GOE 7K AIRFOIL (goe07k-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 7K AIRFOIL (goe07k-il) Reynolds number: 50,000 Max Cl/Cd: 25.18 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe07k-il-50000-n5.txt Download as CSV file: xf-goe07k-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 7K AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4729 0.12570 0.11961 -0.0266 1.0000 0.0863
-8.000 -0.4856 0.12382 0.11781 -0.0286 0.9981 0.0875
-7.750 -0.4939 0.12149 0.11554 -0.0320 0.9939 0.0879
-7.500 -0.5013 0.11876 0.11283 -0.0362 0.9893 0.0883
-7.250 -0.4714 0.11242 0.10645 -0.0308 0.9895 0.0938
-7.000 -0.4736 0.10953 0.10358 -0.0317 0.9860 0.0961
-6.750 -0.4760 0.10622 0.10029 -0.0339 0.9817 0.0992
-6.500 -0.4865 0.10342 0.09741 -0.0430 0.9749 0.1035
-6.250 -0.4778 0.09860 0.09266 -0.0410 0.9728 0.1052
-6.000 -0.4689 0.09478 0.08883 -0.0406 0.9702 0.1074
-5.750 -0.4563 0.08818 0.08202 -0.0447 0.9664 0.0688
-5.250 -0.4305 0.07597 0.06922 -0.0517 0.9586 0.0472
-5.000 -0.4207 0.07210 0.06518 -0.0518 0.9555 0.0469
-4.750 -0.4098 0.06834 0.06116 -0.0517 0.9524 0.0470
-4.500 -0.3947 0.06434 0.05676 -0.0521 0.9493 0.0473
-4.250 -0.3772 0.06071 0.05280 -0.0523 0.9466 0.0471
-4.000 -0.3592 0.05727 0.04897 -0.0522 0.9441 0.0469
-3.750 -0.3454 0.05427 0.04555 -0.0507 0.9410 0.0468
-3.500 -0.3286 0.05132 0.04201 -0.0493 0.9384 0.0482
-3.250 -0.3111 0.04931 0.03992 -0.0487 0.9359 0.0512
-3.000 -0.2886 0.04709 0.03720 -0.0480 0.9334 0.0531
-2.750 -0.2631 0.04497 0.03447 -0.0475 0.9313 0.0562
-2.500 -0.2432 0.04341 0.03224 -0.0457 0.9285 0.0596
-2.250 -0.2234 0.04170 0.03026 -0.0443 0.9260 0.0630
-2.000 -0.2006 0.04062 0.02888 -0.0435 0.9232 0.0691
-1.750 -0.1726 0.03938 0.02727 -0.0435 0.9208 0.0765
-1.500 -0.1427 0.03862 0.02618 -0.0438 0.9187 0.0873
-1.250 -0.1070 0.03798 0.02529 -0.0456 0.9171 0.1025
-1.000 -0.0786 0.03748 0.02464 -0.0461 0.9147 0.1158
-0.750 -0.0547 0.03710 0.02412 -0.0458 0.9114 0.1323
-0.500 -0.0277 0.03685 0.02381 -0.0460 0.9084 0.1491
-0.250 0.0717 0.03483 0.02445 -0.0622 0.9112 1.0000
0.000 0.0945 0.03524 0.02444 -0.0616 0.9075 1.0000
0.250 0.1214 0.03573 0.02456 -0.0619 0.9041 1.0000
0.500 0.1495 0.03627 0.02479 -0.0625 0.9009 1.0000
0.750 0.1654 0.03658 0.02489 -0.0609 0.8957 1.0000
1.000 0.1902 0.03705 0.02513 -0.0609 0.8913 1.0000
1.250 0.2206 0.03763 0.02550 -0.0620 0.8878 1.0000
1.500 0.2377 0.03798 0.02570 -0.0606 0.8816 1.0000
1.750 0.2635 0.03845 0.02603 -0.0608 0.8764 1.0000
2.000 0.2957 0.03904 0.02649 -0.0622 0.8728 1.0000
2.250 0.3101 0.03937 0.02675 -0.0604 0.8652 1.0000
2.500 0.3391 0.03989 0.02719 -0.0612 0.8604 1.0000
2.750 0.3602 0.04035 0.02761 -0.0606 0.8541 1.0000
3.000 0.3847 0.04082 0.02804 -0.0606 0.8479 1.0000
3.250 0.4147 0.04132 0.02853 -0.0616 0.8429 1.0000
3.500 0.4318 0.04175 0.02897 -0.0603 0.8347 1.0000
3.750 0.4650 0.04223 0.02948 -0.0617 0.8300 1.0000
4.000 0.4794 0.04269 0.02998 -0.0600 0.8210 1.0000
4.250 0.5119 0.04313 0.03048 -0.0613 0.8159 1.0000
4.750 0.5605 0.04399 0.03154 -0.0611 0.8012 1.0000
5.000 0.5750 0.04450 0.03214 -0.0595 0.7909 1.0000
5.250 0.6060 0.04488 0.03267 -0.0605 0.7851 1.0000
5.500 0.6233 0.04538 0.03332 -0.0593 0.7749 1.0000
5.750 0.6440 0.04586 0.03394 -0.0586 0.7657 1.0000
6.000 0.6738 0.04613 0.03445 -0.0592 0.7583 1.0000
6.250 0.6904 0.04666 0.03517 -0.0579 0.7471 1.0000
6.500 0.7152 0.04700 0.03572 -0.0577 0.7379 1.0000
6.750 0.7458 0.04692 0.03593 -0.0580 0.7281 1.0000
7.000 0.7716 0.04658 0.03586 -0.0572 0.7136 1.0000
7.250 0.7979 0.04609 0.03569 -0.0563 0.6986 1.0000
7.500 0.8222 0.04574 0.03566 -0.0551 0.6835 1.0000
7.750 0.8509 0.04482 0.03510 -0.0540 0.6672 1.0000
8.000 0.8644 0.04427 0.03487 -0.0508 0.6413 1.0000
8.250 0.8881 0.04216 0.03312 -0.0472 0.6076 1.0000
8.500 0.8998 0.04145 0.03270 -0.0433 0.5663 1.0000
8.750 0.9382 0.03726 0.02692 -0.0373 0.2935 1.0000
9.000 0.9255 0.04014 0.02885 -0.0326 0.1838 1.0000
9.250 0.9193 0.04299 0.03103 -0.0292 0.1139 1.0000
9.500 0.9184 0.04554 0.03325 -0.0264 0.0859 1.0000
9.750 0.9224 0.04776 0.03541 -0.0239 0.0711 1.0000
10.000 0.9322 0.04958 0.03734 -0.0218 0.0607 1.0000
10.250 0.9487 0.05110 0.03904 -0.0201 0.0533 1.0000
10.500 0.9764 0.05242 0.04036 -0.0194 0.0464 1.0000
10.750 1.0254 0.05360 0.04199 -0.0202 0.0403 1.0000
11.000 1.0695 0.05600 0.04452 -0.0216 0.0363 1.0000
11.250 1.1013 0.05921 0.04834 -0.0215 0.0342 1.0000
11.500 1.1176 0.06279 0.05244 -0.0202 0.0331 1.0000
11.750 1.1209 0.06615 0.05622 -0.0177 0.0322 1.0000
12.000 1.1171 0.06949 0.05997 -0.0149 0.0315 1.0000
12.250 1.1096 0.07281 0.06363 -0.0121 0.0310 1.0000
12.500 1.0983 0.07638 0.06751 -0.0093 0.0307 1.0000
12.750 1.0841 0.08013 0.07155 -0.0068 0.0304 1.0000
13.000 1.0677 0.08418 0.07589 -0.0047 0.0305 1.0000
13.250 1.0487 0.08849 0.08045 -0.0031 0.0303 1.0000
13.500 1.0285 0.09314 0.08533 -0.0023 0.0304 1.0000
13.750 1.0067 0.09833 0.09074 -0.0023 0.0307 1.0000
14.000 0.9839 0.10411 0.09672 -0.0032 0.0311 1.0000
14.250 0.9602 0.11070 0.10346 -0.0053 0.0315 1.0000
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