GOE 777 AIRFOIL (goe777-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 777 AIRFOIL (goe777-il) Reynolds number: 100,000 Max Cl/Cd: 32.05 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe777-il-100000-n5.txt Download as CSV file: xf-goe777-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.2807 0.10631 0.09977 -0.0557 0.6488 0.0573
-13.000 -0.5134 0.06105 0.05388 -0.0886 0.6661 0.0573
-12.750 -0.5286 0.05701 0.04964 -0.0905 0.6614 0.0577
-12.500 -0.5385 0.05381 0.04626 -0.0915 0.6559 0.0582
-12.250 -0.5465 0.05103 0.04328 -0.0915 0.6507 0.0588
-12.000 -0.5538 0.04848 0.04047 -0.0907 0.6460 0.0595
-11.750 -0.5618 0.04628 0.03797 -0.0887 0.6420 0.0602
-11.500 -0.5660 0.04402 0.03540 -0.0868 0.6376 0.0611
-11.250 -0.5680 0.04167 0.03263 -0.0849 0.6332 0.0624
-11.000 -0.5502 0.04086 0.03180 -0.0841 0.6286 0.0634
-10.750 -0.5348 0.03988 0.03069 -0.0831 0.6248 0.0646
-10.500 -0.5210 0.03863 0.02921 -0.0819 0.6215 0.0662
-10.250 -0.5084 0.03708 0.02727 -0.0805 0.6185 0.0680
-10.000 -0.4890 0.03603 0.02614 -0.0798 0.6149 0.0693
-9.750 -0.4682 0.03522 0.02530 -0.0792 0.6115 0.0708
-9.500 -0.4485 0.03430 0.02421 -0.0784 0.6083 0.0730
-9.250 -0.4290 0.03326 0.02289 -0.0774 0.6054 0.0755
-9.000 -0.4059 0.03259 0.02221 -0.0769 0.6026 0.0773
-8.750 -0.3834 0.03184 0.02133 -0.0763 0.6000 0.0797
-8.500 -0.3613 0.03104 0.02024 -0.0755 0.5974 0.0827
-8.250 -0.3372 0.03041 0.01972 -0.0752 0.5943 0.0850
-8.000 -0.3136 0.02982 0.01908 -0.0747 0.5914 0.0881
-7.750 -0.2898 0.02920 0.01834 -0.0741 0.5888 0.0914
-7.500 -0.2656 0.02866 0.01785 -0.0737 0.5864 0.0944
-7.250 -0.2414 0.02819 0.01727 -0.0732 0.5841 0.0983
-7.000 -0.2172 0.02767 0.01674 -0.0727 0.5819 0.1017
-6.750 -0.1930 0.02725 0.01630 -0.0721 0.5799 0.1057
-6.500 -0.1683 0.02687 0.01580 -0.0716 0.5779 0.1101
-6.250 -0.1447 0.02647 0.01544 -0.0710 0.5758 0.1143
-6.000 -0.1210 0.02620 0.01517 -0.0704 0.5732 0.1193
-5.750 -0.0981 0.02587 0.01492 -0.0698 0.5708 0.1239
-5.500 -0.0747 0.02563 0.01470 -0.0692 0.5685 0.1293
-5.250 -0.0516 0.02537 0.01447 -0.0685 0.5663 0.1346
-5.000 -0.0284 0.02512 0.01424 -0.0678 0.5639 0.1407
-4.750 -0.0048 0.02488 0.01399 -0.0671 0.5615 0.1473
-4.500 0.0187 0.02461 0.01374 -0.0664 0.5592 0.1558
-4.250 0.0425 0.02433 0.01349 -0.0657 0.5571 0.1673
-4.000 0.0664 0.02403 0.01324 -0.0650 0.5549 0.1870
-3.750 0.0865 0.02372 0.01323 -0.0640 0.5512 0.2274
-3.500 0.1060 0.02340 0.01325 -0.0629 0.5467 0.2923
-3.250 0.1276 0.02312 0.01317 -0.0618 0.5425 0.3509
-3.000 0.1502 0.02283 0.01306 -0.0609 0.5390 0.4039
-2.500 0.1978 0.02251 0.01311 -0.0588 0.5338 0.5223
-2.250 0.2223 0.02263 0.01326 -0.0580 0.5313 0.5698
-2.000 0.2428 0.02289 0.01368 -0.0567 0.5276 0.6089
-1.750 0.2644 0.02311 0.01400 -0.0555 0.5239 0.6426
-1.500 0.2876 0.02328 0.01423 -0.0544 0.5205 0.6706
-1.250 0.3121 0.02339 0.01435 -0.0535 0.5175 0.6955
-1.000 0.3379 0.02346 0.01440 -0.0527 0.5148 0.7194
-0.750 0.3650 0.02350 0.01439 -0.0521 0.5124 0.7430
-0.500 0.3922 0.02360 0.01444 -0.0514 0.5099 0.7656
-0.250 0.4099 0.02405 0.01506 -0.0499 0.5052 0.7857
0.000 0.4313 0.02434 0.01540 -0.0488 0.5009 0.8047
0.250 0.4566 0.02450 0.01556 -0.0482 0.4972 0.8213
0.500 0.4846 0.02456 0.01557 -0.0480 0.4942 0.8366
0.750 0.5146 0.02457 0.01548 -0.0481 0.4916 0.8529
1.000 0.5473 0.02457 0.01537 -0.0487 0.4894 0.8702
1.250 0.5648 0.02531 0.01631 -0.0476 0.4834 0.8916
1.500 0.5960 0.02567 0.01670 -0.0485 0.4786 0.9129
1.750 0.6357 0.02579 0.01675 -0.0507 0.4748 0.9308
2.000 0.6802 0.02574 0.01657 -0.0538 0.4718 0.9441
2.250 0.7181 0.02595 0.01672 -0.0561 0.4680 0.9571
2.500 0.7468 0.02672 0.01759 -0.0578 0.4615 0.9733
2.750 0.7856 0.02693 0.01775 -0.0606 0.4573 0.9859
3.000 0.8293 0.02689 0.01761 -0.0640 0.4541 0.9965
3.250 0.8574 0.02675 0.01732 -0.0643 0.4517 1.0000
3.500 0.8355 0.02795 0.01867 -0.0576 0.4448 1.0000
3.750 0.8410 0.02836 0.01905 -0.0546 0.4404 1.0000
4.000 0.8597 0.02838 0.01898 -0.0532 0.4373 1.0000
4.250 0.8861 0.02821 0.01868 -0.0529 0.4349 1.0000
4.500 0.8530 0.03021 0.02084 -0.0454 0.4268 1.0000
4.750 0.8607 0.03076 0.02135 -0.0430 0.4226 1.0000
5.000 0.8855 0.03072 0.02121 -0.0426 0.4200 1.0000
5.250 0.8424 0.03440 0.02504 -0.0369 0.4111 1.0000
5.500 0.8495 0.03567 0.02629 -0.0358 0.4067 1.0000
5.750 0.8763 0.03559 0.02612 -0.0356 0.4046 1.0000
6.000 0.9077 0.03520 0.02565 -0.0357 0.4030 1.0000
6.250 0.8409 0.04303 0.03366 -0.0327 0.3901 1.0000
6.500 0.8700 0.04267 0.03323 -0.0326 0.3887 1.0000
6.750 0.9019 0.04207 0.03256 -0.0325 0.3876 1.0000
7.250 0.8288 0.05497 0.04562 -0.0307 0.3686 1.0000
7.500 0.8781 0.05225 0.04281 -0.0306 0.3705 1.0000
8.500 0.8931 0.06206 0.05266 -0.0295 0.3558 1.0000
11.500 0.5470 0.12356 0.11559 -0.0174 0.2801 1.0000
11.750 0.5593 0.12460 0.11664 -0.0174 0.2779 1.0000
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