GOE 9K AIRFOIL (goe09k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 9K AIRFOIL (goe09k-il) Reynolds number: 1,000,000 Max Cl/Cd: 63.39 at α=0.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe09k-il-1000000-n5.txt Download as CSV file: xf-goe09k-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5875 0.09389 0.09227 0.0064 1.0000 0.0011
-7.750 -0.5864 0.09061 0.08901 0.0051 1.0000 0.0012
-7.500 -0.5867 0.08746 0.08589 0.0039 1.0000 0.0013
-7.250 -0.5829 0.08382 0.08226 0.0012 1.0000 0.0013
-7.000 -0.5755 0.07985 0.07829 -0.0023 1.0000 0.0012
-6.750 -0.5658 0.07559 0.07402 -0.0062 1.0000 0.0016
-6.500 -0.5543 0.07135 0.06977 -0.0099 1.0000 0.0014
-6.250 -0.5373 0.06659 0.06498 -0.0140 1.0000 0.0019
-6.000 -0.5184 0.06180 0.06013 -0.0181 1.0000 0.0019
-5.750 -0.5002 0.05720 0.05545 -0.0210 1.0000 0.0019
-5.500 -0.4813 0.05282 0.05099 -0.0231 1.0000 0.0020
-5.250 -0.4617 0.04849 0.04655 -0.0247 1.0000 0.0020
-5.000 -0.4449 0.04396 0.04190 -0.0260 1.0000 0.0020
-4.750 -0.4261 0.04027 0.03808 -0.0266 1.0000 0.0021
-4.500 -0.4048 0.03655 0.03420 -0.0269 1.0000 0.0022
-4.250 -0.3830 0.03297 0.03045 -0.0267 1.0000 0.0023
-4.000 -0.3606 0.02958 0.02685 -0.0262 1.0000 0.0024
-3.750 -0.3378 0.02630 0.02334 -0.0252 1.0000 0.0026
-3.500 -0.3145 0.02320 0.02000 -0.0241 1.0000 0.0028
-3.250 -0.2833 0.01998 0.01646 -0.0236 0.9993 0.0032
-3.000 -0.2512 0.01714 0.01329 -0.0237 0.9981 0.0033
-2.500 -0.1906 0.01165 0.00709 -0.0238 0.9959 0.0018
-2.250 -0.1612 0.00972 0.00487 -0.0235 0.9951 0.0015
-2.000 -0.1333 0.00825 0.00318 -0.0230 0.9939 0.0014
-1.750 -0.1047 0.00729 0.00202 -0.0229 0.9924 0.0014
-1.500 -0.0750 0.00672 0.00132 -0.0232 0.9908 0.0018
-1.250 -0.0434 0.00640 0.00094 -0.0241 0.9891 0.0054
-1.000 -0.0105 0.00595 0.00069 -0.0254 0.9871 0.0818
-0.750 0.0164 0.00504 0.00059 -0.0258 0.9826 0.3605
-0.500 0.0501 0.00451 0.00051 -0.0276 0.9783 0.5199
-0.250 0.0789 0.00397 0.00044 -0.0280 0.9692 0.6809
0.000 0.1053 0.00334 0.00042 -0.0276 0.9584 0.8635
0.250 0.1963 0.00312 0.00034 -0.0421 0.9047 0.9997
0.500 0.2187 0.00345 0.00032 -0.0407 0.8087 1.0000
0.750 0.2358 0.00403 0.00037 -0.0383 0.6639 1.0000
1.000 0.2511 0.00518 0.00055 -0.0360 0.3766 1.0000
1.250 0.2686 0.00647 0.00081 -0.0344 0.0528 1.0000
1.500 0.2926 0.00691 0.00112 -0.0336 0.0040 1.0000
2.000 0.3411 0.00788 0.00227 -0.0317 0.0016 1.0000
2.250 0.3639 0.00877 0.00331 -0.0304 0.0016 1.0000
2.500 0.3868 0.01001 0.00471 -0.0288 0.0017 1.0000
2.750 0.4106 0.01162 0.00651 -0.0274 0.0019 1.0000
4.500 0.5724 0.03046 0.02733 -0.0160 0.0020 1.0000
4.750 0.5965 0.03433 0.03145 -0.0140 0.0015 1.0000
5.000 0.6167 0.03814 0.03549 -0.0129 0.0013 1.0000
5.250 0.6359 0.04214 0.03969 -0.0121 0.0013 1.0000
5.500 0.6540 0.04629 0.04402 -0.0117 0.0012 1.0000
5.750 0.6688 0.05025 0.04812 -0.0119 0.0011 1.0000
6.000 0.6814 0.05527 0.05329 -0.0123 0.0011 1.0000
6.250 0.6956 0.05985 0.05799 -0.0131 0.0011 1.0000
6.500 0.7084 0.06458 0.06282 -0.0144 0.0011 1.0000
6.750 0.7193 0.06940 0.06772 -0.0161 0.0011 1.0000
7.000 0.7280 0.07428 0.07267 -0.0184 0.0011 1.0000
7.250 0.7349 0.07902 0.07745 -0.0212 0.0011 1.0000
7.500 0.7395 0.08357 0.08202 -0.0242 0.0011 1.0000
7.750 0.7411 0.08800 0.08647 -0.0275 0.0011 1.0000
8.000 0.7359 0.09202 0.09047 -0.0304 0.0011 1.0000
8.250 0.7344 0.09611 0.09454 -0.0330 0.0011 1.0000
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Polar data table (+)
Polar graphs
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