FX 60-157 AIRFOIL (fx60157-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 60-157 AIRFOIL (fx60157-il) Reynolds number: 200,000 Max Cl/Cd: 57.24 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx60157-il-200000-n5.txt Download as CSV file: xf-fx60157-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 60-157 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6122 0.08048 0.07657 -0.0695 0.9983 0.0116
-13.000 -0.6445 0.06933 0.06512 -0.0784 0.9957 0.0115
-12.750 -0.6662 0.06170 0.05720 -0.0842 0.9930 0.0114
-12.500 -0.6830 0.05595 0.05116 -0.0873 0.9894 0.0114
-12.250 -0.6964 0.05089 0.04578 -0.0897 0.9859 0.0115
-12.000 -0.7027 0.04658 0.04111 -0.0915 0.9830 0.0117
-11.750 -0.7061 0.04346 0.03770 -0.0915 0.9786 0.0118
-11.500 -0.7044 0.04057 0.03449 -0.0915 0.9744 0.0120
-11.250 -0.6950 0.03820 0.03185 -0.0919 0.9715 0.0123
-11.000 -0.6788 0.03663 0.03017 -0.0931 0.9694 0.0126
-10.750 -0.6755 0.03539 0.02883 -0.0910 0.9632 0.0128
-10.500 -0.6621 0.03405 0.02733 -0.0908 0.9597 0.0133
-10.250 -0.6439 0.03254 0.02564 -0.0911 0.9572 0.0140
-10.000 -0.6218 0.03103 0.02389 -0.0917 0.9555 0.0148
-9.750 -0.6192 0.03019 0.02290 -0.0883 0.9487 0.0153
-9.500 -0.6055 0.02935 0.02207 -0.0876 0.9449 0.0163
-9.250 -0.5848 0.02835 0.02094 -0.0877 0.9425 0.0175
-9.000 -0.5610 0.02716 0.01960 -0.0882 0.9408 0.0191
-8.750 -0.5606 0.02651 0.01894 -0.0844 0.9331 0.0200
-8.500 -0.5417 0.02560 0.01796 -0.0840 0.9298 0.0217
-8.250 -0.5183 0.02463 0.01692 -0.0843 0.9275 0.0232
-8.000 -0.4909 0.02389 0.01614 -0.0853 0.9258 0.0251
-7.750 -0.4838 0.02347 0.01565 -0.0822 0.9191 0.0267
-7.500 -0.4632 0.02292 0.01508 -0.0817 0.9153 0.0284
-7.250 -0.4367 0.02246 0.01455 -0.0821 0.9131 0.0313
-7.000 -0.4088 0.02188 0.01392 -0.0830 0.9113 0.0341
-6.750 -0.3787 0.02133 0.01331 -0.0841 0.9100 0.0375
-6.500 -0.3731 0.02101 0.01295 -0.0805 0.9025 0.0392
-6.250 -0.3506 0.02045 0.01238 -0.0803 0.8993 0.0423
-6.000 -0.3234 0.01988 0.01175 -0.0809 0.8972 0.0454
-5.750 -0.2940 0.01923 0.01111 -0.0820 0.8955 0.0497
-5.500 -0.2621 0.01865 0.01051 -0.0834 0.8943 0.0558
-5.250 -0.2502 0.01844 0.01026 -0.0808 0.8872 0.0624
-5.000 -0.2240 0.01795 0.00978 -0.0811 0.8837 0.0733
-4.750 -0.1931 0.01734 0.00927 -0.0824 0.8815 0.0979
-4.500 -0.1607 0.01655 0.00871 -0.0843 0.8800 0.1520
-4.250 -0.1261 0.01548 0.00811 -0.0870 0.8788 0.2591
-3.750 -0.0728 0.01398 0.00768 -0.0889 0.8709 0.4991
-3.500 -0.0445 0.01388 0.00787 -0.0888 0.8676 0.5678
-3.250 -0.0119 0.01390 0.00797 -0.0893 0.8651 0.6073
-3.000 0.0245 0.01393 0.00798 -0.0906 0.8633 0.6358
-2.750 0.0625 0.01402 0.00801 -0.0923 0.8618 0.6584
-2.500 0.0725 0.01437 0.00837 -0.0885 0.8529 0.6704
-2.250 0.1048 0.01447 0.00841 -0.0890 0.8499 0.6817
-2.000 0.1423 0.01445 0.00832 -0.0907 0.8476 0.6917
-1.750 0.1795 0.01443 0.00825 -0.0922 0.8458 0.6967
-1.500 0.1894 0.01462 0.00845 -0.0885 0.8367 0.7008
-1.250 0.2239 0.01452 0.00829 -0.0899 0.8334 0.7056
-1.000 0.2662 0.01428 0.00796 -0.0930 0.8309 0.7105
-0.750 0.2838 0.01432 0.00800 -0.0908 0.8229 0.7126
-0.500 0.3146 0.01422 0.00788 -0.0913 0.8178 0.7148
-0.250 0.3526 0.01408 0.00772 -0.0932 0.8146 0.7175
0.000 0.3724 0.01409 0.00771 -0.0916 0.8056 0.7218
0.250 0.4146 0.01383 0.00738 -0.0946 0.7992 0.7269
0.500 0.4350 0.01382 0.00739 -0.0929 0.7888 0.7291
0.750 0.4727 0.01368 0.00722 -0.0946 0.7823 0.7312
1.000 0.4938 0.01369 0.00724 -0.0933 0.7721 0.7338
1.250 0.5300 0.01356 0.00709 -0.0950 0.7641 0.7361
1.500 0.5578 0.01349 0.00700 -0.0951 0.7521 0.7389
1.750 0.5894 0.01340 0.00686 -0.0961 0.7387 0.7422
2.000 0.6182 0.01335 0.00679 -0.0962 0.7235 0.7444
2.250 0.6450 0.01336 0.00678 -0.0958 0.7073 0.7466
2.500 0.6727 0.01339 0.00677 -0.0957 0.6895 0.7490
2.750 0.7017 0.01342 0.00675 -0.0960 0.6713 0.7513
3.000 0.7296 0.01349 0.00674 -0.0961 0.6501 0.7539
3.250 0.7559 0.01361 0.00674 -0.0959 0.6221 0.7567
3.500 0.7811 0.01380 0.00677 -0.0956 0.5930 0.7594
3.750 0.7991 0.01403 0.00689 -0.0937 0.5641 0.7611
4.000 0.8168 0.01431 0.00706 -0.0918 0.5381 0.7629
4.250 0.8345 0.01458 0.00725 -0.0899 0.5122 0.7648
4.500 0.8511 0.01493 0.00747 -0.0880 0.4855 0.7668
4.750 0.8686 0.01528 0.00772 -0.0863 0.4592 0.7690
5.000 0.8863 0.01568 0.00801 -0.0848 0.4317 0.7713
5.250 0.9046 0.01612 0.00833 -0.0835 0.4069 0.7736
5.500 0.9235 0.01655 0.00868 -0.0823 0.3822 0.7759
5.750 0.9384 0.01702 0.00907 -0.0802 0.3576 0.7777
6.000 0.9528 0.01756 0.00950 -0.0781 0.3311 0.7797
6.500 0.9840 0.01869 0.01043 -0.0747 0.2811 0.7838
6.750 1.0016 0.01923 0.01091 -0.0735 0.2596 0.7862
7.000 1.0189 0.01984 0.01142 -0.0723 0.2395 0.7887
7.250 1.0372 0.02045 0.01195 -0.0713 0.2233 0.7910
7.500 1.0558 0.02096 0.01247 -0.0703 0.2084 0.7928
7.750 1.0726 0.02150 0.01302 -0.0689 0.1933 0.7945
8.000 1.0893 0.02208 0.01360 -0.0676 0.1822 0.7966
8.250 1.1066 0.02267 0.01421 -0.0664 0.1717 0.7988
8.500 1.1237 0.02331 0.01486 -0.0653 0.1608 0.8010
8.750 1.1420 0.02393 0.01550 -0.0644 0.1481 0.8031
9.000 1.1594 0.02463 0.01620 -0.0635 0.1386 0.8053
9.250 1.1765 0.02539 0.01697 -0.0626 0.1303 0.8074
9.500 1.1924 0.02610 0.01773 -0.0614 0.1221 0.8092
9.750 1.2079 0.02683 0.01853 -0.0602 0.1148 0.8110
10.000 1.2232 0.02761 0.01937 -0.0590 0.1051 0.8131
10.250 1.2366 0.02854 0.02033 -0.0577 0.0969 0.8155
10.500 1.2495 0.02956 0.02136 -0.0564 0.0882 0.8181
10.750 1.2621 0.03067 0.02248 -0.0552 0.0781 0.8206
11.000 1.2749 0.03182 0.02364 -0.0542 0.0652 0.8230
11.250 1.2840 0.03317 0.02498 -0.0527 0.0572 0.8249
11.500 1.2928 0.03454 0.02640 -0.0512 0.0510 0.8269
11.750 1.3039 0.03577 0.02775 -0.0500 0.0441 0.8292
12.000 1.3114 0.03735 0.02937 -0.0487 0.0373 0.8315
12.250 1.3183 0.03905 0.03110 -0.0475 0.0341 0.8340
12.500 1.3248 0.04086 0.03298 -0.0464 0.0320 0.8365
12.750 1.3302 0.04284 0.03505 -0.0454 0.0304 0.8392
13.000 1.3337 0.04493 0.03725 -0.0443 0.0291 0.8416
13.250 1.3387 0.04691 0.03940 -0.0433 0.0282 0.8443
13.500 1.3425 0.04912 0.04177 -0.0425 0.0273 0.8472
13.750 1.3452 0.05156 0.04436 -0.0419 0.0266 0.8502
14.000 1.3468 0.05425 0.04719 -0.0415 0.0258 0.8531
14.250 1.3468 0.05722 0.05029 -0.0413 0.0252 0.8559
14.500 1.3443 0.06043 0.05365 -0.0411 0.0247 0.8584
14.750 1.3401 0.06403 0.05737 -0.0412 0.0242 0.8612
15.000 1.3407 0.06719 0.06072 -0.0415 0.0237 0.8643
15.250 1.3397 0.07072 0.06441 -0.0421 0.0232 0.8677
15.750 1.3354 0.07830 0.07231 -0.0438 0.0221 0.8746
16.000 1.3316 0.08243 0.07660 -0.0449 0.0216 0.8785
16.250 1.3273 0.08681 0.08113 -0.0464 0.0211 0.8826
16.500 1.3223 0.09149 0.08596 -0.0481 0.0207 0.8866
16.750 1.3157 0.09629 0.09091 -0.0499 0.0204 0.8908
17.000 1.3083 0.10136 0.09613 -0.0519 0.0201 0.8955
17.250 1.3008 0.10659 0.10149 -0.0542 0.0198 0.9005
17.500 1.2940 0.11149 0.10656 -0.0562 0.0196 0.9068
17.750 1.2870 0.11640 0.11163 -0.0582 0.0194 0.9153
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