FX 77-W-121 (fx77w121-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 77-W-121 (fx77w121-il) Reynolds number: 100,000 Max Cl/Cd: 37.46 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx77w121-il-100000-n5.txt Download as CSV file: xf-fx77w121-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3140 0.11286 0.10719 -0.0208 0.6106 0.0439
-9.500 -0.3141 0.11009 0.10444 -0.0241 0.6053 0.0442
-9.250 -0.3127 0.10717 0.10151 -0.0270 0.6006 0.0444
-9.000 -0.3087 0.10363 0.09797 -0.0291 0.5962 0.0444
-8.750 -0.2895 0.09800 0.09229 -0.0257 0.5900 0.0465
-8.500 -0.2788 0.09502 0.08927 -0.0257 0.5856 0.0486
-8.250 -0.2744 0.09186 0.08609 -0.0271 0.5823 0.0497
-8.000 -0.2710 0.08882 0.08309 -0.0286 0.5786 0.0510
-7.750 -0.2703 0.08555 0.07984 -0.0304 0.5755 0.0520
-7.500 -0.2706 0.08238 0.07668 -0.0322 0.5727 0.0524
-7.250 -0.2745 0.07925 0.07355 -0.0338 0.5704 0.0534
-7.000 -0.2727 0.07580 0.07006 -0.0358 0.5680 0.0534
-6.750 -0.2680 0.07230 0.06655 -0.0378 0.5651 0.0532
-6.500 -0.2680 0.06357 0.05755 -0.0431 0.5640 0.0325
-6.250 -0.2600 0.06006 0.05397 -0.0432 0.5613 0.0316
-6.000 -0.2503 0.05656 0.05033 -0.0436 0.5588 0.0307
-5.750 -0.2397 0.05281 0.04637 -0.0438 0.5564 0.0299
-5.500 -0.2281 0.04888 0.04217 -0.0436 0.5544 0.0294
-5.250 -0.2150 0.04512 0.03810 -0.0430 0.5520 0.0289
-5.000 -0.2001 0.04171 0.03434 -0.0421 0.5492 0.0291
-4.750 -0.1835 0.03872 0.03096 -0.0409 0.5466 0.0304
-4.500 -0.1658 0.03587 0.02761 -0.0394 0.5443 0.0316
-4.250 -0.1469 0.03325 0.02448 -0.0378 0.5421 0.0321
-4.000 -0.1262 0.03094 0.02162 -0.0362 0.5402 0.0326
-3.750 -0.1037 0.02911 0.01929 -0.0349 0.5385 0.0331
-3.500 -0.0810 0.02722 0.01717 -0.0341 0.5362 0.0348
-3.250 -0.0567 0.02631 0.01614 -0.0336 0.5337 0.0380
-3.000 -0.0308 0.02512 0.01464 -0.0329 0.5312 0.0404
-2.750 -0.0038 0.02393 0.01316 -0.0323 0.5289 0.0424
-2.500 0.0228 0.02299 0.01201 -0.0318 0.5267 0.0457
-2.250 0.0486 0.02225 0.01123 -0.0314 0.5250 0.0501
-2.000 0.0747 0.02158 0.01042 -0.0308 0.5234 0.0536
-1.750 0.0997 0.02106 0.00986 -0.0302 0.5214 0.0592
-1.500 0.1243 0.02066 0.00947 -0.0296 0.5194 0.0664
-1.250 0.1492 0.02028 0.00903 -0.0289 0.5172 0.0741
-1.000 0.1748 0.01995 0.00871 -0.0284 0.5150 0.0923
-0.750 0.3331 0.01696 0.00820 -0.0550 0.5115 1.0000
-0.500 0.3577 0.01714 0.00813 -0.0544 0.5100 1.0000
-0.250 0.3825 0.01734 0.00812 -0.0539 0.5087 1.0000
0.000 0.4069 0.01760 0.00827 -0.0534 0.5068 1.0000
0.250 0.4313 0.01786 0.00845 -0.0529 0.5047 1.0000
0.500 0.4557 0.01812 0.00861 -0.0524 0.5023 1.0000
0.750 0.4801 0.01837 0.00876 -0.0519 0.5003 1.0000
1.000 0.5046 0.01864 0.00893 -0.0514 0.4985 1.0000
1.250 0.5291 0.01891 0.00910 -0.0509 0.4969 1.0000
1.500 0.5538 0.01919 0.00928 -0.0504 0.4955 1.0000
1.750 0.5785 0.01947 0.00946 -0.0499 0.4941 1.0000
2.000 0.6019 0.01990 0.00991 -0.0495 0.4917 1.0000
2.250 0.6253 0.02032 0.01037 -0.0490 0.4891 1.0000
2.500 0.6489 0.02074 0.01079 -0.0485 0.4869 1.0000
2.750 0.6727 0.02111 0.01115 -0.0480 0.4847 1.0000
3.000 0.6968 0.02144 0.01146 -0.0475 0.4827 1.0000
3.250 0.7212 0.02172 0.01169 -0.0469 0.4808 1.0000
3.500 0.7460 0.02200 0.01191 -0.0464 0.4791 1.0000
3.750 0.7669 0.02269 0.01274 -0.0459 0.4758 1.0000
4.000 0.7888 0.02328 0.01343 -0.0453 0.4728 1.0000
4.250 0.8115 0.02374 0.01393 -0.0447 0.4701 1.0000
4.500 0.8350 0.02411 0.01432 -0.0441 0.4679 1.0000
4.750 0.8593 0.02439 0.01459 -0.0436 0.4658 1.0000
5.000 0.8836 0.02471 0.01493 -0.0430 0.4639 1.0000
5.250 0.9004 0.02572 0.01616 -0.0422 0.4591 1.0000
5.500 0.9218 0.02623 0.01676 -0.0415 0.4555 1.0000
6.000 0.9707 0.02661 0.01720 -0.0403 0.4505 1.0000
6.250 0.9879 0.02753 0.01830 -0.0394 0.4462 1.0000
6.500 1.0054 0.02834 0.01927 -0.0385 0.4416 1.0000
6.750 1.0283 0.02862 0.01962 -0.0377 0.4385 1.0000
7.000 1.0539 0.02865 0.01972 -0.0372 0.4361 1.0000
7.250 1.0680 0.02970 0.02096 -0.0360 0.4309 1.0000
7.500 1.0842 0.03047 0.02190 -0.0349 0.4257 1.0000
7.750 1.1087 0.03051 0.02202 -0.0342 0.4227 1.0000
8.000 1.1363 0.03033 0.02193 -0.0337 0.4205 1.0000
8.250 1.1351 0.03249 0.02440 -0.0316 0.4123 1.0000
8.500 1.1564 0.03274 0.02477 -0.0308 0.4087 1.0000
8.750 1.1842 0.03245 0.02458 -0.0302 0.4062 1.0000
9.000 1.1737 0.03510 0.02751 -0.0276 0.3971 1.0000
9.250 1.1966 0.03506 0.02759 -0.0266 0.3934 1.0000
9.500 1.2108 0.03567 0.02840 -0.0253 0.3888 1.0000
9.750 1.1248 0.04425 0.03699 -0.0212 0.3714 1.0000
10.250 1.1113 0.05049 0.04338 -0.0209 0.3530 1.0000
10.500 1.1385 0.04957 0.04265 -0.0197 0.3510 1.0000
11.000 1.1494 0.05306 0.04637 -0.0188 0.3368 1.0000
11.500 1.1504 0.05784 0.05135 -0.0183 0.3195 1.0000
11.750 1.1689 0.05761 0.05127 -0.0175 0.3098 1.0000
12.000 1.1897 0.05675 0.05050 -0.0167 0.2921 1.0000
12.250 1.1942 0.05825 0.05197 -0.0163 0.2716 1.0000
12.500 1.2000 0.05950 0.05310 -0.0157 0.2464 1.0000
12.750 1.1977 0.06187 0.05530 -0.0153 0.2204 1.0000
13.000 1.1883 0.06531 0.05859 -0.0153 0.1953 1.0000
13.250 1.1770 0.06932 0.06246 -0.0156 0.1694 1.0000
13.500 1.1644 0.07369 0.06664 -0.0162 0.1392 1.0000
13.750 1.1495 0.07855 0.07127 -0.0170 0.1098 1.0000
14.000 1.1314 0.08405 0.07653 -0.0181 0.0824 1.0000
14.250 1.1155 0.08944 0.08173 -0.0192 0.0601 1.0000
14.500 1.1029 0.09456 0.08676 -0.0203 0.0476 1.0000
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Polar data table (+)
Polar graphs
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