WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il) Xfoil prediction polar at RE=50,000 Ncrit=0
| Details | Polar file |
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Airfoil: WORTMANN FX 62-K-131 AIRFOIL (fx62k131-il) Reynolds number: 50,000 Max Cl/Cd: 30.52 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx62k131-il-50000.txt Download as CSV file: xf-fx62k131-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3388 0.13766 0.13118 -0.0419 1.0001 0.1693
-10.500 -0.3536 0.13724 0.13087 -0.0403 1.0001 0.1748
-10.250 -0.3786 0.13788 0.13166 -0.0392 1.0001 0.1764
-10.000 -0.3610 0.13317 0.12694 -0.0362 1.0001 0.1875
-9.750 -0.3861 0.13357 0.12749 -0.0352 1.0001 0.1904
-9.500 -0.3725 0.12951 0.12344 -0.0325 1.0001 0.2012
-9.250 -0.3991 0.12984 0.12391 -0.0315 1.0001 0.2046
-9.000 -0.3871 0.12606 0.12015 -0.0289 1.0001 0.2165
-8.750 -0.3897 0.12361 0.11777 -0.0270 1.0001 0.2242
-8.500 -0.4087 0.12310 0.11737 -0.0255 1.0001 0.2325
-8.250 -0.4023 0.11999 0.11429 -0.0232 1.0001 0.2442
-8.000 -0.4051 0.11764 0.11201 -0.0212 1.0001 0.2540
-7.750 -0.4352 0.11780 0.11231 -0.0195 1.0001 0.2616
-7.500 -0.4333 0.11516 0.10971 -0.0171 1.0001 0.2753
-7.250 -0.4347 0.11281 0.10742 -0.0147 1.0001 0.2892
-7.000 -0.4400 0.11081 0.10549 -0.0122 1.0001 0.3034
-6.750 -0.4491 0.10911 0.10388 -0.0095 1.0001 0.3181
-6.500 -0.4379 0.10584 0.10063 -0.0069 1.0001 0.3374
-6.250 -0.4397 0.10394 0.09873 -0.0039 1.0001 0.3580
-6.000 -0.4606 0.10321 0.09812 -0.0002 1.0001 0.3754
-5.750 -0.4484 0.10036 0.09529 0.0028 1.0001 0.4026
-5.500 -0.4411 0.09791 0.09288 0.0059 1.0001 0.4300
-5.250 -0.4384 0.09588 0.09089 0.0093 1.0001 0.4589
-5.000 -0.4414 0.09435 0.08943 0.0134 1.0001 0.4892
-4.750 -0.4211 0.09114 0.08622 0.0156 1.0001 0.5228
-3.750 -0.3485 0.04876 0.04065 -0.0694 1.0001 0.1178
-3.500 -0.3047 0.04545 0.03645 -0.0729 1.0001 0.1048
-3.250 -0.2706 0.04291 0.03350 -0.0749 1.0001 0.1037
-3.000 -0.2370 0.04113 0.03122 -0.0763 1.0001 0.1049
-2.750 -0.2069 0.03957 0.02930 -0.0768 1.0001 0.1053
-2.500 -0.1810 0.03822 0.02777 -0.0761 1.0001 0.1066
-2.250 -0.1608 0.03720 0.02681 -0.0742 1.0001 0.1110
-2.000 -0.1404 0.03662 0.02617 -0.0725 1.0001 0.1222
-1.750 -0.1146 0.03596 0.02554 -0.0720 1.0001 0.1390
-1.500 -0.0657 0.03355 0.02644 -0.0743 1.0001 0.6639
-1.250 -0.0918 0.03500 0.02790 -0.0596 1.0001 0.7942
-1.000 -0.1159 0.03526 0.02812 -0.0464 1.0001 0.8563
-0.750 -0.1393 0.03467 0.02748 -0.0343 1.0001 0.9102
-0.500 -0.1570 0.03305 0.02581 -0.0242 1.0001 0.9788
-0.250 -0.1515 0.03207 0.02458 -0.0221 1.0001 0.9999
0.000 -0.1275 0.03255 0.02464 -0.0237 1.0001 0.9999
0.250 -0.1018 0.03318 0.02491 -0.0257 1.0001 0.9999
0.500 -0.0749 0.03393 0.02531 -0.0279 1.0001 0.9999
0.750 -0.0477 0.03477 0.02589 -0.0303 1.0001 0.9999
1.000 -0.0202 0.03571 0.02658 -0.0327 1.0001 0.9999
1.250 0.0073 0.03672 0.02738 -0.0351 1.0001 0.9999
1.500 0.0346 0.03780 0.02829 -0.0375 1.0001 0.9999
1.750 0.0615 0.03895 0.02925 -0.0399 1.0001 0.9999
2.000 0.0880 0.04016 0.03033 -0.0423 1.0001 0.9999
2.250 0.1144 0.04144 0.03150 -0.0446 1.0001 0.9999
2.500 0.1400 0.04278 0.03275 -0.0469 1.0001 0.9999
2.750 0.1650 0.04418 0.03405 -0.0491 1.0001 0.9999
3.000 0.1896 0.04564 0.03546 -0.0513 1.0001 0.9999
3.250 0.2137 0.04718 0.03696 -0.0535 1.0001 0.9999
3.500 0.2373 0.04878 0.03854 -0.0557 1.0001 0.9999
3.750 0.2606 0.05047 0.04021 -0.0578 1.0001 0.9999
4.000 0.2829 0.05221 0.04195 -0.0599 1.0001 0.9999
4.250 0.3189 0.05474 0.04450 -0.0646 0.9915 0.9999
4.500 0.3581 0.05749 0.04729 -0.0699 0.9779 0.9999
4.750 0.4012 0.06051 0.05035 -0.0757 0.9623 0.9999
5.000 0.4319 0.06283 0.05272 -0.0792 0.9465 0.9999
5.250 0.4601 0.06473 0.05471 -0.0819 0.9256 0.9999
5.500 0.4984 0.06743 0.05751 -0.0862 0.9057 0.9999
5.750 0.6149 0.06620 0.05637 -0.0939 0.7944 0.9999
6.000 0.6346 0.06757 0.05790 -0.0944 0.7770 0.9999
6.250 0.6615 0.06901 0.05948 -0.0958 0.7601 0.9999
6.500 0.6942 0.07036 0.06099 -0.0976 0.7432 0.9999
6.750 0.7320 0.07158 0.06239 -0.0998 0.7269 0.9999
7.000 0.7544 0.07301 0.06404 -0.1005 0.7103 0.9999
7.250 0.7735 0.07450 0.06571 -0.1008 0.6935 0.9999
7.500 0.7998 0.07577 0.06719 -0.1017 0.6765 0.9999
7.750 0.8363 0.07647 0.06815 -0.1030 0.6593 0.9999
8.000 0.8652 0.07722 0.06919 -0.1034 0.6410 0.9999
8.250 0.8870 0.07817 0.07038 -0.1032 0.6212 0.9999
8.500 0.9472 0.07603 0.06866 -0.1040 0.6015 0.9999
8.750 0.9596 0.07707 0.06994 -0.1027 0.5786 0.9999
9.000 1.0069 0.07450 0.06786 -0.1015 0.5548 0.9999
9.250 1.0940 0.06542 0.05954 -0.0986 0.5282 0.9999
9.500 1.2439 0.04076 0.03586 -0.0878 0.4430 0.9999
9.750 1.2377 0.04118 0.03560 -0.0816 0.3459 0.9999
10.000 1.2190 0.04450 0.03802 -0.0767 0.2669 0.9999
10.250 1.2050 0.04828 0.04101 -0.0730 0.2100 0.9999
10.500 1.2111 0.05159 0.04362 -0.0698 0.1571 0.9999
10.750 1.2417 0.05464 0.04618 -0.0678 0.1118 0.9999
11.000 1.2675 0.05810 0.04951 -0.0670 0.0863 0.9999
11.250 1.2982 0.06203 0.05365 -0.0666 0.0730 0.9999
11.500 1.3435 0.06760 0.05927 -0.0682 0.0641 0.9999
11.750 1.3447 0.07172 0.06393 -0.0660 0.0634 0.9999
12.000 1.3406 0.07605 0.06874 -0.0638 0.0630 0.9999
12.250 1.3326 0.08050 0.07359 -0.0619 0.0630 0.9999
12.500 1.3205 0.08512 0.07857 -0.0601 0.0631 0.9999
12.750 1.3067 0.08993 0.08369 -0.0588 0.0633 0.9999
13.000 1.2922 0.09500 0.08903 -0.0580 0.0637 0.9999
13.250 1.2781 0.10040 0.09468 -0.0577 0.0640 0.9999
13.500 1.2578 0.10534 0.09993 -0.0579 0.0646 0.9999
13.750 1.2112 0.11109 0.10611 -0.0602 0.0660 0.9999
14.000 1.1614 0.12014 0.11553 -0.0657 0.0683 0.9999
14.250 1.1265 0.13025 0.12582 -0.0725 0.0706 0.9999
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