GOE 777 AIRFOIL (goe777-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 777 AIRFOIL (goe777-il) Reynolds number: 1,000,000 Max Cl/Cd: 101.81 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe777-il-1000000-n5.txt Download as CSV file: xf-goe777-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 777 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.0824 0.07117 0.06665 -0.0704 0.7348 0.0219
-19.500 -1.1021 0.06492 0.06023 -0.0741 0.7206 0.0220
-19.250 -1.1155 0.05961 0.05475 -0.0773 0.7064 0.0221
-19.000 -1.1260 0.05484 0.04984 -0.0801 0.6928 0.0223
-18.750 -1.1326 0.05078 0.04563 -0.0823 0.6799 0.0225
-18.500 -1.1360 0.04730 0.04200 -0.0841 0.6655 0.0226
-18.250 -1.1370 0.04421 0.03879 -0.0855 0.6519 0.0228
-18.000 -1.1358 0.04146 0.03590 -0.0866 0.6377 0.0230
-17.750 -1.1325 0.03901 0.03333 -0.0875 0.6225 0.0232
-17.500 -1.1274 0.03680 0.03100 -0.0881 0.6087 0.0233
-17.250 -1.1204 0.03483 0.02890 -0.0887 0.5954 0.0235
-17.000 -1.1121 0.03304 0.02700 -0.0890 0.5839 0.0236
-16.750 -1.1053 0.03116 0.02502 -0.0893 0.5745 0.0239
-16.500 -1.0972 0.02946 0.02325 -0.0893 0.5668 0.0241
-16.250 -1.0872 0.02801 0.02171 -0.0892 0.5589 0.0243
-16.000 -1.0758 0.02674 0.02037 -0.0889 0.5525 0.0246
-15.750 -1.0632 0.02562 0.01918 -0.0884 0.5475 0.0248
-15.500 -1.0496 0.02462 0.01812 -0.0877 0.5426 0.0251
-15.250 -1.0353 0.02374 0.01717 -0.0870 0.5379 0.0254
-14.750 -1.0039 0.02223 0.01554 -0.0851 0.5307 0.0260
-14.500 -0.9870 0.02158 0.01484 -0.0841 0.5283 0.0263
-14.250 -0.9694 0.02099 0.01420 -0.0830 0.5259 0.0266
-14.000 -0.9510 0.02046 0.01361 -0.0819 0.5233 0.0268
-13.750 -0.9339 0.01990 0.01299 -0.0806 0.5208 0.0271
-13.500 -0.9187 0.01938 0.01243 -0.0788 0.5184 0.0275
-13.250 -0.9021 0.01895 0.01196 -0.0771 0.5159 0.0278
-13.000 -0.8818 0.01852 0.01149 -0.0760 0.5133 0.0282
-12.500 -0.8383 0.01775 0.01065 -0.0740 0.5095 0.0290
-12.250 -0.8154 0.01739 0.01026 -0.0732 0.5084 0.0294
-12.000 -0.7919 0.01706 0.00990 -0.0724 0.5071 0.0299
-11.750 -0.7679 0.01674 0.00955 -0.0717 0.5058 0.0303
-11.500 -0.7441 0.01640 0.00918 -0.0709 0.5044 0.0307
-11.250 -0.7204 0.01604 0.00879 -0.0702 0.5029 0.0312
-11.000 -0.6960 0.01572 0.00845 -0.0695 0.5014 0.0317
-10.750 -0.6711 0.01542 0.00813 -0.0688 0.4999 0.0323
-10.500 -0.6458 0.01514 0.00783 -0.0683 0.4982 0.0329
-10.250 -0.6202 0.01490 0.00754 -0.0677 0.4964 0.0336
-10.000 -0.5942 0.01467 0.00728 -0.0672 0.4946 0.0341
-9.750 -0.5687 0.01439 0.00698 -0.0667 0.4929 0.0349
-9.500 -0.5428 0.01414 0.00672 -0.0662 0.4912 0.0357
-9.250 -0.5166 0.01392 0.00648 -0.0657 0.4895 0.0366
-9.000 -0.4899 0.01370 0.00625 -0.0654 0.4889 0.0377
-8.750 -0.4632 0.01347 0.00601 -0.0650 0.4882 0.0389
-8.500 -0.4364 0.01324 0.00579 -0.0646 0.4875 0.0404
-8.250 -0.4092 0.01304 0.00558 -0.0643 0.4868 0.0421
-8.000 -0.3821 0.01283 0.00538 -0.0640 0.4858 0.0441
-7.750 -0.3547 0.01264 0.00520 -0.0637 0.4846 0.0466
-7.500 -0.3272 0.01245 0.00503 -0.0634 0.4832 0.0497
-7.250 -0.2995 0.01229 0.00488 -0.0632 0.4815 0.0531
-7.000 -0.2714 0.01216 0.00475 -0.0631 0.4797 0.0567
-6.750 -0.2434 0.01203 0.00462 -0.0629 0.4776 0.0597
-6.500 -0.2151 0.01193 0.00450 -0.0628 0.4756 0.0622
-6.250 -0.1870 0.01182 0.00440 -0.0626 0.4739 0.0644
-6.000 -0.1586 0.01174 0.00430 -0.0625 0.4725 0.0666
-5.750 -0.1302 0.01168 0.00421 -0.0624 0.4707 0.0683
-5.500 -0.1018 0.01157 0.00411 -0.0623 0.4693 0.0702
-5.250 -0.0731 0.01146 0.00401 -0.0623 0.4682 0.0722
-5.000 -0.0442 0.01137 0.00392 -0.0623 0.4669 0.0739
-4.750 -0.0152 0.01129 0.00383 -0.0623 0.4656 0.0751
-4.500 0.0133 0.01117 0.00372 -0.0623 0.4640 0.0767
-4.250 0.0420 0.01108 0.00363 -0.0623 0.4622 0.0783
-4.000 0.0708 0.01100 0.00355 -0.0623 0.4603 0.0801
-3.750 0.0996 0.01094 0.00347 -0.0623 0.4584 0.0818
-3.500 0.1283 0.01087 0.00339 -0.0623 0.4565 0.0838
-3.250 0.1568 0.01079 0.00332 -0.0623 0.4544 0.0862
-3.000 0.1853 0.01074 0.00326 -0.0623 0.4523 0.0888
-2.750 0.2143 0.01069 0.00321 -0.0624 0.4510 0.0911
-2.500 0.2432 0.01060 0.00315 -0.0625 0.4498 0.0943
-2.250 0.2721 0.01052 0.00310 -0.0626 0.4484 0.0978
-2.000 0.3011 0.01045 0.00305 -0.0627 0.4467 0.1027
-1.750 0.3298 0.01037 0.00300 -0.0628 0.4447 0.1108
-1.500 0.3578 0.01023 0.00294 -0.0628 0.4425 0.1330
-1.250 0.3843 0.00994 0.00285 -0.0626 0.4401 0.1942
-1.000 0.4109 0.00970 0.00280 -0.0625 0.4374 0.2543
-0.750 0.4381 0.00954 0.00278 -0.0624 0.4345 0.3040
-0.500 0.4662 0.00938 0.00277 -0.0625 0.4322 0.3447
-0.250 0.4943 0.00926 0.00276 -0.0625 0.4289 0.3807
0.000 0.5222 0.00914 0.00275 -0.0626 0.4252 0.4195
0.250 0.5485 0.00892 0.00275 -0.0624 0.4210 0.4937
0.500 0.5760 0.00885 0.00280 -0.0624 0.4170 0.5441
0.750 0.6047 0.00885 0.00284 -0.0625 0.4121 0.5677
1.000 0.6328 0.00888 0.00290 -0.0626 0.4050 0.5896
1.250 0.6609 0.00894 0.00296 -0.0627 0.3977 0.6034
1.500 0.6886 0.00907 0.00304 -0.0627 0.3876 0.6126
1.750 0.7159 0.00919 0.00314 -0.0627 0.3772 0.6228
2.000 0.7427 0.00936 0.00327 -0.0626 0.3669 0.6352
2.500 0.7959 0.00969 0.00355 -0.0624 0.3494 0.6574
2.750 0.8222 0.00987 0.00372 -0.0623 0.3419 0.6676
3.000 0.8488 0.01002 0.00387 -0.0622 0.3363 0.6802
3.250 0.8753 0.01015 0.00402 -0.0621 0.3311 0.6938
3.500 0.9012 0.01032 0.00420 -0.0620 0.3261 0.7083
3.750 0.9273 0.01046 0.00436 -0.0619 0.3222 0.7225
4.000 0.9537 0.01055 0.00451 -0.0618 0.3197 0.7431
4.250 0.9794 0.01063 0.00468 -0.0615 0.3170 0.7700
4.500 1.0046 0.01074 0.00486 -0.0613 0.3143 0.7960
4.750 1.0294 0.01088 0.00506 -0.0609 0.3117 0.8203
5.000 1.0536 0.01103 0.00527 -0.0605 0.3090 0.8460
5.500 1.1019 0.01127 0.00567 -0.0595 0.3052 0.9004
5.750 1.1285 0.01140 0.00589 -0.0594 0.3038 0.9385
6.000 1.1655 0.01162 0.00614 -0.0617 0.3021 0.9705
6.250 1.1993 0.01185 0.00637 -0.0634 0.3003 0.9873
6.500 1.2314 0.01210 0.00661 -0.0648 0.2986 0.9961
6.750 1.2574 0.01235 0.00686 -0.0650 0.2969 1.0000
7.000 1.2722 0.01259 0.00710 -0.0629 0.2953 1.0000
7.250 1.2874 0.01287 0.00738 -0.0610 0.2936 1.0000
7.500 1.3037 0.01320 0.00771 -0.0594 0.2918 1.0000
7.750 1.3210 0.01355 0.00807 -0.0581 0.2901 1.0000
8.000 1.3416 0.01383 0.00837 -0.0574 0.2893 1.0000
8.250 1.3619 0.01414 0.00870 -0.0567 0.2884 1.0000
8.500 1.3818 0.01450 0.00908 -0.0560 0.2874 1.0000
8.750 1.4014 0.01489 0.00950 -0.0554 0.2864 1.0000
9.000 1.4205 0.01533 0.00997 -0.0548 0.2853 1.0000
9.250 1.4389 0.01584 0.01050 -0.0542 0.2839 1.0000
9.500 1.4565 0.01641 0.01110 -0.0535 0.2824 1.0000
9.750 1.4730 0.01709 0.01179 -0.0529 0.2806 1.0000
10.000 1.4884 0.01788 0.01260 -0.0523 0.2789 1.0000
10.250 1.5026 0.01880 0.01354 -0.0517 0.2772 1.0000
10.500 1.5158 0.01984 0.01461 -0.0511 0.2756 1.0000
10.750 1.5291 0.02092 0.01572 -0.0507 0.2743 1.0000
11.000 1.5462 0.02177 0.01662 -0.0506 0.2735 1.0000
11.250 1.5624 0.02270 0.01760 -0.0505 0.2724 1.0000
11.500 1.5770 0.02377 0.01871 -0.0503 0.2710 1.0000
11.750 1.5902 0.02497 0.01995 -0.0501 0.2694 1.0000
12.000 1.6017 0.02631 0.02133 -0.0498 0.2675 1.0000
12.250 1.6105 0.02789 0.02294 -0.0495 0.2653 1.0000
12.500 1.6155 0.02978 0.02487 -0.0490 0.2629 1.0000
12.750 1.6175 0.03195 0.02706 -0.0484 0.2605 1.0000
13.000 1.6233 0.03379 0.02894 -0.0480 0.2590 1.0000
13.250 1.6336 0.03522 0.03043 -0.0477 0.2580 1.0000
13.500 1.6414 0.03691 0.03218 -0.0475 0.2566 1.0000
13.750 1.6495 0.03857 0.03389 -0.0472 0.2549 1.0000
14.000 1.6544 0.04056 0.03593 -0.0469 0.2531 1.0000
14.250 1.6595 0.04251 0.03792 -0.0466 0.2511 1.0000
14.500 1.6601 0.04493 0.04038 -0.0463 0.2489 1.0000
14.750 1.6601 0.04739 0.04287 -0.0459 0.2465 1.0000
15.000 1.6628 0.04966 0.04518 -0.0457 0.2445 1.0000
15.250 1.6716 0.05131 0.04688 -0.0456 0.2425 1.0000
15.500 1.6756 0.05346 0.04908 -0.0455 0.2395 1.0000
15.750 1.6752 0.05605 0.05170 -0.0453 0.2356 1.0000
16.000 1.6714 0.05898 0.05464 -0.0450 0.2319 1.0000
16.250 1.6761 0.06110 0.05681 -0.0450 0.2296 1.0000
16.500 1.6818 0.06307 0.05883 -0.0450 0.2266 1.0000
16.750 1.6829 0.06555 0.06133 -0.0449 0.2222 1.0000
17.000 1.6754 0.06898 0.06478 -0.0448 0.2176 1.0000
17.250 1.6765 0.07149 0.06731 -0.0448 0.2117 1.0000
17.500 1.6652 0.07535 0.07118 -0.0447 0.2055 1.0000
17.750 1.6566 0.07894 0.07477 -0.0447 0.1969 1.0000
18.000 1.6404 0.08347 0.07929 -0.0447 0.1881 1.0000
18.250 1.6248 0.08791 0.08372 -0.0447 0.1795 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 777 AIRFOIL (goe777-il)