FX 77-W-121 (fx77w121-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 77-W-121 (fx77w121-il) Reynolds number: 100,000 Max Cl/Cd: 19 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx77w121-il-100000.txt Download as CSV file: xf-fx77w121-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 77-W-121
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2870 0.10973 0.10482 -0.0259 0.7112 0.0703
-9.250 -0.2923 0.10821 0.10333 -0.0303 0.7048 0.0711
-9.000 -0.2948 0.10585 0.10098 -0.0338 0.6991 0.0714
-8.750 -0.2704 0.09927 0.09433 -0.0306 0.6911 0.0742
-8.500 -0.2585 0.09617 0.09117 -0.0303 0.6854 0.0777
-8.250 -0.2547 0.09331 0.08833 -0.0317 0.6800 0.0809
-8.000 -0.2568 0.09085 0.08590 -0.0342 0.6757 0.0838
-7.750 -0.2737 0.08909 0.08418 -0.0390 0.6730 0.0855
-7.500 -0.2830 0.08704 0.08211 -0.0436 0.6695 0.0860
-7.250 -0.2622 0.08134 0.07647 -0.0397 0.6642 0.0891
-7.000 -0.2520 0.07845 0.07355 -0.0392 0.6602 0.0924
-6.750 -0.2480 0.07571 0.07074 -0.0408 0.6570 0.0958
-6.500 -0.2613 0.07449 0.06924 -0.0484 0.6546 0.1010
-6.250 -0.2426 0.06890 0.06388 -0.0457 0.6506 0.1040
-6.000 -0.2298 0.06632 0.06127 -0.0451 0.6474 0.1086
-5.750 -0.2277 0.06363 0.05825 -0.0488 0.6453 0.1169
-5.500 -0.2112 0.06028 0.05501 -0.0469 0.6426 0.1214
-5.250 -0.2020 0.05765 0.05215 -0.0485 0.6398 0.1326
-5.000 -0.1852 0.05499 0.04959 -0.0475 0.6364 0.1392
-4.750 -0.1720 0.05246 0.04693 -0.0474 0.6335 0.1513
-4.500 -0.1575 0.05025 0.04462 -0.0467 0.6308 0.1676
-4.250 -0.1448 0.04838 0.04255 -0.0460 0.6287 0.1935
-4.000 -0.1284 0.04620 0.04041 -0.0447 0.6265 0.2128
-3.750 -0.1136 0.04446 0.03865 -0.0437 0.6241 0.2404
-3.500 -0.0985 0.04271 0.03696 -0.0420 0.6217 0.2724
-3.250 -0.0482 0.03442 0.02615 -0.0426 0.6200 0.0850
-3.000 -0.0252 0.03251 0.02388 -0.0414 0.6176 0.0845
-2.750 -0.0007 0.03079 0.02175 -0.0402 0.6153 0.0844
-2.500 0.0253 0.02927 0.01987 -0.0393 0.6132 0.0837
-2.250 0.0519 0.02844 0.01877 -0.0388 0.6108 0.0856
-2.000 0.0782 0.02736 0.01769 -0.0390 0.6086 0.0922
-1.750 0.1058 0.02670 0.01696 -0.0389 0.6064 0.0968
-1.500 0.1324 0.02608 0.01634 -0.0387 0.6040 0.1050
-1.250 0.3000 0.02096 0.01400 -0.0650 0.5996 1.0000
-1.000 0.3237 0.02143 0.01414 -0.0644 0.5977 1.0000
-0.750 0.3471 0.02213 0.01471 -0.0645 0.5955 1.0000
-0.500 0.3704 0.02286 0.01531 -0.0646 0.5935 1.0000
-0.250 0.3933 0.02356 0.01587 -0.0644 0.5909 1.0000
0.000 0.4160 0.02416 0.01634 -0.0640 0.5883 1.0000
0.250 0.4388 0.02474 0.01676 -0.0634 0.5861 1.0000
0.500 0.4616 0.02536 0.01725 -0.0628 0.5845 1.0000
0.750 0.4832 0.02627 0.01808 -0.0626 0.5823 1.0000
1.000 0.5023 0.02766 0.01952 -0.0630 0.5789 1.0000
1.250 0.5218 0.02886 0.02069 -0.0630 0.5760 1.0000
1.500 0.5423 0.02973 0.02149 -0.0625 0.5730 1.0000
1.750 0.5641 0.03037 0.02204 -0.0616 0.5706 1.0000
2.000 0.5870 0.03090 0.02247 -0.0606 0.5687 1.0000
2.250 0.5947 0.03370 0.02540 -0.0614 0.5646 1.0000
2.500 0.6048 0.03584 0.02758 -0.0614 0.5608 1.0000
2.750 0.6204 0.03721 0.02894 -0.0607 0.5578 1.0000
3.000 0.6438 0.03766 0.02931 -0.0595 0.5552 1.0000
3.250 0.6455 0.04050 0.03220 -0.0591 0.5506 1.0000
3.500 0.6312 0.04455 0.03633 -0.0587 0.5461 1.0000
3.750 0.6563 0.04485 0.03658 -0.0575 0.5417 1.0000
4.000 0.7010 0.04338 0.03501 -0.0560 0.5390 1.0000
4.250 0.5561 0.05740 0.04920 -0.0537 0.5578 1.0000
4.500 0.5710 0.05922 0.05100 -0.0532 0.5559 1.0000
4.750 0.5900 0.06113 0.05291 -0.0530 0.5545 1.0000
5.000 0.6298 0.05818 0.04987 -0.0496 0.5192 1.0000
5.250 0.6208 0.06117 0.05286 -0.0484 0.5162 1.0000
5.750 0.6205 0.06673 0.05844 -0.0473 0.5137 1.0000
6.000 0.6294 0.06908 0.06083 -0.0471 0.5120 1.0000
6.250 0.6826 0.06574 0.05744 -0.0442 0.4832 1.0000
6.500 0.6985 0.06689 0.05860 -0.0432 0.4752 1.0000
6.750 0.7106 0.06830 0.06004 -0.0424 0.4678 1.0000
7.000 0.7165 0.07013 0.06191 -0.0414 0.4589 1.0000
7.250 0.7368 0.07105 0.06286 -0.0406 0.4527 1.0000
7.500 0.7965 0.06901 0.06089 -0.0395 0.4494 1.0000
7.750 0.7550 0.07466 0.06654 -0.0392 0.4381 1.0000
8.000 0.8072 0.07301 0.06499 -0.0379 0.4345 1.0000
8.250 0.7817 0.07739 0.06938 -0.0377 0.4228 1.0000
8.500 0.8231 0.07662 0.06870 -0.0365 0.4195 1.0000
8.750 0.7932 0.08180 0.07389 -0.0369 0.4086 1.0000
9.000 0.8258 0.08164 0.07381 -0.0357 0.4040 1.0000
9.250 0.8120 0.08548 0.07769 -0.0359 0.3941 1.0000
9.500 0.8343 0.08625 0.07856 -0.0350 0.3889 1.0000
9.750 0.8231 0.09023 0.08258 -0.0355 0.3807 1.0000
10.000 0.8506 0.09026 0.08271 -0.0344 0.3752 1.0000
10.250 0.8375 0.09466 0.08715 -0.0351 0.3674 1.0000
10.500 0.8779 0.09336 0.08599 -0.0335 0.3640 1.0000
10.750 0.8511 0.09928 0.09193 -0.0348 0.3541 1.0000
11.000 0.8900 0.09801 0.09080 -0.0332 0.3506 1.0000
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Polar data table (+)
Polar graphs
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