GOE 286 AIRFOIL (goe286-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 286 AIRFOIL (goe286-il) Reynolds number: 100,000 Max Cl/Cd: 54.47 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe286-il-100000-n5.txt Download as CSV file: xf-goe286-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3573 0.09088 0.08624 -0.0217 1.0000 0.0623
-7.500 -0.3549 0.08790 0.08332 -0.0235 1.0000 0.0640
-7.250 -0.3515 0.08466 0.08013 -0.0278 1.0000 0.0665
-7.000 -0.3492 0.08125 0.07667 -0.0386 1.0000 0.0685
-6.750 -0.3444 0.07788 0.07320 -0.0425 1.0000 0.0688
-6.500 -0.3420 0.07380 0.06933 -0.0372 1.0000 0.0701
-6.250 -0.3375 0.07153 0.06714 -0.0341 1.0000 0.0718
-6.000 -0.3335 0.06907 0.06470 -0.0334 1.0000 0.0735
-5.750 -0.3104 0.06503 0.06057 -0.0381 0.9947 0.0757
-5.500 -0.2648 0.05495 0.04995 -0.0516 0.9856 0.0563
-5.250 -0.2317 0.05031 0.04510 -0.0566 0.9781 0.0559
-5.000 -0.1967 0.04593 0.04052 -0.0612 0.9714 0.0543
-4.750 -0.1595 0.04102 0.03524 -0.0659 0.9628 0.0515
-4.500 -0.1225 0.03590 0.02955 -0.0697 0.9516 0.0494
-4.250 -0.0887 0.03352 0.02690 -0.0718 0.9379 0.0511
-4.000 -0.0565 0.03077 0.02374 -0.0732 0.9223 0.0515
-3.750 -0.0260 0.02810 0.02061 -0.0739 0.9063 0.0508
-3.500 0.0041 0.02594 0.01802 -0.0743 0.8906 0.0505
-3.250 0.0339 0.02418 0.01587 -0.0744 0.8750 0.0506
-3.000 0.0633 0.02274 0.01409 -0.0742 0.8592 0.0509
-2.750 0.0917 0.02171 0.01282 -0.0739 0.8429 0.0526
-2.500 0.1197 0.02076 0.01160 -0.0734 0.8265 0.0544
-2.250 0.1472 0.01983 0.01041 -0.0728 0.8092 0.0551
-2.000 0.1743 0.01902 0.00941 -0.0721 0.7914 0.0556
-1.750 0.2012 0.01832 0.00856 -0.0715 0.7732 0.0564
-1.500 0.2281 0.01773 0.00784 -0.0708 0.7548 0.0572
-1.250 0.2544 0.01715 0.00723 -0.0703 0.7361 0.0586
-0.750 0.3071 0.01642 0.00635 -0.0690 0.6969 0.0640
-0.500 0.3335 0.01621 0.00595 -0.0682 0.6762 0.0691
0.000 0.3863 0.01580 0.00524 -0.0669 0.6359 0.0847
0.250 0.4130 0.01557 0.00502 -0.0664 0.6165 0.1173
0.500 0.4327 0.01376 0.00501 -0.0651 0.5994 0.6883
1.000 0.4972 0.01359 0.00480 -0.0660 0.5633 1.0000
1.250 0.5240 0.01376 0.00480 -0.0656 0.5467 1.0000
1.500 0.5509 0.01393 0.00482 -0.0653 0.5303 1.0000
1.750 0.5778 0.01411 0.00486 -0.0651 0.5137 1.0000
2.000 0.6045 0.01430 0.00491 -0.0648 0.4974 1.0000
2.250 0.6311 0.01451 0.00498 -0.0645 0.4816 1.0000
2.500 0.6575 0.01474 0.00506 -0.0641 0.4660 1.0000
2.750 0.6837 0.01500 0.00518 -0.0638 0.4514 1.0000
3.000 0.7100 0.01527 0.00532 -0.0635 0.4386 1.0000
3.250 0.7365 0.01554 0.00552 -0.0632 0.4277 1.0000
3.500 0.7628 0.01584 0.00574 -0.0630 0.4185 1.0000
3.750 0.7891 0.01613 0.00598 -0.0627 0.4095 1.0000
4.000 0.8155 0.01644 0.00625 -0.0625 0.4011 1.0000
4.250 0.8416 0.01675 0.00654 -0.0622 0.3931 1.0000
4.500 0.8678 0.01707 0.00685 -0.0620 0.3851 1.0000
4.750 0.8935 0.01740 0.00715 -0.0617 0.3759 1.0000
5.000 0.9192 0.01772 0.00749 -0.0614 0.3647 1.0000
5.250 0.9444 0.01805 0.00781 -0.0611 0.3529 1.0000
5.500 0.9694 0.01840 0.00814 -0.0607 0.3420 1.0000
5.750 0.9948 0.01873 0.00852 -0.0604 0.3321 1.0000
6.000 1.0200 0.01908 0.00893 -0.0600 0.3242 1.0000
6.250 1.0453 0.01943 0.00936 -0.0597 0.3169 1.0000
6.500 1.0701 0.01980 0.00979 -0.0593 0.3087 1.0000
6.750 1.0944 0.02018 0.01025 -0.0589 0.2987 1.0000
7.000 1.1189 0.02056 0.01074 -0.0585 0.2888 1.0000
7.250 1.1427 0.02098 0.01123 -0.0580 0.2790 1.0000
7.500 1.1663 0.02141 0.01175 -0.0575 0.2676 1.0000
7.750 1.1895 0.02186 0.01233 -0.0569 0.2545 1.0000
8.000 1.2117 0.02238 0.01290 -0.0563 0.2383 1.0000
8.250 1.2330 0.02296 0.01352 -0.0555 0.2207 1.0000
8.500 1.2538 0.02359 0.01420 -0.0547 0.2043 1.0000
8.750 1.2738 0.02428 0.01497 -0.0539 0.1890 1.0000
9.000 1.2925 0.02508 0.01579 -0.0529 0.1745 1.0000
9.250 1.3091 0.02602 0.01672 -0.0517 0.1608 1.0000
9.500 1.3233 0.02712 0.01779 -0.0503 0.1490 1.0000
9.750 1.3353 0.02836 0.01901 -0.0487 0.1393 1.0000
10.000 1.3470 0.02957 0.02032 -0.0470 0.1313 1.0000
10.250 1.3539 0.03104 0.02181 -0.0449 0.1241 1.0000
10.500 1.3634 0.03220 0.02314 -0.0430 0.1177 1.0000
10.750 1.3674 0.03366 0.02470 -0.0407 0.1117 1.0000
11.000 1.3721 0.03518 0.02636 -0.0387 0.1060 1.0000
11.250 1.3796 0.03662 0.02802 -0.0372 0.0980 1.0000
11.500 1.3942 0.03760 0.02937 -0.0362 0.0747 1.0000
11.750 1.3887 0.04028 0.03186 -0.0349 0.0654 1.0000
12.000 1.3805 0.04355 0.03506 -0.0341 0.0606 1.0000
12.250 1.3717 0.04716 0.03877 -0.0337 0.0567 1.0000
12.500 1.3605 0.05138 0.04311 -0.0340 0.0534 1.0000
12.750 1.3466 0.05627 0.04810 -0.0349 0.0511 1.0000
13.000 1.3385 0.06058 0.05262 -0.0357 0.0479 1.0000
13.250 1.3286 0.06528 0.05751 -0.0368 0.0450 1.0000
13.500 1.3153 0.07053 0.06291 -0.0382 0.0430 1.0000
13.750 1.3044 0.07560 0.06815 -0.0396 0.0407 1.0000
14.000 1.2950 0.08056 0.07330 -0.0410 0.0378 1.0000
14.250 1.2834 0.08598 0.07886 -0.0427 0.0359 1.0000
14.500 1.2732 0.09133 0.08434 -0.0445 0.0340 1.0000
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Polar data table (+)
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