PT40 (pt40-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: PT40 (pt40-il) Reynolds number: 50,000 Max Cl/Cd: 33.41 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-pt40-il-50000-n5.txt Download as CSV file: xf-pt40-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3193 0.10420 0.09622 -0.0238 1.0000 0.1604
-7.500 -0.3402 0.10327 0.09544 -0.0252 1.0000 0.1665
-7.250 -0.3798 0.10288 0.09524 -0.0277 1.0000 0.1679
-7.000 -0.3316 0.09721 0.08957 -0.0231 1.0000 0.1720
-6.750 -0.3264 0.09484 0.08728 -0.0216 1.0000 0.1760
-6.500 -0.3363 0.09311 0.08569 -0.0203 1.0000 0.1805
-6.250 -0.3847 0.09256 0.08530 -0.0251 1.0000 0.1866
-6.000 -0.3668 0.08878 0.08162 -0.0207 1.0000 0.1886
-5.000 -0.3854 0.06877 0.06102 -0.0317 1.0000 0.1107
-4.750 -0.3787 0.06650 0.05881 -0.0301 1.0000 0.1100
-4.500 -0.3718 0.06407 0.05638 -0.0292 1.0000 0.1090
-4.250 -0.3423 0.06031 0.05249 -0.0333 0.9936 0.1069
-4.000 -0.3095 0.05584 0.04772 -0.0386 0.9855 0.1036
-3.750 -0.2748 0.05134 0.04270 -0.0439 0.9773 0.1014
-3.500 -0.2397 0.04875 0.03993 -0.0473 0.9702 0.1025
-3.250 -0.2080 0.04627 0.03723 -0.0499 0.9612 0.1032
-3.000 -0.1732 0.04371 0.03433 -0.0528 0.9531 0.1031
-2.750 -0.1377 0.04138 0.03165 -0.0554 0.9450 0.1028
-2.500 -0.1047 0.03959 0.02963 -0.0572 0.9362 0.1037
-2.250 -0.0674 0.03798 0.02779 -0.0596 0.9285 0.1057
-2.000 -0.0352 0.03657 0.02610 -0.0609 0.9190 0.1073
-1.750 0.0039 0.03509 0.02433 -0.0631 0.9116 0.1082
-1.500 0.0361 0.03396 0.02293 -0.0640 0.9017 0.1092
-1.250 0.0753 0.03283 0.02161 -0.0660 0.8943 0.1117
-1.000 0.1071 0.03198 0.02079 -0.0669 0.8843 0.1142
-0.750 0.1456 0.03107 0.01980 -0.0686 0.8765 0.1165
-0.500 0.1794 0.03034 0.01897 -0.0693 0.8669 0.1186
-0.250 0.2154 0.02970 0.01818 -0.0702 0.8577 0.1221
0.000 0.2484 0.02902 0.01760 -0.0708 0.8480 0.1256
0.250 0.2826 0.02843 0.01704 -0.0713 0.8379 0.1291
0.500 0.3159 0.02798 0.01655 -0.0715 0.8273 0.1334
0.750 0.3512 0.02738 0.01600 -0.0721 0.8163 0.1389
1.000 0.3819 0.02683 0.01550 -0.0716 0.8005 0.1447
1.250 0.4151 0.02617 0.01481 -0.0711 0.7834 0.1517
1.500 0.4472 0.02542 0.01415 -0.0706 0.7653 0.1620
1.750 0.4787 0.02477 0.01357 -0.0699 0.7476 0.1748
2.000 0.5084 0.02418 0.01314 -0.0692 0.7302 0.1998
2.500 0.5678 0.02162 0.01275 -0.0672 0.6914 1.0000
2.750 0.5937 0.02166 0.01257 -0.0658 0.6707 1.0000
3.000 0.6194 0.02170 0.01243 -0.0644 0.6488 1.0000
3.250 0.6446 0.02177 0.01232 -0.0630 0.6254 1.0000
3.500 0.6674 0.02193 0.01237 -0.0613 0.5988 1.0000
3.750 0.6914 0.02207 0.01234 -0.0597 0.5708 1.0000
4.000 0.7148 0.02226 0.01235 -0.0581 0.5408 1.0000
4.250 0.7374 0.02253 0.01243 -0.0564 0.5084 1.0000
4.500 0.7588 0.02291 0.01261 -0.0547 0.4736 1.0000
4.750 0.7799 0.02338 0.01285 -0.0530 0.4394 1.0000
5.000 0.8005 0.02396 0.01315 -0.0513 0.4073 1.0000
5.250 0.8210 0.02462 0.01362 -0.0498 0.3783 1.0000
5.500 0.8418 0.02534 0.01412 -0.0484 0.3547 1.0000
5.750 0.8629 0.02611 0.01470 -0.0471 0.3348 1.0000
6.000 0.8849 0.02690 0.01535 -0.0460 0.3177 1.0000
6.250 0.9073 0.02772 0.01606 -0.0450 0.3028 1.0000
6.500 0.9301 0.02857 0.01679 -0.0441 0.2900 1.0000
6.750 0.9531 0.02943 0.01756 -0.0432 0.2780 1.0000
7.000 0.9758 0.03033 0.01846 -0.0423 0.2665 1.0000
7.250 0.9991 0.03124 0.01925 -0.0415 0.2563 1.0000
7.500 1.0196 0.03217 0.02023 -0.0404 0.2445 1.0000
7.750 1.0381 0.03309 0.02114 -0.0390 0.2321 1.0000
8.000 1.0552 0.03397 0.02192 -0.0375 0.2197 1.0000
8.250 1.0702 0.03485 0.02280 -0.0358 0.2072 1.0000
8.500 1.0844 0.03583 0.02387 -0.0341 0.1954 1.0000
8.750 1.0997 0.03683 0.02485 -0.0325 0.1854 1.0000
9.000 1.1138 0.03785 0.02588 -0.0308 0.1757 1.0000
9.250 1.1263 0.03904 0.02720 -0.0290 0.1657 1.0000
9.500 1.1384 0.04020 0.02835 -0.0272 0.1571 1.0000
9.750 1.1484 0.04144 0.02965 -0.0252 0.1485 1.0000
10.000 1.1564 0.04288 0.03120 -0.0231 0.1402 1.0000
10.250 1.1648 0.04418 0.03244 -0.0211 0.1336 1.0000
10.500 1.1714 0.04593 0.03436 -0.0191 0.1264 1.0000
10.750 1.1786 0.04759 0.03604 -0.0174 0.1208 1.0000
11.000 1.1839 0.04948 0.03805 -0.0157 0.1154 1.0000
11.250 1.1902 0.05132 0.03991 -0.0142 0.1113 1.0000
11.500 1.1931 0.05374 0.04254 -0.0128 0.1071 1.0000
11.750 1.1986 0.05571 0.04453 -0.0115 0.1041 1.0000
12.000 1.1993 0.05842 0.04740 -0.0105 0.1013 1.0000
12.250 1.1954 0.06166 0.05088 -0.0097 0.0986 1.0000
12.500 1.1940 0.06454 0.05387 -0.0091 0.0964 1.0000
12.750 1.1983 0.06679 0.05610 -0.0085 0.0945 1.0000
13.000 1.1817 0.07186 0.06149 -0.0090 0.0930 1.0000
13.250 1.1586 0.07807 0.06804 -0.0105 0.0918 1.0000
13.500 1.1266 0.08613 0.07640 -0.0137 0.0910 1.0000
13.750 1.0621 0.10108 0.09179 -0.0220 0.0910 1.0000
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Polar data table (+)
Polar graphs
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