GOE 766 AIRFOIL (goe766-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 766 AIRFOIL (goe766-il) Reynolds number: 50,000 Max Cl/Cd: 19.16 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe766-il-50000.txt Download as CSV file: xf-goe766-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 766 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4683 0.10005 0.09265 0.0171 1.0000 0.3967
-8.250 -0.4376 0.09490 0.08748 0.0172 1.0000 0.4046
-8.000 -0.6502 0.06920 0.06168 -0.0149 1.0000 0.1908
-7.750 -0.6327 0.06488 0.05740 -0.0144 1.0000 0.1867
-7.500 -0.6631 0.05790 0.04979 -0.0144 1.0000 0.1734
-7.250 -0.6567 0.05399 0.04571 -0.0133 1.0000 0.1723
-7.000 -0.6500 0.05029 0.04177 -0.0119 1.0000 0.1711
-6.750 -0.6420 0.04679 0.03797 -0.0102 1.0000 0.1699
-6.500 -0.6323 0.04355 0.03437 -0.0084 1.0000 0.1693
-6.250 -0.6208 0.04078 0.03121 -0.0065 1.0000 0.1708
-6.000 -0.6080 0.03836 0.02830 -0.0043 1.0000 0.1734
-5.750 -0.5906 0.03590 0.02568 -0.0028 1.0000 0.1768
-5.500 -0.5704 0.03385 0.02357 -0.0015 1.0000 0.1811
-5.250 -0.5512 0.03206 0.02150 0.0002 1.0000 0.1877
-5.000 -0.5306 0.03022 0.01953 0.0016 1.0000 0.1954
-4.750 -0.5086 0.02866 0.01784 0.0029 1.0000 0.2052
-4.500 -0.4859 0.02709 0.01634 0.0041 1.0000 0.2184
-4.250 -0.4625 0.02561 0.01490 0.0052 1.0000 0.2362
-4.000 -0.4386 0.02415 0.01360 0.0064 1.0000 0.2624
-3.750 -0.4158 0.02272 0.01255 0.0076 1.0000 0.3027
-3.500 -0.3955 0.02129 0.01163 0.0093 1.0000 0.3669
-3.250 -0.3824 0.01967 0.01098 0.0124 1.0000 0.4731
-3.000 -0.3756 0.01874 0.01148 0.0195 1.0000 0.6856
-2.750 -0.2809 0.02135 0.01409 0.0181 1.0000 0.8837
-2.500 -0.1007 0.02249 0.01436 -0.0052 1.0000 0.9578
-2.250 0.0191 0.02126 0.01274 -0.0231 1.0000 1.0000
-2.000 0.0263 0.02083 0.01235 -0.0216 1.0000 1.0000
-1.750 0.0298 0.02058 0.01218 -0.0196 1.0000 1.0000
-1.500 0.0187 0.02073 0.01250 -0.0161 1.0000 1.0000
-1.250 0.0115 0.02174 0.01359 -0.0163 0.9844 1.0000
-1.000 0.1415 0.02116 0.01285 -0.0357 0.9328 1.0000
-0.750 0.2261 0.02051 0.01200 -0.0457 0.8780 1.0000
-0.500 0.2639 0.02036 0.01160 -0.0470 0.8303 1.0000
-0.250 0.2852 0.02046 0.01149 -0.0455 0.7921 1.0000
0.000 0.3039 0.02064 0.01146 -0.0435 0.7608 1.0000
0.250 0.3216 0.02089 0.01155 -0.0416 0.7323 1.0000
0.500 0.3403 0.02120 0.01170 -0.0397 0.7081 1.0000
0.750 0.3581 0.02159 0.01200 -0.0380 0.6842 1.0000
1.000 0.3770 0.02203 0.01233 -0.0364 0.6628 1.0000
1.250 0.3961 0.02252 0.01272 -0.0348 0.6433 1.0000
1.500 0.4149 0.02306 0.01317 -0.0332 0.6249 1.0000
1.750 0.4336 0.02366 0.01372 -0.0317 0.6079 1.0000
2.000 0.4523 0.02434 0.01436 -0.0302 0.5920 1.0000
2.250 0.4710 0.02507 0.01505 -0.0288 0.5775 1.0000
2.500 0.4902 0.02576 0.01567 -0.0272 0.5644 1.0000
2.750 0.5089 0.02656 0.01646 -0.0258 0.5512 1.0000
3.000 0.5262 0.02759 0.01756 -0.0245 0.5387 1.0000
3.250 0.5453 0.02847 0.01840 -0.0231 0.5280 1.0000
3.500 0.5633 0.02945 0.01942 -0.0217 0.5165 1.0000
3.750 0.5793 0.03072 0.02079 -0.0204 0.5058 1.0000
4.000 0.6000 0.03154 0.02154 -0.0189 0.4964 1.0000
4.250 0.6126 0.03316 0.02333 -0.0177 0.4853 1.0000
4.500 0.6335 0.03402 0.02414 -0.0161 0.4764 1.0000
4.750 0.6446 0.03579 0.02609 -0.0148 0.4653 1.0000
5.000 0.6603 0.03716 0.02750 -0.0133 0.4555 1.0000
5.250 0.6772 0.03834 0.02873 -0.0117 0.4449 1.0000
5.500 0.6848 0.04051 0.03105 -0.0102 0.4342 1.0000
5.750 0.7109 0.04081 0.03127 -0.0083 0.4239 1.0000
6.000 0.7113 0.04360 0.03427 -0.0069 0.4122 1.0000
6.250 0.7201 0.04562 0.03638 -0.0052 0.4013 1.0000
6.500 0.7516 0.04526 0.03594 -0.0031 0.3891 1.0000
6.750 0.7398 0.04925 0.04018 -0.0018 0.3774 1.0000
7.000 0.7416 0.05191 0.04292 -0.0002 0.3656 1.0000
7.250 0.7651 0.05221 0.04323 0.0020 0.3522 1.0000
7.500 0.7965 0.05155 0.04254 0.0043 0.3375 1.0000
7.750 0.7333 0.06127 0.05246 0.0037 0.3317 1.0000
8.000 0.7536 0.06180 0.05303 0.0060 0.3180 1.0000
8.250 0.6832 0.07253 0.06366 0.0028 0.3175 1.0000
8.500 0.6443 0.08020 0.07123 -0.0001 0.3154 1.0000
8.750 0.7450 0.07131 0.06258 0.0092 0.2880 1.0000
9.000 0.6800 0.08306 0.07419 0.0033 0.2899 1.0000
9.250 0.6568 0.08978 0.08085 0.0007 0.2875 1.0000
9.500 0.6370 0.09617 0.08719 -0.0019 0.2870 1.0000
9.750 0.6284 0.10205 0.09309 -0.0041 0.2902 1.0000
10.000 0.6340 0.10681 0.09786 -0.0049 0.2887 1.0000
10.250 0.5775 0.12193 0.11297 -0.0168 0.3720 1.0000
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Polar data table (+)
Polar graphs
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