GOE 385 AIRFOIL (goe385-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 385 AIRFOIL (goe385-il) Reynolds number: 100,000 Max Cl/Cd: 56.17 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe385-il-100000-n5.txt Download as CSV file: xf-goe385-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 385 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3431 0.09655 0.09194 -0.0315 1.0000 0.0465
-8.000 -0.3472 0.09387 0.08936 -0.0350 1.0000 0.0469
-7.750 -0.3472 0.09067 0.08621 -0.0390 1.0000 0.0471
-7.500 -0.3473 0.08753 0.08310 -0.0414 1.0000 0.0473
-7.250 -0.3482 0.08448 0.08006 -0.0427 1.0000 0.0474
-7.000 -0.3502 0.08162 0.07719 -0.0430 1.0000 0.0474
-6.750 -0.3381 0.07556 0.07125 -0.0432 0.9953 0.0484
-6.500 -0.3200 0.07229 0.06803 -0.0424 0.9893 0.0511
-6.250 -0.2919 0.06790 0.06355 -0.0488 0.9803 0.0564
-5.750 -0.2297 0.05682 0.05202 -0.0644 0.9601 0.0632
-5.500 -0.2026 0.05305 0.04815 -0.0674 0.9512 0.0655
-5.250 -0.1705 0.04923 0.04383 -0.0728 0.9382 0.0767
-5.000 -0.1342 0.04270 0.03647 -0.0748 0.9264 0.0474
-4.750 -0.1097 0.03844 0.03210 -0.0763 0.9148 0.0462
-4.500 -0.0826 0.03518 0.02852 -0.0777 0.9032 0.0493
-4.250 -0.0517 0.03230 0.02504 -0.0785 0.8921 0.0485
-4.000 -0.0226 0.03014 0.02245 -0.0788 0.8796 0.0480
-3.750 0.0043 0.02791 0.02004 -0.0793 0.8676 0.0498
-3.500 0.0323 0.02644 0.01835 -0.0796 0.8557 0.0520
-3.250 0.0615 0.02478 0.01629 -0.0795 0.8443 0.0519
-3.000 0.0906 0.02337 0.01450 -0.0793 0.8334 0.0519
-2.750 0.1190 0.02221 0.01303 -0.0790 0.8218 0.0522
-2.500 0.1468 0.02131 0.01191 -0.0787 0.8097 0.0538
-2.250 0.1745 0.02058 0.01098 -0.0784 0.7980 0.0562
-2.000 0.2022 0.01981 0.01001 -0.0781 0.7869 0.0568
-1.750 0.2297 0.01910 0.00916 -0.0776 0.7762 0.0572
-1.500 0.2565 0.01850 0.00845 -0.0771 0.7630 0.0577
-1.250 0.2828 0.01795 0.00782 -0.0765 0.7490 0.0585
-1.000 0.3089 0.01748 0.00728 -0.0759 0.7350 0.0595
-0.750 0.3350 0.01710 0.00681 -0.0753 0.7215 0.0605
-0.500 0.3612 0.01668 0.00634 -0.0749 0.7095 0.0638
-0.250 0.3880 0.01644 0.00602 -0.0745 0.6986 0.0688
0.000 0.4153 0.01625 0.00570 -0.0742 0.6882 0.0725
0.250 0.4425 0.01611 0.00545 -0.0738 0.6770 0.0768
0.500 0.4697 0.01596 0.00524 -0.0735 0.6664 0.0873
0.750 0.5001 0.01350 0.00516 -0.0737 0.6568 1.0000
1.000 0.5269 0.01365 0.00507 -0.0733 0.6460 1.0000
1.250 0.5536 0.01382 0.00504 -0.0729 0.6352 1.0000
1.500 0.5802 0.01399 0.00504 -0.0726 0.6252 1.0000
1.750 0.6068 0.01417 0.00508 -0.0723 0.6145 1.0000
2.000 0.6334 0.01436 0.00517 -0.0720 0.6033 1.0000
2.250 0.6599 0.01456 0.00527 -0.0717 0.5923 1.0000
2.500 0.6863 0.01476 0.00537 -0.0714 0.5816 1.0000
2.750 0.7127 0.01495 0.00551 -0.0711 0.5697 1.0000
3.000 0.7389 0.01515 0.00569 -0.0709 0.5572 1.0000
3.250 0.7651 0.01535 0.00586 -0.0706 0.5445 1.0000
3.500 0.7911 0.01555 0.00603 -0.0702 0.5312 1.0000
3.750 0.8170 0.01576 0.00623 -0.0699 0.5176 1.0000
4.000 0.8428 0.01598 0.00643 -0.0696 0.5039 1.0000
4.250 0.8684 0.01621 0.00664 -0.0692 0.4896 1.0000
4.500 0.8938 0.01646 0.00686 -0.0688 0.4744 1.0000
4.750 0.9188 0.01673 0.00712 -0.0684 0.4587 1.0000
5.000 0.9437 0.01703 0.00739 -0.0679 0.4434 1.0000
5.250 0.9684 0.01737 0.00769 -0.0674 0.4291 1.0000
5.500 0.9929 0.01773 0.00806 -0.0670 0.4158 1.0000
5.750 1.0173 0.01813 0.00843 -0.0665 0.4033 1.0000
6.000 1.0414 0.01854 0.00884 -0.0660 0.3914 1.0000
6.250 1.0656 0.01897 0.00933 -0.0656 0.3801 1.0000
6.500 1.0897 0.01942 0.00982 -0.0651 0.3708 1.0000
6.750 1.1136 0.01990 0.01033 -0.0646 0.3622 1.0000
7.000 1.1373 0.02037 0.01089 -0.0641 0.3522 1.0000
7.250 1.1603 0.02088 0.01146 -0.0635 0.3422 1.0000
7.500 1.1830 0.02139 0.01203 -0.0629 0.3324 1.0000
7.750 1.2054 0.02190 0.01267 -0.0622 0.3218 1.0000
8.000 1.2271 0.02244 0.01330 -0.0615 0.3110 1.0000
8.250 1.2473 0.02298 0.01395 -0.0605 0.2971 1.0000
8.500 1.2662 0.02353 0.01459 -0.0595 0.2810 1.0000
8.750 1.2844 0.02412 0.01527 -0.0583 0.2643 1.0000
9.000 1.3010 0.02477 0.01599 -0.0570 0.2452 1.0000
9.250 1.3169 0.02549 0.01678 -0.0556 0.2269 1.0000
9.500 1.3324 0.02626 0.01769 -0.0542 0.2042 1.0000
9.750 1.3446 0.02724 0.01867 -0.0524 0.1750 1.0000
10.000 1.3456 0.02894 0.02006 -0.0496 0.1338 1.0000
10.250 1.3430 0.03084 0.02179 -0.0463 0.1077 1.0000
10.500 1.3367 0.03324 0.02397 -0.0432 0.0652 1.0000
10.750 1.3294 0.03589 0.02650 -0.0406 0.0503 1.0000
11.000 1.3253 0.03847 0.02917 -0.0387 0.0406 1.0000
11.250 1.3213 0.04123 0.03204 -0.0372 0.0343 1.0000
11.500 1.3176 0.04414 0.03509 -0.0363 0.0304 1.0000
11.750 1.3114 0.04749 0.03853 -0.0357 0.0280 1.0000
12.000 1.3060 0.05095 0.04216 -0.0355 0.0263 1.0000
12.250 1.2992 0.05476 0.04617 -0.0356 0.0249 1.0000
12.500 1.2908 0.05896 0.05052 -0.0362 0.0239 1.0000
12.750 1.2805 0.06356 0.05526 -0.0370 0.0231 1.0000
13.000 1.2685 0.06853 0.06038 -0.0381 0.0225 1.0000
13.250 1.2554 0.07383 0.06583 -0.0394 0.0221 1.0000
13.500 1.2438 0.07906 0.07121 -0.0408 0.0217 1.0000
13.750 1.2331 0.08434 0.07666 -0.0424 0.0215 1.0000
14.000 1.2231 0.08963 0.08211 -0.0440 0.0212 1.0000
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Polar data table (+)
Polar graphs
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