FX 79-W-151 A (fx79w151a-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 79-W-151 A (fx79w151a-il) Reynolds number: 500,000 Max Cl/Cd: 104.09 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx79w151a-il-500000.txt Download as CSV file: xf-fx79w151a-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.6652 0.08648 0.08379 -0.0541 1.0000 0.0138
-14.750 -0.6937 0.07742 0.07462 -0.0599 1.0000 0.0139
-14.500 -0.7287 0.06728 0.06432 -0.0667 1.0000 0.0140
-14.250 -0.7327 0.06216 0.05911 -0.0706 1.0000 0.0137
-13.750 -0.7753 0.04678 0.04338 -0.0831 1.0000 0.0136
-13.500 -0.7918 0.04099 0.03738 -0.0879 1.0000 0.0138
-13.250 -0.7982 0.03759 0.03384 -0.0897 1.0000 0.0138
-13.000 -0.8098 0.03440 0.03050 -0.0900 1.0000 0.0138
-12.750 -0.8060 0.03133 0.02723 -0.0920 0.9830 0.0139
-12.500 -0.7892 0.02810 0.02380 -0.0960 0.9672 0.0146
-12.250 -0.7638 0.02645 0.02201 -0.0987 0.9533 0.0152
-12.000 -0.7469 0.02518 0.02056 -0.0987 0.9366 0.0155
-11.750 -0.7399 0.02411 0.01933 -0.0963 0.9206 0.0160
-11.500 -0.7329 0.02337 0.01844 -0.0933 0.9072 0.0164
-11.250 -0.7237 0.02264 0.01755 -0.0906 0.8958 0.0169
-11.000 -0.7126 0.02186 0.01659 -0.0882 0.8856 0.0173
-10.750 -0.7003 0.02111 0.01570 -0.0859 0.8756 0.0179
-10.500 -0.6927 0.01994 0.01440 -0.0830 0.8666 0.0186
-10.250 -0.6788 0.01918 0.01356 -0.0809 0.8579 0.0197
-10.000 -0.6604 0.01870 0.01298 -0.0794 0.8500 0.0209
-9.750 -0.6416 0.01818 0.01233 -0.0779 0.8423 0.0220
-9.500 -0.6263 0.01732 0.01135 -0.0759 0.8347 0.0237
-9.250 -0.6078 0.01672 0.01070 -0.0745 0.8271 0.0257
-9.000 -0.5866 0.01629 0.01017 -0.0733 0.8202 0.0279
-8.750 -0.5680 0.01562 0.00941 -0.0718 0.8126 0.0307
-8.500 -0.5465 0.01518 0.00891 -0.0708 0.8060 0.0334
-8.250 -0.5229 0.01491 0.00853 -0.0700 0.7986 0.0361
-8.000 -0.5029 0.01431 0.00789 -0.0687 0.7920 0.0403
-7.750 -0.4793 0.01402 0.00755 -0.0679 0.7846 0.0438
-7.500 -0.4570 0.01360 0.00706 -0.0669 0.7784 0.0482
-7.250 -0.4332 0.01330 0.00675 -0.0662 0.7713 0.0529
-7.000 -0.4097 0.01298 0.00634 -0.0654 0.7647 0.0580
-6.750 -0.3853 0.01274 0.00610 -0.0648 0.7579 0.0647
-6.500 -0.3612 0.01247 0.00581 -0.0641 0.7510 0.0717
-6.250 -0.3353 0.01236 0.00564 -0.0637 0.7446 0.0786
-6.000 -0.3111 0.01209 0.00539 -0.0631 0.7375 0.0862
-5.750 -0.2847 0.01204 0.00521 -0.0627 0.7314 0.0923
-5.500 -0.2605 0.01175 0.00496 -0.0620 0.7243 0.0993
-5.250 -0.2345 0.01166 0.00478 -0.0617 0.7181 0.1051
-5.000 -0.2096 0.01144 0.00455 -0.0611 0.7114 0.1115
-4.750 -0.1840 0.01131 0.00437 -0.0606 0.7049 0.1176
-4.500 -0.1581 0.01120 0.00418 -0.0602 0.6987 0.1229
-4.250 -0.1333 0.01098 0.00399 -0.0597 0.6918 0.1301
-4.000 -0.1069 0.01093 0.00382 -0.0593 0.6859 0.1361
-3.750 -0.0823 0.01069 0.00363 -0.0587 0.6792 0.1439
-3.500 -0.0561 0.01061 0.00348 -0.0584 0.6732 0.1512
-3.250 -0.0312 0.01042 0.00333 -0.0578 0.6671 0.1618
-3.000 -0.0059 0.01026 0.00317 -0.0573 0.6607 0.1727
-2.750 0.0194 0.01013 0.00303 -0.0568 0.6551 0.1863
-2.500 0.0445 0.00994 0.00292 -0.0563 0.6487 0.2059
-2.250 0.0691 0.00976 0.00279 -0.0557 0.6429 0.2351
-2.000 0.0933 0.00954 0.00271 -0.0551 0.6372 0.2771
-1.750 0.1167 0.00928 0.00263 -0.0543 0.6311 0.3311
-1.500 0.1388 0.00900 0.00254 -0.0533 0.6259 0.4049
-1.250 0.1595 0.00865 0.00252 -0.0519 0.6201 0.4944
-1.000 0.1796 0.00836 0.00249 -0.0504 0.6147 0.5774
-0.750 0.1988 0.00811 0.00247 -0.0485 0.6097 0.6591
-0.500 0.2184 0.00785 0.00250 -0.0466 0.6038 0.7399
-0.250 0.2439 0.00766 0.00253 -0.0459 0.5984 0.8166
0.000 0.2910 0.00762 0.00263 -0.0499 0.5928 0.8841
0.250 0.3460 0.00771 0.00273 -0.0557 0.5864 0.9157
0.500 0.3926 0.00787 0.00280 -0.0596 0.5807 0.9337
0.750 0.4336 0.00801 0.00292 -0.0623 0.5750 0.9445
1.000 0.4700 0.00819 0.00305 -0.0641 0.5694 0.9547
1.250 0.5029 0.00838 0.00316 -0.0651 0.5641 0.9645
1.500 0.5504 0.00855 0.00331 -0.0692 0.5579 0.9715
1.750 0.5938 0.00873 0.00343 -0.0725 0.5520 0.9789
2.000 0.6383 0.00888 0.00354 -0.0762 0.5463 0.9848
2.250 0.6856 0.00896 0.00360 -0.0804 0.5402 0.9898
2.500 0.7314 0.00908 0.00363 -0.0844 0.5346 0.9950
2.750 0.7729 0.00906 0.00363 -0.0876 0.5284 0.9986
3.000 0.8042 0.00910 0.00364 -0.0886 0.5226 1.0000
3.250 0.8261 0.00918 0.00370 -0.0877 0.5175 1.0000
3.500 0.8483 0.00923 0.00376 -0.0868 0.5121 1.0000
3.750 0.8704 0.00933 0.00383 -0.0859 0.5070 1.0000
4.000 0.8926 0.00943 0.00392 -0.0850 0.5019 1.0000
4.250 0.9149 0.00950 0.00401 -0.0841 0.4962 1.0000
4.500 0.9368 0.00963 0.00410 -0.0831 0.4911 1.0000
4.750 0.9592 0.00974 0.00423 -0.0822 0.4860 1.0000
5.000 0.9815 0.00984 0.00436 -0.0813 0.4808 1.0000
5.250 1.0034 0.01000 0.00448 -0.0803 0.4759 1.0000
5.500 1.0255 0.01013 0.00465 -0.0793 0.4709 1.0000
5.750 1.0475 0.01025 0.00480 -0.0784 0.4656 1.0000
6.000 1.0690 0.01044 0.00496 -0.0773 0.4607 1.0000
6.250 1.0908 0.01060 0.00516 -0.0763 0.4559 1.0000
6.500 1.1124 0.01075 0.00535 -0.0753 0.4507 1.0000
6.750 1.1337 0.01096 0.00555 -0.0742 0.4460 1.0000
7.000 1.1549 0.01113 0.00577 -0.0731 0.4409 1.0000
7.250 1.1752 0.01129 0.00597 -0.0718 0.4345 1.0000
7.500 1.1941 0.01150 0.00618 -0.0703 0.4267 1.0000
7.750 1.2114 0.01168 0.00636 -0.0685 0.4166 1.0000
8.000 1.2278 0.01187 0.00657 -0.0665 0.4043 1.0000
8.250 1.2429 0.01212 0.00681 -0.0643 0.3913 1.0000
8.500 1.2573 0.01241 0.00709 -0.0620 0.3786 1.0000
8.750 1.2710 0.01275 0.00741 -0.0596 0.3681 1.0000
9.000 1.2844 0.01308 0.00776 -0.0572 0.3566 1.0000
9.250 1.2928 0.01345 0.00811 -0.0538 0.3428 1.0000
9.500 1.3020 0.01385 0.00852 -0.0507 0.3302 1.0000
9.750 1.3057 0.01453 0.00912 -0.0471 0.3088 1.0000
10.000 1.3097 0.01539 0.00988 -0.0439 0.2830 1.0000
10.250 1.3071 0.01674 0.01104 -0.0402 0.2454 1.0000
10.500 1.2966 0.01876 0.01280 -0.0361 0.2004 1.0000
10.750 1.2812 0.02137 0.01513 -0.0322 0.1548 1.0000
11.000 1.2634 0.02444 0.01794 -0.0287 0.1088 1.0000
11.250 1.2566 0.02694 0.02031 -0.0265 0.0820 1.0000
11.500 1.2399 0.03040 0.02356 -0.0241 0.0490 1.0000
11.750 1.2281 0.03367 0.02673 -0.0223 0.0295 1.0000
12.000 1.2250 0.03629 0.02935 -0.0211 0.0234 1.0000
12.250 1.2240 0.03887 0.03197 -0.0201 0.0202 1.0000
12.500 1.2269 0.04113 0.03431 -0.0195 0.0190 1.0000
12.750 1.2245 0.04399 0.03722 -0.0188 0.0169 1.0000
13.000 1.2242 0.04673 0.04004 -0.0183 0.0163 1.0000
13.250 1.2224 0.04970 0.04310 -0.0179 0.0155 1.0000
13.500 1.2252 0.05220 0.04568 -0.0177 0.0150 1.0000
13.750 1.2263 0.05495 0.04850 -0.0175 0.0140 1.0000
14.000 1.2231 0.05826 0.05189 -0.0173 0.0132 1.0000
14.250 1.2241 0.06111 0.05482 -0.0173 0.0131 1.0000
14.500 1.2160 0.06509 0.05887 -0.0174 0.0125 1.0000
14.750 1.2067 0.06931 0.06319 -0.0175 0.0120 1.0000
15.000 1.2045 0.07270 0.06666 -0.0176 0.0119 1.0000
15.250 1.2079 0.07545 0.06949 -0.0179 0.0115 1.0000
15.500 1.2089 0.07848 0.07260 -0.0181 0.0112 1.0000
15.750 1.2068 0.08195 0.07614 -0.0184 0.0112 1.0000
16.000 1.2067 0.08518 0.07944 -0.0188 0.0109 1.0000
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