GOE 285 AIRFOIL (goe285-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 285 AIRFOIL (goe285-il) Reynolds number: 100,000 Max Cl/Cd: 50.14 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe285-il-100000-n5.txt Download as CSV file: xf-goe285-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 285 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3673 0.09097 0.08563 -0.0365 1.0000 0.0540
-8.500 -0.3727 0.08738 0.08211 -0.0375 1.0000 0.0537
-8.000 -0.4308 0.07490 0.06982 -0.0437 1.0000 0.0507
-7.750 -0.4379 0.07171 0.06665 -0.0433 1.0000 0.0505
-7.500 -0.4458 0.06856 0.06352 -0.0425 1.0000 0.0502
-7.250 -0.4544 0.06523 0.06017 -0.0416 1.0000 0.0499
-7.000 -0.4383 0.05871 0.05344 -0.0476 0.9935 0.0495
-6.750 -0.4187 0.05147 0.04585 -0.0537 0.9851 0.0492
-6.500 -0.3995 0.04427 0.03812 -0.0583 0.9763 0.0492
-6.250 -0.3787 0.03745 0.03046 -0.0616 0.9682 0.0504
-6.000 -0.3511 0.03394 0.02646 -0.0636 0.9614 0.0511
-5.750 -0.3220 0.03183 0.02408 -0.0649 0.9543 0.0517
-5.500 -0.2901 0.02984 0.02178 -0.0665 0.9478 0.0524
-5.250 -0.2582 0.02805 0.01970 -0.0679 0.9413 0.0533
-5.000 -0.2257 0.02639 0.01775 -0.0692 0.9339 0.0544
-4.750 -0.1912 0.02486 0.01589 -0.0706 0.9269 0.0562
-4.500 -0.1582 0.02358 0.01436 -0.0715 0.9171 0.0585
-4.250 -0.1251 0.02277 0.01350 -0.0725 0.9064 0.0604
-4.000 -0.0891 0.02174 0.01233 -0.0738 0.8975 0.0628
-3.750 -0.0592 0.02082 0.01124 -0.0739 0.8856 0.0654
-3.500 -0.0273 0.02005 0.01045 -0.0745 0.8765 0.0683
-3.250 0.0036 0.01945 0.00980 -0.0748 0.8663 0.0732
-3.000 0.0329 0.01887 0.00922 -0.0749 0.8555 0.0797
-2.750 0.0645 0.01827 0.00856 -0.0753 0.8463 0.0890
-2.500 0.0918 0.01786 0.00816 -0.0749 0.8338 0.0990
-2.250 0.1205 0.01752 0.00783 -0.0749 0.8226 0.1107
-2.000 0.1500 0.01723 0.00752 -0.0749 0.8119 0.1237
-1.750 0.1769 0.01706 0.00736 -0.0745 0.7987 0.1409
-1.500 0.2043 0.01683 0.00713 -0.0742 0.7861 0.1589
-1.250 0.2315 0.01650 0.00682 -0.0737 0.7729 0.1734
-1.000 0.2584 0.01618 0.00650 -0.0732 0.7585 0.1903
-0.750 0.2847 0.01588 0.00624 -0.0725 0.7421 0.2144
-0.500 0.3106 0.01549 0.00601 -0.0719 0.7240 0.2646
-0.250 0.3331 0.01459 0.00587 -0.0708 0.7047 0.4827
0.000 0.3852 0.01351 0.00589 -0.0738 0.6830 0.9562
0.250 0.4320 0.01356 0.00568 -0.0774 0.6641 1.0000
0.500 0.4563 0.01366 0.00559 -0.0765 0.6481 1.0000
0.750 0.4806 0.01378 0.00553 -0.0755 0.6322 1.0000
1.000 0.5048 0.01393 0.00550 -0.0746 0.6164 1.0000
1.250 0.5290 0.01408 0.00550 -0.0737 0.6008 1.0000
1.500 0.5531 0.01425 0.00552 -0.0728 0.5850 1.0000
1.750 0.5772 0.01443 0.00557 -0.0719 0.5688 1.0000
2.000 0.6012 0.01462 0.00563 -0.0710 0.5522 1.0000
2.250 0.6251 0.01481 0.00571 -0.0701 0.5351 1.0000
2.500 0.6489 0.01502 0.00581 -0.0692 0.5179 1.0000
2.750 0.6726 0.01525 0.00591 -0.0682 0.5009 1.0000
3.000 0.6963 0.01550 0.00604 -0.0673 0.4846 1.0000
3.250 0.7199 0.01577 0.00618 -0.0664 0.4692 1.0000
3.500 0.7436 0.01607 0.00636 -0.0656 0.4547 1.0000
3.750 0.7673 0.01638 0.00659 -0.0647 0.4410 1.0000
4.000 0.7912 0.01670 0.00683 -0.0639 0.4285 1.0000
4.250 0.8149 0.01706 0.00709 -0.0632 0.4170 1.0000
4.500 0.8386 0.01741 0.00740 -0.0624 0.4056 1.0000
4.750 0.8626 0.01777 0.00773 -0.0617 0.3950 1.0000
5.000 0.8862 0.01818 0.00805 -0.0609 0.3858 1.0000
5.250 0.9103 0.01854 0.00845 -0.0603 0.3759 1.0000
5.500 0.9340 0.01896 0.00879 -0.0595 0.3683 1.0000
5.750 0.9581 0.01935 0.00923 -0.0589 0.3600 1.0000
6.000 0.9819 0.01977 0.00963 -0.0583 0.3532 1.0000
6.250 1.0060 0.02020 0.01009 -0.0576 0.3463 1.0000
6.500 1.0297 0.02063 0.01054 -0.0570 0.3397 1.0000
6.750 1.0534 0.02108 0.01098 -0.0564 0.3341 1.0000
7.000 1.0767 0.02152 0.01151 -0.0557 0.3271 1.0000
7.250 1.0993 0.02194 0.01191 -0.0549 0.3204 1.0000
7.500 1.1213 0.02237 0.01243 -0.0540 0.3124 1.0000
7.750 1.1428 0.02279 0.01286 -0.0530 0.3049 1.0000
8.000 1.1640 0.02324 0.01339 -0.0521 0.2972 1.0000
8.250 1.1846 0.02369 0.01387 -0.0510 0.2897 1.0000
8.500 1.2052 0.02417 0.01444 -0.0500 0.2826 1.0000
8.750 1.2252 0.02466 0.01501 -0.0489 0.2756 1.0000
9.000 1.2445 0.02518 0.01558 -0.0477 0.2686 1.0000
9.250 1.2624 0.02569 0.01620 -0.0464 0.2602 1.0000
9.500 1.2796 0.02625 0.01684 -0.0449 0.2522 1.0000
9.750 1.2955 0.02682 0.01751 -0.0433 0.2435 1.0000
10.000 1.3106 0.02744 0.01823 -0.0417 0.2346 1.0000
10.250 1.3227 0.02811 0.01896 -0.0396 0.2247 1.0000
10.500 1.3336 0.02878 0.01980 -0.0374 0.2132 1.0000
10.750 1.3432 0.02955 0.02071 -0.0351 0.2014 1.0000
11.000 1.3520 0.03043 0.02173 -0.0329 0.1850 1.0000
11.250 1.3580 0.03153 0.02288 -0.0306 0.1527 1.0000
11.500 1.3500 0.03359 0.02464 -0.0276 0.1257 1.0000
11.750 1.3428 0.03605 0.02700 -0.0252 0.1107 1.0000
12.000 1.3364 0.03871 0.02967 -0.0233 0.0999 1.0000
12.250 1.3287 0.04169 0.03270 -0.0219 0.0912 1.0000
12.500 1.3235 0.04466 0.03578 -0.0210 0.0832 1.0000
12.750 1.3150 0.04815 0.03936 -0.0204 0.0777 1.0000
13.000 1.3067 0.05185 0.04319 -0.0203 0.0729 1.0000
13.250 1.2946 0.05622 0.04766 -0.0207 0.0699 1.0000
13.500 1.2843 0.06060 0.05218 -0.0214 0.0671 1.0000
13.750 1.2723 0.06537 0.05709 -0.0224 0.0649 1.0000
14.000 1.2589 0.07053 0.06237 -0.0237 0.0632 1.0000
14.250 1.2446 0.07601 0.06795 -0.0252 0.0618 1.0000
14.500 1.2310 0.08150 0.07351 -0.0269 0.0607 1.0000
14.750 1.2227 0.08622 0.07837 -0.0282 0.0593 1.0000
15.000 1.2158 0.09076 0.08302 -0.0294 0.0578 1.0000
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Polar data table (+)
Polar graphs
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