WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il) Reynolds number: 50,000 Max Cl/Cd: 29.01 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx62k131-il-50000-n5.txt Download as CSV file: xf-fx62k131-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 62-K-131 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4030 0.09444 0.08850 -0.0637 0.9731 0.0508
-7.500 -0.3907 0.09128 0.08533 -0.0618 0.9697 0.0493
-7.250 -0.3866 0.08720 0.08124 -0.0642 0.9646 0.0481
-7.000 -0.3841 0.08263 0.07665 -0.0680 0.9593 0.0468
-6.750 -0.3840 0.07820 0.07215 -0.0711 0.9528 0.0456
-6.500 -0.3757 0.07295 0.06672 -0.0762 0.9480 0.0439
-6.250 -0.3743 0.06865 0.06223 -0.0783 0.9415 0.0425
-6.000 -0.3590 0.06295 0.05607 -0.0833 0.9368 0.0401
-5.750 -0.3353 0.05884 0.05109 -0.0873 0.9321 0.0377
-5.500 -0.3161 0.05494 0.04692 -0.0890 0.9279 0.0373
-5.250 -0.2877 0.05106 0.04261 -0.0921 0.9246 0.0369
-5.000 -0.2530 0.04742 0.03843 -0.0956 0.9221 0.0368
-4.750 -0.2221 0.04455 0.03503 -0.0976 0.9189 0.0370
-4.500 -0.1922 0.04233 0.03221 -0.0988 0.9150 0.0377
-4.250 -0.1614 0.03990 0.02964 -0.1007 0.9120 0.0412
-4.000 -0.1281 0.03832 0.02777 -0.1019 0.9093 0.0449
-3.750 -0.0971 0.03695 0.02610 -0.1017 0.9067 0.0471
-3.500 -0.0786 0.03614 0.02508 -0.0995 0.9016 0.0492
-3.250 -0.0534 0.03519 0.02406 -0.0987 0.8978 0.0543
-3.000 -0.0213 0.03443 0.02309 -0.0996 0.8947 0.0644
-2.750 0.0085 0.03352 0.02205 -0.1007 0.8906 0.0766
-2.250 0.0495 0.03136 0.02299 -0.0971 0.8825 0.6909
-2.000 0.0395 0.03283 0.02446 -0.0862 0.8757 0.7740
-1.750 0.0232 0.03344 0.02507 -0.0743 0.8687 0.8249
-1.500 0.0207 0.03348 0.02496 -0.0665 0.8631 0.8624
-1.250 0.0393 0.03346 0.02462 -0.0652 0.8569 0.8752
-1.000 0.0681 0.03342 0.02419 -0.0658 0.8528 0.8866
-0.750 0.0871 0.03347 0.02400 -0.0649 0.8465 0.8976
-0.500 0.1105 0.03342 0.02372 -0.0646 0.8411 0.9079
-0.250 0.1422 0.03339 0.02343 -0.0657 0.8374 0.9172
0.000 0.1577 0.03354 0.02344 -0.0646 0.8296 0.9268
0.250 0.1883 0.03357 0.02324 -0.0658 0.8251 0.9352
0.500 0.2099 0.03373 0.02327 -0.0657 0.8183 0.9436
0.750 0.2387 0.03388 0.02328 -0.0667 0.8127 0.9514
1.000 0.2701 0.03401 0.02326 -0.0682 0.8078 0.9588
1.250 0.2936 0.03431 0.02348 -0.0687 0.8002 0.9668
1.500 0.3310 0.03445 0.02352 -0.0711 0.7961 0.9740
1.750 0.3529 0.03488 0.02391 -0.0716 0.7874 0.9834
2.250 0.4081 0.03554 0.02449 -0.0739 0.7732 0.9999
2.500 0.4455 0.03584 0.02475 -0.0764 0.7687 0.9999
2.750 0.4673 0.03653 0.02545 -0.0770 0.7596 0.9999
3.000 0.5048 0.03681 0.02573 -0.0794 0.7549 0.9999
3.250 0.5267 0.03754 0.02649 -0.0799 0.7454 0.9999
3.500 0.5651 0.03775 0.02672 -0.0823 0.7407 0.9999
3.750 0.5864 0.03853 0.02756 -0.0827 0.7305 0.9999
4.000 0.6262 0.03860 0.02773 -0.0851 0.7262 0.9999
4.250 0.6467 0.03943 0.02864 -0.0854 0.7153 0.9999
4.500 0.6720 0.04008 0.02939 -0.0862 0.7060 0.9999
4.750 0.7083 0.04022 0.02969 -0.0880 0.7000 0.9999
5.000 0.7299 0.04104 0.03063 -0.0884 0.6892 0.9999
5.500 0.7901 0.04177 0.03166 -0.0905 0.6730 0.9999
5.750 0.8126 0.04255 0.03266 -0.0909 0.6620 0.9999
6.250 0.8736 0.04299 0.03351 -0.0926 0.6449 0.9999
6.500 0.8957 0.04372 0.03444 -0.0927 0.6331 0.9999
6.750 0.9199 0.04426 0.03521 -0.0929 0.6219 0.9999
7.000 0.9595 0.04346 0.03475 -0.0937 0.6159 0.9999
7.250 0.9823 0.04391 0.03545 -0.0935 0.6031 0.9999
7.500 1.0072 0.04404 0.03586 -0.0932 0.5903 0.9999
7.750 1.0355 0.04365 0.03576 -0.0928 0.5768 0.9999
8.000 1.0689 0.04251 0.03500 -0.0922 0.5618 0.9999
8.250 1.0976 0.04163 0.03442 -0.0912 0.5427 0.9999
8.500 1.1244 0.04085 0.03392 -0.0899 0.5201 0.9999
8.750 1.1463 0.04061 0.03394 -0.0885 0.4934 0.9999
9.000 1.1678 0.04030 0.03380 -0.0868 0.4593 0.9999
9.250 1.1815 0.04073 0.03430 -0.0847 0.4152 0.9999
9.500 1.1895 0.04168 0.03506 -0.0822 0.3572 0.9999
9.750 1.1889 0.04369 0.03678 -0.0796 0.2934 0.9999
10.000 1.1827 0.04659 0.03931 -0.0774 0.2328 0.9999
10.250 1.1749 0.04996 0.04232 -0.0756 0.1845 0.9999
10.500 1.1673 0.05354 0.04562 -0.0741 0.1475 0.9999
10.750 1.1609 0.05721 0.04909 -0.0729 0.1194 0.9999
11.000 1.1558 0.06087 0.05261 -0.0717 0.1009 0.9999
11.250 1.1535 0.06436 0.05609 -0.0707 0.0847 0.9999
11.500 1.1521 0.06781 0.05954 -0.0698 0.0707 0.9999
11.750 1.1528 0.07108 0.06284 -0.0689 0.0607 0.9999
12.000 1.1524 0.07447 0.06621 -0.0683 0.0515 0.9999
12.250 1.1557 0.07761 0.06953 -0.0678 0.0434 0.9999
12.500 1.1609 0.08058 0.07267 -0.0671 0.0371 0.9999
12.750 1.1664 0.08356 0.07581 -0.0666 0.0327 0.9999
13.000 1.1730 0.08645 0.07879 -0.0659 0.0295 0.9999
13.250 1.1829 0.08943 0.08219 -0.0650 0.0269 0.9999
13.500 1.1891 0.09299 0.08608 -0.0645 0.0255 0.9999
13.750 1.1899 0.09725 0.09066 -0.0647 0.0246 0.9999
14.000 1.1862 0.10203 0.09575 -0.0656 0.0241 0.9999
14.250 1.1794 0.10742 0.10143 -0.0671 0.0237 0.9999
14.500 1.1701 0.11332 0.10762 -0.0694 0.0235 0.9999
14.750 1.1584 0.11995 0.11452 -0.0726 0.0235 0.9999
15.000 1.1446 0.12745 0.12228 -0.0768 0.0235 0.9999
15.250 1.1287 0.13585 0.13093 -0.0821 0.0238 0.9999
15.500 1.1116 0.14553 0.14083 -0.0886 0.0242 0.9999
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