FX 84-W-127 (fx84w127-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 84-W-127 (fx84w127-il) Reynolds number: 200,000 Max Cl/Cd: 79.76 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx84w127-il-200000-n5.txt Download as CSV file: xf-fx84w127-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 84-W-127
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3342 0.09111 0.08757 -0.0574 0.9651 0.0212
-10.250 -0.4909 0.04637 0.04250 -0.0940 0.9225 0.0197
-10.000 -0.5230 0.04120 0.03691 -0.0940 0.9025 0.0196
-9.750 -0.5274 0.03833 0.03378 -0.0932 0.8910 0.0198
-9.500 -0.5238 0.03611 0.03130 -0.0921 0.8823 0.0201
-9.250 -0.5156 0.03407 0.02901 -0.0913 0.8734 0.0205
-9.000 -0.5062 0.03192 0.02653 -0.0903 0.8662 0.0210
-8.750 -0.4937 0.02981 0.02409 -0.0894 0.8585 0.0216
-8.250 -0.4621 0.02595 0.01937 -0.0876 0.8453 0.0238
-8.000 -0.4425 0.02461 0.01784 -0.0870 0.8396 0.0246
-7.750 -0.4205 0.02372 0.01683 -0.0865 0.8338 0.0255
-7.500 -0.3981 0.02273 0.01567 -0.0860 0.8276 0.0264
-7.250 -0.3755 0.02168 0.01438 -0.0854 0.8225 0.0276
-7.000 -0.3515 0.02075 0.01319 -0.0850 0.8167 0.0292
-6.750 -0.3278 0.01992 0.01227 -0.0846 0.8110 0.0307
-6.500 -0.3034 0.01931 0.01157 -0.0842 0.8064 0.0322
-6.250 -0.2784 0.01861 0.01076 -0.0839 0.8004 0.0340
-6.000 -0.2531 0.01796 0.00993 -0.0835 0.7950 0.0359
-5.750 -0.2284 0.01732 0.00924 -0.0831 0.7907 0.0382
-5.500 -0.2025 0.01688 0.00876 -0.0829 0.7848 0.0410
-5.250 -0.1767 0.01639 0.00814 -0.0826 0.7795 0.0437
-5.000 -0.1514 0.01586 0.00756 -0.0823 0.7752 0.0470
-4.750 -0.1251 0.01550 0.00716 -0.0822 0.7695 0.0511
-4.500 -0.0990 0.01508 0.00667 -0.0819 0.7642 0.0552
-4.250 -0.0728 0.01472 0.00627 -0.0817 0.7598 0.0608
-4.000 -0.0463 0.01439 0.00591 -0.0815 0.7539 0.0670
-3.750 -0.0198 0.01408 0.00558 -0.0814 0.7486 0.0749
-3.500 0.0068 0.01378 0.00525 -0.0812 0.7442 0.0847
-3.250 0.0336 0.01351 0.00500 -0.0811 0.7382 0.0969
-3.000 0.0604 0.01325 0.00476 -0.0810 0.7329 0.1134
-2.750 0.0873 0.01300 0.00451 -0.0809 0.7286 0.1351
-2.500 0.1139 0.01274 0.00436 -0.0809 0.7225 0.1644
-2.250 0.1405 0.01245 0.00419 -0.0808 0.7173 0.2041
-2.000 0.1670 0.01214 0.00401 -0.0807 0.7130 0.2597
-1.750 0.1926 0.01173 0.00392 -0.0807 0.7070 0.3446
-1.500 0.2170 0.01120 0.00384 -0.0803 0.7018 0.4724
-1.250 0.2404 0.01077 0.00385 -0.0793 0.6974 0.6063
-1.000 0.2639 0.01058 0.00396 -0.0782 0.6915 0.6976
-0.750 0.2884 0.01052 0.00399 -0.0771 0.6864 0.7559
-0.500 0.3132 0.01051 0.00400 -0.0760 0.6818 0.7966
-0.250 0.3376 0.01052 0.00406 -0.0750 0.6758 0.8293
0.000 0.3623 0.01054 0.00406 -0.0740 0.6706 0.8570
0.250 0.3871 0.01057 0.00406 -0.0730 0.6656 0.8820
0.500 0.4127 0.01059 0.00409 -0.0722 0.6595 0.9043
0.750 0.4413 0.01061 0.00407 -0.0719 0.6543 0.9330
1.000 0.4771 0.01064 0.00407 -0.0733 0.6487 0.9578
1.250 0.5146 0.01067 0.00407 -0.0753 0.6425 0.9693
1.500 0.5521 0.01070 0.00401 -0.0774 0.6375 0.9776
1.750 0.5888 0.01075 0.00405 -0.0795 0.6311 0.9862
2.000 0.6256 0.01080 0.00406 -0.0815 0.6254 0.9941
2.250 0.6582 0.01086 0.00408 -0.0828 0.6200 1.0000
2.500 0.6796 0.01096 0.00417 -0.0818 0.6136 1.0000
2.750 0.7023 0.01107 0.00423 -0.0809 0.6082 1.0000
3.000 0.7255 0.01119 0.00435 -0.0802 0.6022 1.0000
3.250 0.7496 0.01131 0.00445 -0.0796 0.5956 1.0000
3.500 0.7746 0.01144 0.00455 -0.0792 0.5897 1.0000
3.750 0.7995 0.01157 0.00471 -0.0788 0.5824 1.0000
4.250 0.8505 0.01186 0.00501 -0.0782 0.5691 1.0000
4.500 0.8764 0.01201 0.00514 -0.0779 0.5626 1.0000
4.750 0.9018 0.01218 0.00535 -0.0776 0.5553 1.0000
5.000 0.9275 0.01234 0.00551 -0.0774 0.5482 1.0000
5.250 0.9527 0.01251 0.00573 -0.0770 0.5395 1.0000
5.500 0.9780 0.01269 0.00589 -0.0766 0.5311 1.0000
5.750 1.0026 0.01288 0.00615 -0.0762 0.5214 1.0000
6.000 1.0275 0.01309 0.00638 -0.0758 0.5129 1.0000
6.250 1.0520 0.01330 0.00664 -0.0754 0.5035 1.0000
6.500 1.0759 0.01352 0.00691 -0.0748 0.4925 1.0000
6.750 1.0975 0.01376 0.00713 -0.0739 0.4743 1.0000
7.000 1.1169 0.01407 0.00738 -0.0725 0.4496 1.0000
7.250 1.1353 0.01446 0.00769 -0.0711 0.4252 1.0000
7.500 1.1538 0.01487 0.00807 -0.0698 0.4019 1.0000
7.750 1.1699 0.01538 0.00850 -0.0681 0.3761 1.0000
8.000 1.1832 0.01599 0.00902 -0.0660 0.3474 1.0000
8.250 1.1933 0.01672 0.00963 -0.0635 0.3153 1.0000
8.500 1.1968 0.01760 0.01035 -0.0600 0.2814 1.0000
8.750 1.1982 0.01868 0.01125 -0.0565 0.2479 1.0000
9.000 1.1986 0.01996 0.01235 -0.0532 0.2122 1.0000
9.250 1.1990 0.02139 0.01363 -0.0503 0.1796 1.0000
9.500 1.1987 0.02300 0.01506 -0.0476 0.1467 1.0000
9.750 1.1990 0.02469 0.01659 -0.0452 0.1178 1.0000
10.250 1.2039 0.02807 0.01978 -0.0413 0.0796 1.0000
10.500 1.2081 0.02973 0.02142 -0.0397 0.0677 1.0000
11.000 1.2187 0.03309 0.02482 -0.0371 0.0526 1.0000
11.250 1.2228 0.03495 0.02670 -0.0358 0.0478 1.0000
11.500 1.2290 0.03669 0.02851 -0.0348 0.0436 1.0000
11.750 1.2324 0.03872 0.03057 -0.0338 0.0405 1.0000
12.000 1.2369 0.04071 0.03265 -0.0330 0.0381 1.0000
12.250 1.2419 0.04269 0.03472 -0.0322 0.0356 1.0000
12.500 1.2450 0.04492 0.03700 -0.0315 0.0334 1.0000
12.750 1.2455 0.04750 0.03964 -0.0309 0.0319 1.0000
13.000 1.2509 0.04966 0.04192 -0.0305 0.0302 1.0000
13.250 1.2544 0.05205 0.04442 -0.0302 0.0289 1.0000
13.500 1.2581 0.05450 0.04695 -0.0299 0.0276 1.0000
13.750 1.2597 0.05725 0.04977 -0.0298 0.0265 1.0000
14.000 1.2597 0.06024 0.05280 -0.0298 0.0254 1.0000
14.250 1.2640 0.06280 0.05550 -0.0297 0.0244 1.0000
14.500 1.2676 0.06550 0.05831 -0.0298 0.0234 1.0000
14.750 1.2706 0.06831 0.06123 -0.0300 0.0226 1.0000
15.000 1.2730 0.07123 0.06425 -0.0303 0.0219 1.0000
15.250 1.2744 0.07435 0.06744 -0.0308 0.0212 1.0000
15.500 1.2747 0.07764 0.07078 -0.0312 0.0206 1.0000
15.750 1.2774 0.08066 0.07391 -0.0316 0.0200 1.0000
16.000 1.2803 0.08371 0.07712 -0.0321 0.0194 1.0000
16.250 1.2828 0.08686 0.08039 -0.0327 0.0188 1.0000
16.500 1.2847 0.09015 0.08381 -0.0335 0.0182 1.0000
16.750 1.2857 0.09366 0.08742 -0.0345 0.0176 1.0000
17.000 1.2863 0.09726 0.09113 -0.0357 0.0171 1.0000
17.250 1.2867 0.10089 0.09486 -0.0368 0.0167 1.0000
17.500 1.2868 0.10457 0.09862 -0.0381 0.0164 1.0000
17.750 1.2866 0.10831 0.10244 -0.0392 0.0160 1.0000
18.000 1.2856 0.11239 0.10671 -0.0407 0.0157 1.0000
18.250 1.2834 0.11672 0.11123 -0.0425 0.0154 1.0000
18.500 1.2805 0.12124 0.11594 -0.0445 0.0151 1.0000
18.750 1.2762 0.12610 0.12098 -0.0468 0.0149 1.0000
19.000 1.2709 0.13127 0.12633 -0.0494 0.0146 1.0000
19.250 1.2649 0.13667 0.13189 -0.0524 0.0143 1.0000
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