GOE 777 AIRFOIL (goe777-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 777 AIRFOIL (goe777-il) Reynolds number: 200,000 Max Cl/Cd: 57.68 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe777-il-200000-n5.txt Download as CSV file: xf-goe777-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.7041 0.07478 0.06921 -0.0736 0.7513 0.0381
-16.250 -0.7177 0.06940 0.06363 -0.0771 0.7337 0.0384
-16.000 -0.7279 0.06467 0.05872 -0.0801 0.7181 0.0386
-15.750 -0.7366 0.06034 0.05420 -0.0828 0.7044 0.0388
-15.500 -0.7434 0.05643 0.05011 -0.0851 0.6912 0.0391
-15.250 -0.7485 0.05290 0.04640 -0.0870 0.6795 0.0394
-15.000 -0.7522 0.04967 0.04298 -0.0885 0.6680 0.0398
-14.750 -0.7543 0.04675 0.03986 -0.0897 0.6580 0.0402
-14.500 -0.7548 0.04410 0.03701 -0.0905 0.6481 0.0406
-14.250 -0.7540 0.04169 0.03438 -0.0910 0.6396 0.0412
-14.000 -0.7519 0.03944 0.03191 -0.0912 0.6314 0.0418
-13.750 -0.7478 0.03748 0.02971 -0.0910 0.6238 0.0424
-13.500 -0.7378 0.03622 0.02838 -0.0906 0.6170 0.0428
-13.250 -0.7273 0.03502 0.02712 -0.0901 0.6102 0.0434
-13.000 -0.7164 0.03389 0.02588 -0.0894 0.6041 0.0440
-12.500 -0.6927 0.03169 0.02340 -0.0875 0.5942 0.0454
-12.250 -0.6795 0.03060 0.02216 -0.0864 0.5899 0.0462
-12.000 -0.6658 0.02967 0.02109 -0.0852 0.5858 0.0470
-11.750 -0.6523 0.02907 0.02044 -0.0836 0.5822 0.0477
-11.500 -0.6374 0.02852 0.01981 -0.0821 0.5789 0.0485
-11.250 -0.6200 0.02791 0.01909 -0.0809 0.5759 0.0495
-11.000 -0.6014 0.02721 0.01829 -0.0799 0.5731 0.0507
-10.750 -0.5820 0.02651 0.01749 -0.0789 0.5703 0.0518
-10.500 -0.5619 0.02602 0.01698 -0.0780 0.5675 0.0527
-10.250 -0.5410 0.02554 0.01645 -0.0771 0.5648 0.0539
-10.000 -0.5195 0.02504 0.01585 -0.0762 0.5623 0.0554
-9.750 -0.4977 0.02453 0.01522 -0.0754 0.5600 0.0571
-9.500 -0.4753 0.02418 0.01484 -0.0747 0.5577 0.0584
-9.250 -0.4525 0.02382 0.01438 -0.0739 0.5554 0.0603
-9.000 -0.4291 0.02337 0.01381 -0.0732 0.5533 0.0624
-8.750 -0.4057 0.02301 0.01346 -0.0726 0.5511 0.0640
-8.500 -0.3817 0.02267 0.01308 -0.0720 0.5491 0.0662
-8.250 -0.3572 0.02231 0.01264 -0.0714 0.5471 0.0688
-8.000 -0.3330 0.02201 0.01234 -0.0708 0.5452 0.0709
-7.750 -0.3082 0.02172 0.01198 -0.0703 0.5434 0.0738
-7.500 -0.2835 0.02139 0.01161 -0.0698 0.5416 0.0762
-7.250 -0.2587 0.02110 0.01130 -0.0693 0.5399 0.0787
-7.000 -0.2333 0.02086 0.01098 -0.0688 0.5382 0.0817
-6.750 -0.2086 0.02055 0.01066 -0.0683 0.5366 0.0843
-6.500 -0.1834 0.02032 0.01038 -0.0678 0.5349 0.0872
-6.250 -0.1575 0.02015 0.01011 -0.0674 0.5331 0.0902
-6.000 -0.1328 0.01986 0.00984 -0.0669 0.5314 0.0929
-5.750 -0.1073 0.01963 0.00963 -0.0665 0.5300 0.0959
-5.500 -0.0813 0.01945 0.00942 -0.0661 0.5285 0.0992
-5.250 -0.0565 0.01917 0.00920 -0.0656 0.5267 0.1026
-5.000 -0.0308 0.01897 0.00901 -0.0652 0.5243 0.1067
-4.750 -0.0052 0.01876 0.00879 -0.0648 0.5215 0.1109
-4.500 0.0202 0.01852 0.00856 -0.0643 0.5188 0.1155
-4.250 0.0464 0.01835 0.00833 -0.0639 0.5160 0.1201
-4.000 0.0721 0.01814 0.00811 -0.0635 0.5136 0.1253
-3.750 0.0985 0.01802 0.00794 -0.0632 0.5111 0.1323
-3.500 0.1239 0.01781 0.00779 -0.0628 0.5085 0.1433
-3.250 0.1487 0.01752 0.00766 -0.0623 0.5060 0.1658
-3.000 0.1722 0.01711 0.00756 -0.0618 0.5038 0.2267
-2.750 0.1962 0.01679 0.00750 -0.0612 0.5017 0.2935
-2.500 0.2212 0.01657 0.00745 -0.0608 0.4994 0.3415
-2.250 0.2465 0.01638 0.00739 -0.0603 0.4971 0.3831
-2.000 0.2717 0.01618 0.00734 -0.0598 0.4948 0.4265
-1.750 0.2954 0.01595 0.00738 -0.0590 0.4927 0.4950
-1.500 0.3207 0.01590 0.00747 -0.0583 0.4907 0.5618
-1.250 0.3472 0.01595 0.00757 -0.0579 0.4887 0.5978
-1.000 0.3733 0.01598 0.00770 -0.0575 0.4864 0.6228
-0.750 0.3997 0.01602 0.00780 -0.0572 0.4838 0.6435
-0.500 0.4264 0.01607 0.00787 -0.0569 0.4810 0.6626
-0.250 0.4530 0.01608 0.00793 -0.0565 0.4782 0.6799
0.000 0.4800 0.01608 0.00794 -0.0562 0.4754 0.6963
0.250 0.5072 0.01608 0.00793 -0.0560 0.4729 0.7126
0.500 0.5346 0.01610 0.00792 -0.0557 0.4705 0.7289
0.750 0.5603 0.01615 0.00806 -0.0553 0.4676 0.7459
1.000 0.5857 0.01621 0.00822 -0.0548 0.4642 0.7632
1.500 0.6375 0.01628 0.00840 -0.0539 0.4577 0.7993
1.750 0.6641 0.01629 0.00843 -0.0536 0.4548 0.8181
2.000 0.6914 0.01630 0.00842 -0.0533 0.4521 0.8381
2.250 0.7173 0.01642 0.00865 -0.0529 0.4482 0.8625
2.500 0.7454 0.01653 0.00884 -0.0530 0.4437 0.8875
2.750 0.7777 0.01661 0.00894 -0.0539 0.4394 0.9083
3.000 0.8132 0.01668 0.00894 -0.0555 0.4356 0.9243
3.250 0.8486 0.01687 0.00918 -0.0574 0.4303 0.9403
3.500 0.8842 0.01705 0.00936 -0.0593 0.4247 0.9562
3.750 0.9202 0.01717 0.00942 -0.0612 0.4201 0.9715
4.000 0.9562 0.01738 0.00963 -0.0633 0.4147 0.9851
4.250 0.9932 0.01760 0.00984 -0.0657 0.4086 0.9959
4.500 1.0181 0.01775 0.00991 -0.0657 0.4038 1.0000
4.750 1.0324 0.01796 0.01011 -0.0636 0.3987 1.0000
5.000 1.0467 0.01818 0.01030 -0.0616 0.3935 1.0000
5.250 1.0614 0.01840 0.01044 -0.0596 0.3889 1.0000
5.500 1.0763 0.01868 0.01070 -0.0577 0.3843 1.0000
5.750 1.0907 0.01901 0.01101 -0.0558 0.3794 1.0000
6.000 1.1032 0.01935 0.01129 -0.0536 0.3749 1.0000
6.250 1.1149 0.01973 0.01160 -0.0513 0.3710 1.0000
6.500 1.1275 0.02021 0.01210 -0.0494 0.3668 1.0000
6.750 1.1406 0.02074 0.01261 -0.0477 0.3628 1.0000
7.000 1.1543 0.02130 0.01313 -0.0462 0.3594 1.0000
7.250 1.1688 0.02189 0.01367 -0.0450 0.3564 1.0000
7.500 1.1832 0.02257 0.01436 -0.0438 0.3535 1.0000
7.750 1.1969 0.02332 0.01515 -0.0428 0.3506 1.0000
8.000 1.2107 0.02412 0.01595 -0.0418 0.3477 1.0000
8.250 1.2247 0.02493 0.01677 -0.0410 0.3451 1.0000
8.500 1.2397 0.02573 0.01754 -0.0402 0.3427 1.0000
8.750 1.2565 0.02644 0.01821 -0.0397 0.3406 1.0000
9.000 1.2714 0.02731 0.01909 -0.0391 0.3385 1.0000
9.250 1.2827 0.02845 0.02031 -0.0384 0.3362 1.0000
9.500 1.2938 0.02964 0.02155 -0.0378 0.3338 1.0000
9.750 1.3046 0.03087 0.02283 -0.0372 0.3313 1.0000
10.000 1.3170 0.03200 0.02398 -0.0367 0.3291 1.0000
10.250 1.3318 0.03297 0.02495 -0.0363 0.3273 1.0000
10.500 1.3489 0.03376 0.02573 -0.0360 0.3256 1.0000
10.750 1.3687 0.03437 0.02631 -0.0358 0.3240 1.0000
11.000 1.3826 0.03544 0.02742 -0.0354 0.3224 1.0000
11.250 1.3867 0.03732 0.02941 -0.0349 0.3206 1.0000
11.500 1.3907 0.03924 0.03144 -0.0344 0.3186 1.0000
11.750 1.3942 0.04122 0.03352 -0.0339 0.3164 1.0000
12.000 1.3994 0.04308 0.03545 -0.0335 0.3142 1.0000
12.250 1.4079 0.04467 0.03709 -0.0332 0.3124 1.0000
12.500 1.4189 0.04604 0.03851 -0.0330 0.3108 1.0000
12.750 1.4349 0.04696 0.03944 -0.0328 0.3093 1.0000
13.000 1.4565 0.04736 0.03982 -0.0328 0.3078 1.0000
13.250 1.4745 0.04812 0.04059 -0.0326 0.3062 1.0000
13.500 1.4413 0.05379 0.04652 -0.0320 0.3032 1.0000
13.750 1.4131 0.05930 0.05222 -0.0318 0.2994 1.0000
14.000 1.4079 0.06251 0.05552 -0.0317 0.2965 1.0000
14.250 1.4165 0.06424 0.05730 -0.0317 0.2943 1.0000
14.500 1.4337 0.06501 0.05806 -0.0317 0.2926 1.0000
14.750 1.4607 0.06468 0.05772 -0.0318 0.2912 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 777 AIRFOIL (goe777-il)