FX 79-W-151 A (fx79w151a-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 79-W-151 A (fx79w151a-il) Reynolds number: 200,000 Max Cl/Cd: 69.81 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx79w151a-il-200000.txt Download as CSV file: xf-fx79w151a-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 79-W-151 A
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3454 0.10643 0.10309 -0.0535 1.0000 0.0446
-11.750 -0.4740 0.07210 0.06889 -0.0703 1.0000 0.0359
-11.500 -0.5298 0.05861 0.05535 -0.0808 1.0000 0.0344
-11.250 -0.5675 0.05560 0.05237 -0.0799 1.0000 0.0339
-11.000 -0.6002 0.04535 0.04158 -0.0917 0.9832 0.0332
-10.750 -0.6064 0.03973 0.03542 -0.0953 0.9714 0.0336
-10.500 -0.6003 0.03576 0.03095 -0.0966 0.9603 0.0343
-10.250 -0.5910 0.03299 0.02768 -0.0963 0.9489 0.0356
-10.000 -0.5832 0.03024 0.02449 -0.0949 0.9376 0.0369
-9.750 -0.5650 0.02870 0.02291 -0.0944 0.9288 0.0389
-9.500 -0.5501 0.02814 0.02225 -0.0926 0.9179 0.0417
-9.250 -0.5378 0.02713 0.02094 -0.0902 0.9073 0.0443
-9.000 -0.5249 0.02529 0.01886 -0.0882 0.8991 0.0471
-8.750 -0.5086 0.02478 0.01833 -0.0863 0.8893 0.0503
-8.500 -0.4915 0.02418 0.01749 -0.0844 0.8809 0.0543
-8.250 -0.4747 0.02307 0.01626 -0.0827 0.8727 0.0585
-8.000 -0.4555 0.02276 0.01589 -0.0812 0.8643 0.0631
-7.750 -0.4362 0.02202 0.01490 -0.0796 0.8569 0.0681
-7.500 -0.4161 0.02156 0.01448 -0.0783 0.8488 0.0731
-7.250 -0.3951 0.02127 0.01392 -0.0768 0.8416 0.0790
-7.000 -0.3740 0.02053 0.01321 -0.0758 0.8340 0.0849
-6.750 -0.3521 0.02029 0.01277 -0.0745 0.8269 0.0920
-6.500 -0.3299 0.01963 0.01213 -0.0736 0.8198 0.0988
-6.250 -0.3073 0.01942 0.01171 -0.0724 0.8125 0.1065
-6.000 -0.2838 0.01879 0.01110 -0.0716 0.8064 0.1144
-5.750 -0.2608 0.01844 0.01060 -0.0707 0.7985 0.1225
-5.500 -0.2361 0.01799 0.01013 -0.0700 0.7932 0.1309
-5.250 -0.2130 0.01761 0.00969 -0.0692 0.7849 0.1391
-5.000 -0.1880 0.01729 0.00929 -0.0685 0.7792 0.1477
-4.750 -0.1642 0.01689 0.00888 -0.0678 0.7717 0.1560
-4.500 -0.1391 0.01663 0.00852 -0.0672 0.7655 0.1650
-4.250 -0.1146 0.01623 0.00814 -0.0666 0.7593 0.1739
-4.000 -0.0901 0.01594 0.00779 -0.0659 0.7522 0.1840
-3.750 -0.0642 0.01561 0.00742 -0.0654 0.7472 0.1951
-3.500 -0.0414 0.01530 0.00719 -0.0646 0.7394 0.2064
-3.250 -0.0165 0.01496 0.00684 -0.0639 0.7338 0.2213
-3.000 0.0066 0.01468 0.00663 -0.0630 0.7269 0.2405
-2.750 0.0296 0.01431 0.00637 -0.0621 0.7207 0.2670
-2.500 0.0519 0.01389 0.00612 -0.0610 0.7155 0.3127
-2.250 0.0695 0.01341 0.00602 -0.0592 0.7083 0.3930
-2.000 0.0861 0.01282 0.00588 -0.0569 0.7031 0.5147
-1.750 0.1020 0.01239 0.00592 -0.0543 0.6967 0.6328
-1.500 0.1267 0.01203 0.00595 -0.0531 0.6906 0.7491
-1.250 0.1825 0.01193 0.00599 -0.0579 0.6856 0.8483
-1.000 0.2373 0.01212 0.00616 -0.0630 0.6782 0.8935
-0.750 0.2842 0.01229 0.00619 -0.0664 0.6727 0.9211
-0.500 0.3312 0.01257 0.00638 -0.0699 0.6660 0.9381
-0.250 0.3790 0.01277 0.00645 -0.0736 0.6596 0.9526
0.000 0.4280 0.01296 0.00650 -0.0777 0.6540 0.9659
0.250 0.4811 0.01310 0.00657 -0.0829 0.6467 0.9788
0.500 0.5422 0.01308 0.00638 -0.0897 0.6411 0.9911
0.750 0.5930 0.01301 0.00629 -0.0950 0.6335 1.0000
1.000 0.6140 0.01301 0.00619 -0.0940 0.6280 1.0000
1.250 0.6344 0.01306 0.00621 -0.0930 0.6219 1.0000
1.500 0.6552 0.01311 0.00622 -0.0919 0.6156 1.0000
1.750 0.6781 0.01315 0.00615 -0.0912 0.6109 1.0000
2.000 0.6981 0.01327 0.00630 -0.0901 0.6042 1.0000
2.250 0.7204 0.01333 0.00631 -0.0892 0.5986 1.0000
2.500 0.7428 0.01344 0.00636 -0.0883 0.5933 1.0000
2.750 0.7635 0.01357 0.00651 -0.0872 0.5867 1.0000
3.000 0.7871 0.01367 0.00654 -0.0865 0.5817 1.0000
3.250 0.8082 0.01386 0.00675 -0.0855 0.5759 1.0000
3.500 0.8301 0.01400 0.00689 -0.0845 0.5700 1.0000
3.750 0.8547 0.01414 0.00694 -0.0840 0.5654 1.0000
4.000 0.8743 0.01436 0.00725 -0.0827 0.5589 1.0000
4.250 0.8972 0.01451 0.00737 -0.0819 0.5534 1.0000
4.500 0.9213 0.01471 0.00753 -0.0813 0.5489 1.0000
4.750 0.9409 0.01496 0.00788 -0.0800 0.5426 1.0000
5.000 0.9645 0.01513 0.00803 -0.0793 0.5376 1.0000
5.250 0.9874 0.01537 0.00827 -0.0785 0.5326 1.0000
5.500 1.0073 0.01564 0.00862 -0.0773 0.5266 1.0000
5.750 1.0315 0.01584 0.00881 -0.0767 0.5221 1.0000
6.000 1.0540 0.01613 0.00913 -0.0759 0.5173 1.0000
6.250 1.0735 0.01643 0.00953 -0.0745 0.5115 1.0000
6.500 1.0980 0.01663 0.00972 -0.0740 0.5069 1.0000
6.750 1.1202 0.01696 0.01011 -0.0732 0.5022 1.0000
7.000 1.1390 0.01729 0.01055 -0.0717 0.4965 1.0000
7.250 1.1634 0.01752 0.01079 -0.0712 0.4921 1.0000
7.500 1.1862 0.01786 0.01118 -0.0705 0.4876 1.0000
7.750 1.2036 0.01823 0.01171 -0.0688 0.4818 1.0000
8.000 1.2281 0.01843 0.01192 -0.0683 0.4768 1.0000
8.250 1.2477 0.01875 0.01233 -0.0670 0.4710 1.0000
8.500 1.2665 0.01894 0.01260 -0.0655 0.4639 1.0000
8.750 1.2843 0.01898 0.01269 -0.0637 0.4546 1.0000
9.000 1.2973 0.01877 0.01246 -0.0608 0.4403 1.0000
9.250 1.3047 0.01869 0.01238 -0.0571 0.4244 1.0000
9.500 1.3123 0.01882 0.01252 -0.0536 0.4104 1.0000
9.750 1.3219 0.01907 0.01277 -0.0506 0.3986 1.0000
10.000 1.3273 0.01945 0.01325 -0.0469 0.3875 1.0000
10.250 1.3305 0.01988 0.01375 -0.0429 0.3768 1.0000
10.500 1.3331 0.02041 0.01434 -0.0392 0.3641 1.0000
10.750 1.3346 0.02114 0.01510 -0.0357 0.3492 1.0000
11.000 1.3312 0.02220 0.01615 -0.0320 0.3279 1.0000
11.250 1.3287 0.02352 0.01747 -0.0289 0.3043 1.0000
11.500 1.3154 0.02569 0.01947 -0.0253 0.2663 1.0000
11.750 1.2934 0.02886 0.02236 -0.0218 0.2180 1.0000
12.000 1.2683 0.03274 0.02596 -0.0189 0.1754 1.0000
12.250 1.2439 0.03695 0.02993 -0.0167 0.1379 1.0000
12.500 1.2204 0.04140 0.03416 -0.0150 0.1029 1.0000
12.750 1.1919 0.04670 0.03919 -0.0137 0.0688 1.0000
13.000 1.1724 0.05139 0.04376 -0.0129 0.0528 1.0000
13.250 1.1619 0.05534 0.04771 -0.0125 0.0450 1.0000
13.500 1.1528 0.05928 0.05171 -0.0122 0.0405 1.0000
13.750 1.1449 0.06315 0.05563 -0.0121 0.0366 1.0000
14.000 1.1355 0.06730 0.05982 -0.0121 0.0332 1.0000
14.250 1.1337 0.07058 0.06321 -0.0122 0.0323 1.0000
14.500 1.1308 0.07402 0.06672 -0.0123 0.0301 1.0000
14.750 1.1274 0.07754 0.07030 -0.0124 0.0287 1.0000
15.000 1.1237 0.08103 0.07380 -0.0125 0.0276 1.0000
15.250 1.1229 0.08391 0.07668 -0.0120 0.0265 1.0000
15.500 1.1283 0.08617 0.07904 -0.0118 0.0258 1.0000
15.750 1.1344 0.08833 0.08127 -0.0115 0.0250 1.0000
16.000 1.1418 0.09022 0.08322 -0.0109 0.0241 1.0000
16.250 1.1519 0.09166 0.08471 -0.0101 0.0237 1.0000
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