.6855 0.04298 0.03723 -0.0137 0.0253 1.0000
16.750 1.6857 0.04565 0.03998 -0.0134 0.0252 1.0000
17.000 1.6839 0.04865 0.04306 -0.0133 0.0251 1.0000
17.250 1.6802 0.05195 0.04645 -0.0135 0.0250 1.0000
17.500 1.6746 0.05562 0.05022 -0.0139 0.0249 1.0000
17.750 1.6668 0.05973 0.05443 -0.0147 0.0248 1.0000
18.000 1.6577 0.06413 0.05893 -0.0157 0.0247 1.0000
18.250 1.6501 0.06845 0.06337 -0.0168 0.0246 1.0000
18.500 1.6409 0.07311 0.06813 -0.0182 0.0246 1.0000
18.750 1.6290 0.07827 0.07341 -0.0198 0.0245 1.0000
19.000 1.6153 0.08375 0.07901 -0.0218 0.0245 1.0000
19.250 1.5996 0.08969 0.08506 -0.0240 0.0245 1.0000
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