FX 77-W-121 (fx77w121-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 77-W-121 (fx77w121-il) Reynolds number: 500,000 Max Cl/Cd: 115.46 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx77w121-il-500000.txt Download as CSV file: xf-fx77w121-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2750 0.09274 0.08877 -0.0326 0.5129 0.0178
-8.750 -0.2713 0.08936 0.08538 -0.0338 0.5108 0.0178
-8.500 -0.2699 0.08594 0.08196 -0.0360 0.5095 0.0178
-8.250 -0.2691 0.08239 0.07843 -0.0379 0.5076 0.0179
-8.000 -0.2709 0.07876 0.07485 -0.0398 0.5061 0.0178
-7.750 -0.2866 0.07365 0.06979 -0.0403 0.5052 0.0184
-7.500 -0.2893 0.07006 0.06619 -0.0420 0.5039 0.0183
-7.250 -0.2821 0.06847 0.06460 -0.0408 0.5021 0.0191
-7.000 -0.2793 0.06488 0.06098 -0.0424 0.5007 0.0192
-6.750 -0.2735 0.06160 0.05765 -0.0436 0.4991 0.0194
-6.500 -0.2663 0.05833 0.05431 -0.0444 0.4978 0.0198
-6.250 -0.2576 0.05495 0.05085 -0.0450 0.4968 0.0210
-6.000 -0.2475 0.05132 0.04709 -0.0455 0.4955 0.0215
-5.750 -0.2359 0.04769 0.04329 -0.0455 0.4941 0.0220
-5.500 -0.2144 0.04384 0.03908 -0.0447 0.4931 0.0242
-5.250 -0.2020 0.04051 0.03550 -0.0433 0.4919 0.0243
-5.000 -0.2040 0.03354 0.02822 -0.0410 0.4910 0.0254
-4.750 -0.1866 0.03153 0.02608 -0.0399 0.4895 0.0259
-4.500 -0.1677 0.02997 0.02441 -0.0389 0.4882 0.0267
-4.250 -0.1473 0.02878 0.02310 -0.0379 0.4868 0.0285
-4.000 -0.1336 0.02316 0.01674 -0.0336 0.4859 0.0228
-3.750 -0.1168 0.01932 0.01233 -0.0308 0.4849 0.0207
-3.500 -0.0932 0.01769 0.01039 -0.0295 0.4837 0.0212
-3.250 -0.0678 0.01670 0.00919 -0.0286 0.4825 0.0225
-3.000 -0.0418 0.01591 0.00820 -0.0279 0.4813 0.0235
-2.750 -0.0167 0.01483 0.00695 -0.0272 0.4798 0.0260
-2.500 0.0091 0.01436 0.00645 -0.0267 0.4785 0.0278
-2.250 0.0353 0.01388 0.00593 -0.0261 0.4774 0.0297
-2.000 0.0615 0.01353 0.00552 -0.0256 0.4764 0.0321
-1.750 0.0866 0.01301 0.00495 -0.0248 0.4753 0.0346
-1.500 0.1115 0.01259 0.00452 -0.0241 0.4742 0.0383
-1.250 0.1374 0.01237 0.00427 -0.0236 0.4730 0.0417
-1.000 0.1636 0.01221 0.00407 -0.0231 0.4718 0.0453
-0.750 0.1889 0.01192 0.00377 -0.0224 0.4707 0.0523
-0.500 0.2150 0.01175 0.00359 -0.0219 0.4694 0.0642
-0.250 0.2379 0.01120 0.00347 -0.0210 0.4682 0.1899
0.000 0.2516 0.01007 0.00344 -0.0186 0.4671 0.5433
0.250 0.4409 0.00970 0.00399 -0.0531 0.4644 0.9966
0.500 0.4827 0.00970 0.00394 -0.0561 0.4634 1.0000
0.750 0.5080 0.00976 0.00396 -0.0556 0.4625 1.0000
1.000 0.5332 0.00982 0.00399 -0.0551 0.4614 1.0000
1.250 0.5586 0.00989 0.00404 -0.0546 0.4603 1.0000
1.500 0.5839 0.00995 0.00407 -0.0542 0.4586 1.0000
1.750 0.6094 0.01004 0.00414 -0.0537 0.4574 1.0000
2.000 0.6349 0.01010 0.00418 -0.0533 0.4558 1.0000
2.250 0.6605 0.01017 0.00421 -0.0529 0.4541 1.0000
2.500 0.6862 0.01027 0.00427 -0.0525 0.4527 1.0000
2.750 0.7119 0.01041 0.00437 -0.0521 0.4515 1.0000
3.000 0.7375 0.01066 0.00458 -0.0517 0.4497 1.0000
3.250 0.7628 0.01076 0.00471 -0.0513 0.4485 1.0000
3.500 0.7881 0.01083 0.00481 -0.0509 0.4469 1.0000
3.750 0.8134 0.01090 0.00492 -0.0504 0.4449 1.0000
4.000 0.8388 0.01096 0.00500 -0.0500 0.4427 1.0000
4.250 0.8643 0.01104 0.00508 -0.0496 0.4408 1.0000
4.500 0.8900 0.01112 0.00517 -0.0492 0.4389 1.0000
4.750 0.9157 0.01124 0.00526 -0.0489 0.4370 1.0000
5.000 0.9411 0.01149 0.00549 -0.0486 0.4345 1.0000
5.250 0.9660 0.01149 0.00558 -0.0480 0.4322 1.0000
5.500 0.9910 0.01158 0.00575 -0.0476 0.4301 1.0000
5.750 1.0162 0.01169 0.00591 -0.0472 0.4280 1.0000
6.000 1.0415 0.01179 0.00605 -0.0468 0.4260 1.0000
6.250 1.0670 0.01189 0.00617 -0.0465 0.4241 1.0000
6.500 1.0927 0.01201 0.00631 -0.0462 0.4221 1.0000
6.750 1.1179 0.01224 0.00655 -0.0458 0.4196 1.0000
7.000 1.1422 0.01230 0.00674 -0.0453 0.4172 1.0000
7.250 1.1667 0.01238 0.00692 -0.0448 0.4144 1.0000
7.500 1.1917 0.01244 0.00707 -0.0444 0.4117 1.0000
7.750 1.2169 0.01246 0.00712 -0.0440 0.4087 1.0000
8.000 1.2418 0.01244 0.00712 -0.0435 0.4042 1.0000
8.250 1.2656 0.01212 0.00693 -0.0427 0.3962 1.0000
8.500 1.2899 0.01190 0.00678 -0.0421 0.3880 1.0000
8.750 1.3143 0.01167 0.00663 -0.0415 0.3754 1.0000
9.000 1.3382 0.01159 0.00658 -0.0409 0.3541 1.0000
9.250 1.3578 0.01193 0.00679 -0.0398 0.3227 1.0000
9.500 1.3704 0.01289 0.00752 -0.0379 0.2779 1.0000
9.750 1.3760 0.01442 0.00876 -0.0351 0.2252 1.0000
10.000 1.3782 0.01608 0.01016 -0.0321 0.1764 1.0000
10.250 1.3602 0.01882 0.01243 -0.0267 0.1056 1.0000
10.500 1.3355 0.02137 0.01476 -0.0207 0.0665 1.0000
10.750 1.3145 0.02443 0.01779 -0.0178 0.0477 1.0000
11.000 1.2941 0.02932 0.02264 -0.0183 0.0288 1.0000
11.250 1.2795 0.03375 0.02709 -0.0186 0.0206 1.0000
11.500 1.2729 0.03722 0.03065 -0.0187 0.0178 1.0000
11.750 1.2659 0.04065 0.03414 -0.0187 0.0152 1.0000
12.000 1.2520 0.04482 0.03840 -0.0186 0.0125 1.0000
12.250 1.2467 0.04807 0.04175 -0.0186 0.0128 1.0000
12.500 1.2466 0.05075 0.04451 -0.0186 0.0123 1.0000
12.750 1.2411 0.05404 0.04788 -0.0186 0.0112 1.0000
13.000 1.2356 0.05746 0.05137 -0.0187 0.0105 1.0000
13.250 1.2281 0.06123 0.05520 -0.0190 0.0097 1.0000
13.500 1.2230 0.06484 0.05890 -0.0194 0.0095 1.0000
13.750 1.2163 0.06871 0.06286 -0.0198 0.0094 1.0000
14.000 1.2100 0.07262 0.06686 -0.0203 0.0087 1.0000
14.250 1.2085 0.07591 0.07023 -0.0207 0.0086 1.0000
14.500 1.2072 0.07929 0.07369 -0.0212 0.0080 1.0000
14.750 1.2084 0.08228 0.07677 -0.0217 0.0081 1.0000
15.000 1.2037 0.08609 0.08065 -0.0222 0.0081 1.0000
15.250 1.2017 0.08958 0.08422 -0.0227 0.0079 1.0000
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