PT40 (pt40-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: PT40 (pt40-il) Reynolds number: 100,000 Max Cl/Cd: 46.26 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-pt40-il-100000-n5.txt Download as CSV file: xf-pt40-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3298 0.09578 0.09004 -0.0292 1.0000 0.0891
-7.500 -0.3562 0.09302 0.08740 -0.0315 1.0000 0.0906
-7.250 -0.3803 0.09001 0.08450 -0.0333 1.0000 0.0909
-7.000 -0.3835 0.08697 0.08154 -0.0328 1.0000 0.0912
-6.750 -0.3744 0.08501 0.07965 -0.0294 1.0000 0.0919
-6.500 -0.3752 0.08287 0.07758 -0.0276 1.0000 0.0925
-6.250 -0.3805 0.08065 0.07542 -0.0263 1.0000 0.0930
-6.000 -0.3843 0.06956 0.06402 -0.0388 0.9940 0.0751
-5.750 -0.3591 0.06633 0.06078 -0.0416 0.9878 0.0743
-5.500 -0.3328 0.06155 0.05586 -0.0473 0.9806 0.0738
-5.250 -0.3066 0.05689 0.05104 -0.0523 0.9725 0.0729
-5.000 -0.2812 0.05177 0.04566 -0.0569 0.9637 0.0712
-4.750 -0.2511 0.04579 0.03920 -0.0624 0.9570 0.0698
-4.500 -0.2247 0.04325 0.03650 -0.0640 0.9477 0.0706
-4.250 -0.1907 0.04039 0.03341 -0.0671 0.9426 0.0717
-4.000 -0.1639 0.03767 0.03039 -0.0684 0.9329 0.0721
-3.750 -0.1294 0.03486 0.02723 -0.0708 0.9276 0.0722
-3.500 -0.1018 0.03270 0.02479 -0.0715 0.9181 0.0726
-3.250 -0.0678 0.03063 0.02235 -0.0731 0.9118 0.0738
-3.000 -0.0381 0.02877 0.01999 -0.0736 0.9029 0.0753
-2.750 -0.0054 0.02753 0.01872 -0.0746 0.8955 0.0761
-2.500 0.0267 0.02638 0.01744 -0.0754 0.8878 0.0768
-2.250 0.0575 0.02534 0.01628 -0.0758 0.8787 0.0777
-2.000 0.0924 0.02432 0.01512 -0.0768 0.8720 0.0792
-1.750 0.1207 0.02353 0.01415 -0.0766 0.8610 0.0811
-1.500 0.1557 0.02262 0.01300 -0.0774 0.8539 0.0828
-1.250 0.1831 0.02192 0.01232 -0.0770 0.8423 0.0838
-1.000 0.2163 0.02120 0.01160 -0.0776 0.8343 0.0851
-0.750 0.2439 0.02072 0.01111 -0.0771 0.8223 0.0871
-0.500 0.2763 0.02017 0.01047 -0.0774 0.8135 0.0898
-0.250 0.3033 0.01971 0.01000 -0.0767 0.7998 0.0916
0.000 0.3319 0.01917 0.00950 -0.0762 0.7839 0.0934
0.250 0.3594 0.01869 0.00901 -0.0752 0.7636 0.0957
0.500 0.3862 0.01832 0.00858 -0.0742 0.7423 0.0989
0.750 0.4130 0.01795 0.00823 -0.0734 0.7244 0.1019
1.000 0.4399 0.01763 0.00794 -0.0726 0.7086 0.1048
1.250 0.4656 0.01743 0.00773 -0.0716 0.6910 0.1085
1.500 0.4914 0.01722 0.00754 -0.0707 0.6733 0.1130
1.750 0.5174 0.01707 0.00739 -0.0698 0.6550 0.1185
2.000 0.5434 0.01694 0.00723 -0.0689 0.6356 0.1245
2.250 0.5694 0.01684 0.00711 -0.0680 0.6148 0.1345
2.750 0.6108 0.01493 0.00718 -0.0645 0.5715 0.7358
3.250 0.6781 0.01502 0.00712 -0.0652 0.5112 1.0000
3.500 0.7012 0.01532 0.00720 -0.0639 0.4793 1.0000
3.750 0.7235 0.01569 0.00732 -0.0625 0.4441 1.0000
4.000 0.7452 0.01611 0.00750 -0.0610 0.4058 1.0000
4.250 0.7663 0.01661 0.00773 -0.0596 0.3676 1.0000
4.500 0.7872 0.01716 0.00802 -0.0581 0.3347 1.0000
4.750 0.8084 0.01773 0.00837 -0.0568 0.3094 1.0000
5.000 0.8300 0.01829 0.00876 -0.0555 0.2894 1.0000
5.250 0.8517 0.01886 0.00918 -0.0543 0.2739 1.0000
5.500 0.8738 0.01942 0.00962 -0.0532 0.2607 1.0000
5.750 0.8963 0.01996 0.01010 -0.0521 0.2495 1.0000
6.000 0.9177 0.02058 0.01057 -0.0509 0.2394 1.0000
6.250 0.9403 0.02109 0.01107 -0.0499 0.2282 1.0000
6.500 0.9618 0.02166 0.01156 -0.0488 0.2172 1.0000
6.750 0.9822 0.02226 0.01204 -0.0476 0.2056 1.0000
7.000 1.0037 0.02274 0.01252 -0.0465 0.1936 1.0000
7.250 1.0246 0.02329 0.01304 -0.0453 0.1837 1.0000
7.500 1.0448 0.02387 0.01357 -0.0441 0.1754 1.0000
7.750 1.0660 0.02441 0.01415 -0.0430 0.1670 1.0000
8.000 1.0850 0.02503 0.01472 -0.0416 0.1594 1.0000
8.250 1.1054 0.02558 0.01534 -0.0404 0.1507 1.0000
8.500 1.1242 0.02621 0.01597 -0.0391 0.1424 1.0000
8.750 1.1414 0.02689 0.01662 -0.0376 0.1342 1.0000
9.000 1.1593 0.02755 0.01735 -0.0361 0.1248 1.0000
9.250 1.1756 0.02830 0.01811 -0.0345 0.1154 1.0000
9.500 1.1897 0.02911 0.01892 -0.0326 0.1063 1.0000
9.750 1.2023 0.03001 0.01983 -0.0306 0.0981 1.0000
10.000 1.2138 0.03103 0.02083 -0.0285 0.0912 1.0000
10.250 1.2240 0.03216 0.02192 -0.0265 0.0859 1.0000
10.500 1.2345 0.03334 0.02315 -0.0245 0.0812 1.0000
10.750 1.2429 0.03466 0.02447 -0.0226 0.0780 1.0000
11.000 1.2518 0.03602 0.02590 -0.0208 0.0748 1.0000
11.250 1.2587 0.03751 0.02740 -0.0190 0.0725 1.0000
11.500 1.2658 0.03908 0.02904 -0.0174 0.0703 1.0000
11.750 1.2724 0.04074 0.03079 -0.0160 0.0683 1.0000
12.000 1.2776 0.04254 0.03263 -0.0146 0.0667 1.0000
12.250 1.2815 0.04450 0.03460 -0.0134 0.0654 1.0000
12.500 1.2868 0.04648 0.03672 -0.0124 0.0640 1.0000
12.750 1.2911 0.04860 0.03894 -0.0114 0.0628 1.0000
13.000 1.2945 0.05084 0.04128 -0.0107 0.0618 1.0000
13.250 1.2973 0.05318 0.04369 -0.0100 0.0609 1.0000
13.500 1.2997 0.05562 0.04617 -0.0095 0.0602 1.0000
13.750 1.3023 0.05808 0.04867 -0.0091 0.0596 1.0000
14.000 1.3034 0.06088 0.05164 -0.0088 0.0589 1.0000
14.250 1.3032 0.06387 0.05479 -0.0087 0.0582 1.0000
14.500 1.3018 0.06707 0.05814 -0.0089 0.0575 1.0000
14.750 1.2993 0.07047 0.06169 -0.0093 0.0569 1.0000
15.000 1.2958 0.07405 0.06541 -0.0099 0.0563 1.0000
15.250 1.2918 0.07780 0.06927 -0.0107 0.0557 1.0000
15.500 1.2879 0.08163 0.07321 -0.0116 0.0552 1.0000
15.750 1.2851 0.08534 0.07700 -0.0126 0.0547 1.0000
16.000 1.2846 0.08872 0.08042 -0.0134 0.0542 1.0000
16.250 1.2726 0.09421 0.08611 -0.0157 0.0539 1.0000
16.500 1.2537 0.10121 0.09338 -0.0192 0.0536 1.0000
16.750 1.2292 0.10962 0.10207 -0.0239 0.0534 1.0000
17.000 1.1916 0.12138 0.11416 -0.0312 0.0534 1.0000
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Polar data table (+)
Polar graphs
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