GOE 286 AIRFOIL (goe286-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 286 AIRFOIL (goe286-il) Reynolds number: 200,000 Max Cl/Cd: 72.25 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe286-il-200000.txt Download as CSV file: xf-goe286-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 286 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3699 0.08853 0.08522 -0.0210 1.0000 0.0478
-7.500 -0.3661 0.08414 0.08083 -0.0366 1.0000 0.0492
-7.250 -0.3627 0.07894 0.07566 -0.0382 1.0000 0.0497
-7.000 -0.3571 0.07613 0.07291 -0.0342 1.0000 0.0504
-6.750 -0.3516 0.07378 0.07060 -0.0322 1.0000 0.0513
-6.500 -0.3480 0.07141 0.06826 -0.0315 1.0000 0.0525
-6.250 -0.3460 0.06900 0.06587 -0.0311 1.0000 0.0538
-6.000 -0.3449 0.06652 0.06340 -0.0311 1.0000 0.0556
-5.500 -0.2964 0.05660 0.05320 -0.0439 0.9941 0.0619
-5.250 -0.2604 0.05327 0.04984 -0.0481 0.9878 0.0649
-5.000 -0.2046 0.04724 0.04317 -0.0597 0.9815 0.0733
-4.750 -0.1720 0.04348 0.03951 -0.0629 0.9754 0.0752
-4.500 -0.1318 0.04063 0.03659 -0.0672 0.9712 0.0799
-4.250 -0.0921 0.03683 0.03236 -0.0718 0.9618 0.0888
-4.000 -0.0597 0.03442 0.02995 -0.0738 0.9526 0.0922
-3.750 -0.0241 0.03209 0.02712 -0.0760 0.9413 0.1031
-3.500 -0.0002 0.02985 0.02493 -0.0758 0.9254 0.1061
-3.250 0.0262 0.02863 0.02331 -0.0752 0.9065 0.1184
-3.000 0.0475 0.02654 0.02128 -0.0742 0.8869 0.1225
-2.750 0.0710 0.02519 0.01968 -0.0732 0.8675 0.1361
-2.500 0.1088 0.02004 0.01328 -0.0711 0.8512 0.0702
-2.250 0.1344 0.01817 0.01109 -0.0700 0.8303 0.0663
-2.000 0.1611 0.01677 0.00927 -0.0688 0.8105 0.0635
-1.750 0.1875 0.01600 0.00828 -0.0679 0.7915 0.0641
-1.500 0.2144 0.01537 0.00750 -0.0673 0.7724 0.0655
-1.250 0.2417 0.01467 0.00666 -0.0667 0.7531 0.0656
-1.000 0.2689 0.01409 0.00596 -0.0661 0.7341 0.0662
-0.750 0.2959 0.01361 0.00538 -0.0656 0.7152 0.0676
-0.500 0.3228 0.01323 0.00489 -0.0650 0.6959 0.0696
-0.250 0.3498 0.01297 0.00450 -0.0645 0.6758 0.0721
0.000 0.3765 0.01264 0.00412 -0.0641 0.6566 0.0786
0.250 0.4037 0.01250 0.00386 -0.0637 0.6385 0.0890
0.500 0.4288 0.01126 0.00367 -0.0636 0.6221 0.4220
0.750 0.4598 0.00998 0.00355 -0.0634 0.6048 1.0000
1.000 0.4870 0.01016 0.00353 -0.0631 0.5880 1.0000
1.250 0.5144 0.01030 0.00353 -0.0628 0.5704 1.0000
1.500 0.5417 0.01044 0.00354 -0.0626 0.5519 1.0000
1.750 0.5691 0.01057 0.00355 -0.0624 0.5328 1.0000
2.000 0.5963 0.01072 0.00356 -0.0622 0.5137 1.0000
2.250 0.6233 0.01090 0.00360 -0.0620 0.4958 1.0000
2.500 0.6504 0.01110 0.00366 -0.0618 0.4791 1.0000
2.750 0.6774 0.01133 0.00376 -0.0616 0.4640 1.0000
3.000 0.7042 0.01158 0.00389 -0.0614 0.4493 1.0000
3.250 0.7310 0.01184 0.00404 -0.0612 0.4357 1.0000
3.500 0.7578 0.01210 0.00420 -0.0610 0.4223 1.0000
3.750 0.7844 0.01236 0.00438 -0.0609 0.4091 1.0000
4.000 0.8111 0.01262 0.00458 -0.0607 0.3967 1.0000
4.250 0.8376 0.01290 0.00479 -0.0605 0.3868 1.0000
4.500 0.8646 0.01312 0.00502 -0.0604 0.3779 1.0000
4.750 0.8912 0.01340 0.00526 -0.0602 0.3703 1.0000
5.000 0.9181 0.01362 0.00551 -0.0601 0.3619 1.0000
5.250 0.9446 0.01388 0.00576 -0.0599 0.3536 1.0000
5.500 0.9711 0.01412 0.00603 -0.0597 0.3455 1.0000
5.750 0.9975 0.01437 0.00630 -0.0595 0.3375 1.0000
6.000 1.0237 0.01463 0.00657 -0.0593 0.3291 1.0000
6.250 1.0499 0.01487 0.00686 -0.0591 0.3196 1.0000
6.500 1.0755 0.01515 0.00716 -0.0589 0.3099 1.0000
6.750 1.1014 0.01540 0.00747 -0.0586 0.2995 1.0000
7.000 1.1270 0.01567 0.00779 -0.0584 0.2886 1.0000
7.250 1.1522 0.01596 0.00814 -0.0580 0.2756 1.0000
7.500 1.1770 0.01629 0.00850 -0.0577 0.2616 1.0000
7.750 1.2014 0.01666 0.00889 -0.0573 0.2452 1.0000
8.000 1.2246 0.01713 0.00932 -0.0568 0.2237 1.0000
8.250 1.2466 0.01772 0.00985 -0.0561 0.1973 1.0000
8.500 1.2673 0.01846 0.01046 -0.0554 0.1731 1.0000
8.750 1.2872 0.01925 0.01117 -0.0545 0.1572 1.0000
9.000 1.3070 0.02003 0.01194 -0.0537 0.1473 1.0000
9.250 1.3257 0.02086 0.01279 -0.0526 0.1397 1.0000
9.500 1.3444 0.02165 0.01364 -0.0516 0.1332 1.0000
9.750 1.3601 0.02264 0.01465 -0.0502 0.1266 1.0000
10.000 1.3774 0.02347 0.01559 -0.0491 0.1191 1.0000
10.250 1.3909 0.02454 0.01671 -0.0474 0.1123 1.0000
10.500 1.4074 0.02531 0.01761 -0.0462 0.1034 1.0000
10.750 1.4264 0.02587 0.01833 -0.0452 0.0909 1.0000
11.000 1.4408 0.02671 0.01901 -0.0438 0.0665 1.0000
11.250 1.4354 0.02871 0.02088 -0.0401 0.0583 1.0000
11.500 1.4280 0.03111 0.02344 -0.0369 0.0524 1.0000
11.750 1.4164 0.03415 0.02659 -0.0342 0.0475 1.0000
12.000 1.4119 0.03691 0.02951 -0.0327 0.0427 1.0000
12.250 1.3998 0.04066 0.03333 -0.0317 0.0402 1.0000
12.500 1.4027 0.04315 0.03600 -0.0313 0.0369 1.0000
12.750 1.4012 0.04623 0.03920 -0.0312 0.0347 1.0000
13.000 1.3972 0.04975 0.04280 -0.0315 0.0333 1.0000
13.250 1.3897 0.05375 0.04686 -0.0319 0.0322 1.0000
13.500 1.3880 0.05710 0.05037 -0.0321 0.0311 1.0000
13.750 1.3852 0.06061 0.05400 -0.0324 0.0300 1.0000
14.000 1.3821 0.06417 0.05766 -0.0328 0.0291 1.0000
14.250 1.3788 0.06778 0.06136 -0.0333 0.0283 1.0000
14.500 1.3754 0.07148 0.06515 -0.0340 0.0275 1.0000
14.750 1.3714 0.07526 0.06897 -0.0347 0.0268 1.0000
15.000 1.3681 0.07872 0.07246 -0.0347 0.0261 1.0000
15.250 1.3663 0.08235 0.07625 -0.0353 0.0255 1.0000
15.500 1.3644 0.08603 0.08007 -0.0359 0.0248 1.0000
15.750 1.3627 0.08966 0.08382 -0.0365 0.0243 1.0000
16.000 1.3614 0.09323 0.08750 -0.0370 0.0238 1.0000
16.250 1.3594 0.09701 0.09141 -0.0378 0.0234 1.0000
16.500 1.3563 0.10105 0.09557 -0.0388 0.0231 1.0000
16.750 1.3528 0.10520 0.09985 -0.0399 0.0228 1.0000
17.000 1.3488 0.10952 0.10430 -0.0413 0.0225 1.0000
17.250 1.3440 0.11407 0.10900 -0.0429 0.0223 1.0000
17.500 1.3379 0.11896 0.11403 -0.0448 0.0221 1.0000
17.750 1.3302 0.12429 0.11952 -0.0471 0.0220 1.0000
18.000 1.3200 0.13029 0.12570 -0.0501 0.0220 1.0000
18.250 1.3064 0.13729 0.13291 -0.0540 0.0220 1.0000
18.500 1.2886 0.14559 0.14144 -0.0590 0.0221 1.0000
18.750 1.2606 0.15703 0.15318 -0.0664 0.0225 1.0000
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Polar data table (+)
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