FX 63-145 AIRFOIL (fx63145-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: FX 63-145 AIRFOIL (fx63145-il) Reynolds number: 50,000 Max Cl/Cd: 33.7 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63145-il-50000-n5.txt Download as CSV file: xf-fx63145-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-145 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2935 0.09785 0.09149 -0.0469 1.0000 0.0379
-9.000 -0.2924 0.09475 0.08850 -0.0470 1.0000 0.0372
-8.750 -0.2951 0.09122 0.08509 -0.0477 1.0000 0.0365
-8.500 -0.3006 0.08743 0.08143 -0.0485 1.0000 0.0357
-8.250 -0.3100 0.08329 0.07742 -0.0496 1.0000 0.0347
-8.000 -0.3278 0.07886 0.07315 -0.0507 1.0000 0.0338
-7.750 -0.3568 0.07561 0.07008 -0.0503 1.0000 0.0332
-7.500 -0.3713 0.06857 0.06288 -0.0602 0.9856 0.0319
-7.250 -0.3546 0.06301 0.05713 -0.0679 0.9642 0.0315
-7.000 -0.3359 0.05770 0.05151 -0.0747 0.9442 0.0310
-6.750 -0.3130 0.05274 0.04616 -0.0807 0.9266 0.0306
-6.500 -0.2859 0.04824 0.04119 -0.0856 0.9109 0.0304
-6.250 -0.2545 0.04431 0.03673 -0.0899 0.8969 0.0305
-6.000 -0.2174 0.04076 0.03255 -0.0940 0.8851 0.0313
-5.750 -0.1796 0.03784 0.02910 -0.0972 0.8729 0.0326
-5.500 -0.1454 0.03566 0.02664 -0.0992 0.8592 0.0341
-5.250 -0.1092 0.03365 0.02428 -0.1007 0.8466 0.0354
-5.000 -0.0718 0.03187 0.02219 -0.1016 0.8354 0.0364
-4.750 -0.0397 0.03058 0.02062 -0.1014 0.8220 0.0376
-4.500 -0.0103 0.02948 0.01933 -0.1010 0.8088 0.0390
-4.250 0.0191 0.02835 0.01804 -0.1013 0.7971 0.0414
-4.000 0.0499 0.02735 0.01680 -0.1021 0.7868 0.0445
-3.750 0.0779 0.02638 0.01573 -0.1030 0.7757 0.0490
-3.500 0.1109 0.02538 0.01456 -0.1045 0.7669 0.0616
-3.250 0.1402 0.02246 0.01356 -0.1084 0.7568 0.3550
-3.000 0.1578 0.02347 0.01517 -0.1039 0.7481 0.5635
-2.750 0.1757 0.02441 0.01596 -0.1000 0.7386 0.6115
-2.500 0.2025 0.02465 0.01590 -0.0992 0.7299 0.6341
-2.250 0.2252 0.02493 0.01597 -0.0973 0.7212 0.6529
-2.000 0.2486 0.02514 0.01598 -0.0958 0.7132 0.6709
-1.750 0.2721 0.02531 0.01596 -0.0947 0.7050 0.6876
-1.500 0.2984 0.02540 0.01584 -0.0941 0.6981 0.7027
-1.250 0.3217 0.02552 0.01581 -0.0933 0.6897 0.7155
-1.000 0.3486 0.02552 0.01560 -0.0926 0.6832 0.7273
-0.750 0.3713 0.02565 0.01562 -0.0919 0.6739 0.7388
-0.500 0.4021 0.02561 0.01535 -0.0924 0.6669 0.7505
-0.250 0.4218 0.02576 0.01545 -0.0909 0.6579 0.7597
0.000 0.4509 0.02575 0.01525 -0.0910 0.6505 0.7705
0.250 0.4719 0.02591 0.01536 -0.0900 0.6414 0.7805
0.500 0.4989 0.02588 0.01519 -0.0896 0.6338 0.7907
0.750 0.5224 0.02607 0.01532 -0.0893 0.6248 0.8020
1.000 0.5467 0.02604 0.01519 -0.0883 0.6174 0.8116
1.250 0.5696 0.02622 0.01534 -0.0877 0.6093 0.8221
1.500 0.5939 0.02629 0.01535 -0.0871 0.6019 0.8326
1.750 0.6176 0.02640 0.01541 -0.0864 0.5949 0.8431
2.000 0.6400 0.02662 0.01564 -0.0858 0.5868 0.8546
2.250 0.6659 0.02657 0.01551 -0.0852 0.5804 0.8655
2.500 0.6840 0.02685 0.01587 -0.0840 0.5713 0.8774
2.750 0.7115 0.02673 0.01569 -0.0836 0.5647 0.8912
3.000 0.7289 0.02699 0.01604 -0.0823 0.5554 0.9080
3.250 0.7576 0.02683 0.01583 -0.0822 0.5487 0.9266
3.500 0.7821 0.02715 0.01624 -0.0825 0.5394 0.9523
3.750 0.8192 0.02716 0.01621 -0.0845 0.5323 1.0000
4.000 0.8454 0.02781 0.01696 -0.0855 0.5232 1.0000
4.250 0.8788 0.02807 0.01717 -0.0871 0.5160 1.0000
4.500 0.9040 0.02877 0.01794 -0.0879 0.5071 1.0000
4.750 0.9357 0.02906 0.01822 -0.0891 0.5001 1.0000
5.000 0.9607 0.02976 0.01904 -0.0897 0.4921 1.0000
5.250 0.9899 0.03016 0.01947 -0.0905 0.4853 1.0000
5.500 1.0164 0.03071 0.02006 -0.0910 0.4783 1.0000
5.750 1.0403 0.03135 0.02083 -0.0912 0.4704 1.0000
6.000 1.0687 0.03171 0.02121 -0.0916 0.4641 1.0000
6.250 1.0843 0.03280 0.02248 -0.0909 0.4547 1.0000
6.500 1.1087 0.03331 0.02308 -0.0909 0.4476 1.0000
6.750 1.1229 0.03441 0.02435 -0.0899 0.4383 1.0000
7.000 1.1440 0.03503 0.02506 -0.0895 0.4307 1.0000
7.250 1.1625 0.03571 0.02586 -0.0887 0.4221 1.0000
7.500 1.1819 0.03630 0.02656 -0.0879 0.4138 1.0000
7.750 1.2008 0.03691 0.02727 -0.0871 0.4052 1.0000
8.000 1.2100 0.03813 0.02863 -0.0855 0.3960 1.0000
8.250 1.2244 0.03891 0.02951 -0.0842 0.3871 1.0000
8.500 1.2183 0.04113 0.03191 -0.0817 0.3761 1.0000
8.750 1.2280 0.04231 0.03320 -0.0804 0.3669 1.0000
9.000 1.2450 0.04292 0.03389 -0.0794 0.3583 1.0000
9.250 1.2528 0.04436 0.03543 -0.0782 0.3488 1.0000
9.500 1.2809 0.04402 0.03508 -0.0775 0.3402 1.0000
9.750 1.2652 0.04772 0.03899 -0.0760 0.3284 1.0000
10.000 1.2547 0.05137 0.04280 -0.0754 0.3170 1.0000
10.250 1.2589 0.05353 0.04508 -0.0749 0.3069 1.0000
10.500 1.2765 0.05410 0.04568 -0.0741 0.2977 1.0000
10.750 1.2831 0.05608 0.04773 -0.0736 0.2882 1.0000
11.000 1.3005 0.05676 0.04839 -0.0728 0.2796 1.0000
11.250 1.2940 0.06056 0.05235 -0.0729 0.2696 1.0000
11.500 1.2788 0.06576 0.05775 -0.0737 0.2596 1.0000
11.750 1.2802 0.06875 0.06086 -0.0738 0.2514 1.0000
12.000 1.2832 0.07159 0.06381 -0.0740 0.2440 1.0000
12.250 1.2982 0.07269 0.06495 -0.0734 0.2383 1.0000
12.500 1.3018 0.07558 0.06797 -0.0736 0.2321 1.0000
12.750 1.3284 0.07506 0.06747 -0.0724 0.2274 1.0000
13.000 1.3052 0.08216 0.07482 -0.0744 0.2206 1.0000
13.250 1.3101 0.08501 0.07780 -0.0746 0.2153 1.0000
13.500 1.2704 0.09545 0.08846 -0.0784 0.2085 1.0000
13.750 1.2539 0.10235 0.09551 -0.0809 0.2027 1.0000
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Polar data table (+)
Polar graphs
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