PT40 (pt40-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: PT40 (pt40-il) Reynolds number: 50,000 Max Cl/Cd: 32.06 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-pt40-il-50000.txt Download as CSV file: xf-pt40-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3309 0.10682 0.09914 -0.0181 1.0000 0.2496
-7.250 -0.3000 0.10223 0.09455 -0.0161 1.0000 0.2602
-7.000 -0.3366 0.10360 0.09613 -0.0156 1.0000 0.2686
-6.750 -0.2997 0.09763 0.09016 -0.0142 1.0000 0.2778
-6.500 -0.3173 0.09725 0.08994 -0.0124 1.0000 0.2890
-6.250 -0.3126 0.09401 0.08680 -0.0109 1.0000 0.2966
-6.000 -0.3114 0.09224 0.08514 -0.0085 1.0000 0.3090
-5.750 -0.3576 0.09284 0.08599 -0.0060 1.0000 0.3152
-5.500 -0.3216 0.08853 0.08169 -0.0030 1.0000 0.3304
-5.250 -0.3477 0.08752 0.08086 -0.0001 1.0000 0.3397
-5.000 -0.3449 0.08576 0.07920 0.0032 1.0000 0.3553
-4.750 -0.3395 0.08315 0.07669 0.0065 1.0000 0.3692
-4.500 -0.3710 0.08274 0.07644 0.0094 1.0000 0.3841
-4.250 -0.3912 0.08275 0.07655 0.0119 1.0000 0.4043
-4.000 -0.3889 0.08061 0.07451 0.0165 1.0000 0.4266
-3.750 -0.3887 0.07839 0.07241 0.0212 1.0000 0.4508
-3.500 -0.3635 0.07522 0.06932 0.0270 1.0000 0.4807
-3.250 -0.3763 0.07458 0.06879 0.0322 1.0000 0.5157
-3.000 0.1403 0.04804 0.04154 -0.0231 1.0000 1.0000
-2.750 0.1429 0.04703 0.04065 -0.0220 1.0000 1.0000
-2.500 0.1435 0.04619 0.03994 -0.0206 1.0000 1.0000
-2.250 0.1417 0.04555 0.03943 -0.0189 1.0000 1.0000
-2.000 0.0747 0.04837 0.04247 -0.0032 1.0000 0.9767
-1.750 -0.0018 0.05111 0.04543 0.0130 1.0000 0.9427
-1.500 -0.0748 0.05304 0.04756 0.0269 1.0000 0.9058
-1.250 -0.1504 0.05464 0.04933 0.0404 1.0000 0.8765
-1.000 -0.1710 0.04511 0.03686 -0.0290 1.0000 0.2472
-0.750 -0.1492 0.04298 0.03476 -0.0297 1.0000 0.2383
-0.500 -0.1188 0.04189 0.03310 -0.0318 1.0000 0.2242
-0.250 -0.0803 0.04058 0.03161 -0.0351 0.9952 0.2188
0.000 -0.0204 0.03959 0.03006 -0.0416 0.9839 0.2090
0.250 0.0327 0.03910 0.02924 -0.0468 0.9717 0.2078
0.500 0.0826 0.03855 0.02858 -0.0514 0.9586 0.2096
0.750 0.1318 0.03820 0.02808 -0.0556 0.9442 0.2104
1.000 0.1830 0.03787 0.02773 -0.0598 0.9280 0.2155
1.250 0.2394 0.03753 0.02729 -0.0641 0.9093 0.2228
1.500 0.2862 0.03706 0.02679 -0.0666 0.8879 0.2296
1.750 0.3343 0.03649 0.02633 -0.0690 0.8666 0.2438
2.000 0.3825 0.03575 0.02578 -0.0712 0.8459 0.2620
2.250 0.4311 0.03472 0.02516 -0.0732 0.8256 0.3033
2.500 0.4832 0.03189 0.02426 -0.0739 0.8071 1.0000
2.750 0.5326 0.03136 0.02331 -0.0747 0.7856 1.0000
3.000 0.5772 0.03066 0.02242 -0.0747 0.7628 1.0000
3.250 0.6212 0.02974 0.02139 -0.0743 0.7388 1.0000
3.500 0.6656 0.02857 0.02011 -0.0736 0.7135 1.0000
3.750 0.7060 0.02745 0.01888 -0.0721 0.6849 1.0000
4.000 0.7385 0.02669 0.01799 -0.0699 0.6503 1.0000
4.250 0.7682 0.02615 0.01727 -0.0674 0.6116 1.0000
4.500 0.7964 0.02590 0.01677 -0.0650 0.5714 1.0000
4.750 0.8220 0.02608 0.01666 -0.0629 0.5328 1.0000
5.000 0.8472 0.02657 0.01687 -0.0611 0.4994 1.0000
5.250 0.8716 0.02724 0.01730 -0.0596 0.4706 1.0000
5.500 0.8978 0.02800 0.01780 -0.0584 0.4470 1.0000
5.750 0.9217 0.02894 0.01859 -0.0572 0.4260 1.0000
6.000 0.9465 0.02993 0.01945 -0.0562 0.4076 1.0000
6.250 0.9683 0.03106 0.02057 -0.0549 0.3904 1.0000
6.500 0.9894 0.03233 0.02188 -0.0537 0.3748 1.0000
6.750 1.0109 0.03363 0.02318 -0.0524 0.3600 1.0000
7.000 1.0335 0.03483 0.02431 -0.0513 0.3452 1.0000
7.250 1.0553 0.03586 0.02523 -0.0499 0.3283 1.0000
7.500 1.0758 0.03684 0.02608 -0.0484 0.3104 1.0000
7.750 1.0959 0.03790 0.02701 -0.0470 0.2927 1.0000
8.000 1.1172 0.03913 0.02810 -0.0457 0.2757 1.0000
8.250 1.1324 0.04063 0.02969 -0.0438 0.2594 1.0000
8.500 1.1460 0.04242 0.03159 -0.0417 0.2434 1.0000
8.750 1.1583 0.04450 0.03377 -0.0396 0.2282 1.0000
9.000 1.1693 0.04683 0.03622 -0.0375 0.2146 1.0000
9.250 1.1857 0.04898 0.03830 -0.0360 0.2026 1.0000
9.500 1.1942 0.05141 0.04091 -0.0338 0.1928 1.0000
9.750 1.1978 0.05450 0.04421 -0.0315 0.1858 1.0000
10.000 1.1914 0.05799 0.04806 -0.0285 0.1804 1.0000
10.250 1.2206 0.05995 0.04976 -0.0285 0.1737 1.0000
10.500 1.1953 0.06462 0.05496 -0.0246 0.1721 1.0000
10.750 1.1646 0.06966 0.06039 -0.0213 0.1713 1.0000
11.000 1.1254 0.07514 0.06613 -0.0184 0.1715 1.0000
11.250 1.0798 0.08234 0.07355 -0.0180 0.1726 1.0000
11.500 1.0358 0.09133 0.08269 -0.0203 0.1738 1.0000
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Polar data table (+)
Polar graphs
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