GOE 9K AIRFOIL (goe09k-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 9K AIRFOIL (goe09k-il) Reynolds number: 100,000 Max Cl/Cd: 23.83 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe09k-il-100000.txt Download as CSV file: xf-goe09k-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 9K 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5970 0.10392 0.09901 0.0057 1.0000 0.0462
-8.000 -0.5974 0.10151 0.09667 0.0026 1.0000 0.0468
-7.750 -0.5968 0.09906 0.09428 -0.0029 1.0000 0.0472
-7.500 -0.5893 0.09598 0.09120 -0.0095 1.0000 0.0475
-7.250 -0.5848 0.08938 0.08465 -0.0003 1.0000 0.0520
-7.000 -0.5781 0.08567 0.08096 -0.0032 1.0000 0.0548
-6.750 -0.5680 0.08188 0.07716 -0.0090 1.0000 0.0572
-6.500 -0.5516 0.07834 0.07349 -0.0176 1.0000 0.0582
-6.250 -0.5478 0.07340 0.06867 -0.0132 1.0000 0.0625
-6.000 -0.5276 0.06964 0.06473 -0.0203 1.0000 0.0668
-5.750 -0.5190 0.06506 0.06022 -0.0192 1.0000 0.0710
-5.500 -0.4973 0.06105 0.05594 -0.0243 1.0000 0.0771
-5.250 -0.4743 0.05862 0.05312 -0.0276 1.0000 0.0866
-5.000 -0.4668 0.05312 0.04792 -0.0251 1.0000 0.0924
-4.750 -0.4470 0.04925 0.04387 -0.0267 1.0000 0.1036
-4.500 -0.4275 0.04569 0.04015 -0.0275 1.0000 0.1175
-4.250 -0.4055 0.04277 0.03692 -0.0287 1.0000 0.1409
-4.000 -0.3888 0.03911 0.03328 -0.0278 1.0000 0.1599
-3.250 -0.3407 0.03074 0.02495 -0.0234 1.0000 0.3060
-3.000 -0.2681 0.02658 0.01853 -0.0275 1.0000 0.1001
-2.750 -0.2355 0.02311 0.01431 -0.0256 1.0000 0.0578
-2.500 -0.2088 0.02035 0.01128 -0.0245 1.0000 0.0516
-2.250 -0.1808 0.01848 0.00891 -0.0230 1.0000 0.0463
-2.000 -0.1546 0.01653 0.00680 -0.0217 1.0000 0.0456
-1.750 -0.1301 0.01488 0.00515 -0.0205 1.0000 0.0530
-1.500 -0.1063 0.01354 0.00381 -0.0192 1.0000 0.0702
-1.250 -0.0608 0.00956 0.00231 -0.0219 1.0000 1.0000
-1.000 -0.0369 0.00955 0.00185 -0.0210 1.0000 1.0000
-0.750 -0.0129 0.00955 0.00158 -0.0202 1.0000 1.0000
-0.500 0.0109 0.00956 0.00140 -0.0194 1.0000 1.0000
-0.250 0.0347 0.00959 0.00128 -0.0187 1.0000 1.0000
0.000 0.0585 0.00962 0.00121 -0.0180 1.0000 1.0000
0.250 0.0822 0.00967 0.00121 -0.0173 1.0000 1.0000
0.500 0.1059 0.00972 0.00127 -0.0165 1.0000 1.0000
0.750 0.1294 0.00979 0.00139 -0.0158 1.0000 1.0000
1.000 0.1530 0.00987 0.00156 -0.0151 1.0000 1.0000
1.250 0.1764 0.00996 0.00178 -0.0143 1.0000 1.0000
1.500 0.1998 0.01007 0.00207 -0.0136 1.0000 1.0000
1.750 0.2232 0.01019 0.00253 -0.0128 1.0000 1.0000
2.000 0.2464 0.01034 0.00304 -0.0120 1.0000 1.0000
2.250 0.3528 0.01573 0.00558 -0.0255 0.0474 1.0000
2.500 0.3770 0.01731 0.00726 -0.0239 0.0435 1.0000
2.750 0.4039 0.01928 0.00935 -0.0227 0.0433 1.0000
3.000 0.4319 0.02145 0.01178 -0.0215 0.0443 1.0000
3.250 0.4611 0.02387 0.01466 -0.0200 0.0521 1.0000
3.500 0.4915 0.02722 0.01853 -0.0182 0.0752 1.0000
4.750 0.6313 0.04437 0.03859 -0.0130 0.1614 1.0000
5.250 0.6617 0.05148 0.04590 -0.0117 0.1170 1.0000
5.500 0.6755 0.05558 0.05006 -0.0113 0.1021 1.0000
5.750 0.6899 0.05932 0.05409 -0.0119 0.0899 1.0000
6.000 0.7030 0.06355 0.05853 -0.0130 0.0810 1.0000
6.250 0.7135 0.06818 0.06322 -0.0133 0.0753 1.0000
6.500 0.7251 0.07220 0.06733 -0.0137 0.0686 1.0000
6.750 0.7335 0.07685 0.07215 -0.0168 0.0661 1.0000
7.000 0.7411 0.08114 0.07654 -0.0196 0.0619 1.0000
7.250 0.7483 0.08675 0.08204 -0.0167 0.0586 1.0000
7.500 0.7514 0.09053 0.08595 -0.0219 0.0581 1.0000
7.750 0.7525 0.09461 0.09005 -0.0271 0.0572 1.0000
8.000 0.7493 0.09858 0.09398 -0.0310 0.0559 1.0000
8.250 0.7479 0.10254 0.09790 -0.0339 0.0544 1.0000
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Polar data table (+)
Polar graphs
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