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GOE 362 AIRFOIL (goe362-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 362 AIRFOIL (goe362-il)
Reynolds number: 100,000
Max Cl/Cd: 58.38 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe362-il-100000.txt
Download as CSV file: xf-goe362-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 362 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3122   0.09521   0.09047  -0.0232   1.0000   0.0650
  -7.250  -0.3182   0.09437   0.08974  -0.0243   1.0000   0.0661
  -7.000  -0.3186   0.09376   0.08924  -0.0299   1.0000   0.0668
  -6.750  -0.3118   0.09234   0.08785  -0.0365   1.0000   0.0671
  -6.500  -0.3099   0.08583   0.08144  -0.0269   1.0000   0.0686
  -6.250  -0.3044   0.08278   0.07843  -0.0235   1.0000   0.0719
  -6.000  -0.3014   0.08053   0.07625  -0.0237   1.0000   0.0751
  -5.750  -0.2972   0.07853   0.07431  -0.0261   1.0000   0.0781
  -5.500  -0.2761   0.07745   0.07314  -0.0400   1.0000   0.0806
  -5.250  -0.2826   0.07315   0.06898  -0.0329   1.0000   0.0817
  -5.000  -0.2825   0.07046   0.06636  -0.0292   1.0000   0.0833
  -4.750  -0.2781   0.06813   0.06408  -0.0280   1.0000   0.0859
  -4.500  -0.2681   0.06571   0.06165  -0.0296   1.0000   0.0899
  -4.250  -0.2365   0.06226   0.05801  -0.0399   1.0000   0.0953
  -4.000  -0.2356   0.05957   0.05542  -0.0365   1.0000   0.0970
  -3.750  -0.2264   0.05725   0.05312  -0.0359   1.0000   0.1005
  -3.500  -0.1696   0.05238   0.04800  -0.0477   0.9942   0.1109
  -3.250  -0.1176   0.04824   0.04365  -0.0563   0.9865   0.1247
  -3.000  -0.0734   0.04463   0.03992  -0.0621   0.9787   0.1402
  -2.750  -0.0254   0.04110   0.03624  -0.0682   0.9715   0.1562
  -2.500   0.0235   0.03820   0.03305  -0.0745   0.9624   0.1823
  -2.250   0.0999   0.02950   0.02287  -0.0838   0.9589   0.0953
  -2.000   0.1446   0.02610   0.01909  -0.0871   0.9513   0.0887
  -1.750   0.1929   0.02347   0.01576  -0.0904   0.9438   0.0911
  -1.500   0.2359   0.02157   0.01343  -0.0929   0.9345   0.0982
  -1.250   0.2853   0.02010   0.01174  -0.0965   0.9275   0.1148
  -1.000   0.3262   0.01901   0.01047  -0.0984   0.9165   0.1368
  -0.750   0.3675   0.01793   0.00953  -0.1005   0.9062   0.1711
  -0.500   0.4123   0.01693   0.00867  -0.1030   0.8977   0.2281
  -0.250   0.4475   0.01608   0.00806  -0.1038   0.8846   0.2958
   0.000   0.4905   0.01380   0.00734  -0.1058   0.8726   1.0000
   0.250   0.5238   0.01370   0.00693  -0.1059   0.8577   1.0000
   0.500   0.5549   0.01362   0.00663  -0.1055   0.8419   1.0000
   0.750   0.5843   0.01357   0.00639  -0.1049   0.8255   1.0000
   1.000   0.6107   0.01362   0.00628  -0.1038   0.8065   1.0000
   1.250   0.6370   0.01368   0.00620  -0.1027   0.7871   1.0000
   1.500   0.6636   0.01376   0.00612  -0.1015   0.7682   1.0000
   1.750   0.6891   0.01390   0.00613  -0.1004   0.7480   1.0000
   2.000   0.7145   0.01407   0.00617  -0.0993   0.7275   1.0000
   2.250   0.7405   0.01425   0.00619  -0.0983   0.7086   1.0000
   2.500   0.7656   0.01451   0.00637  -0.0973   0.6883   1.0000
   2.750   0.7911   0.01478   0.00653  -0.0964   0.6694   1.0000
   3.000   0.8168   0.01507   0.00671  -0.0955   0.6518   1.0000
   3.250   0.8426   0.01539   0.00692  -0.0947   0.6352   1.0000
   3.500   0.8679   0.01574   0.00724  -0.0940   0.6185   1.0000
   3.750   0.8932   0.01611   0.00758  -0.0932   0.6024   1.0000
   4.000   0.9185   0.01649   0.00793  -0.0925   0.5871   1.0000
   4.250   0.9439   0.01686   0.00829  -0.0919   0.5723   1.0000
   4.500   0.9692   0.01725   0.00871  -0.0912   0.5580   1.0000
   4.750   0.9945   0.01763   0.00910  -0.0905   0.5440   1.0000
   5.000   1.0198   0.01803   0.00951  -0.0898   0.5304   1.0000
   5.250   1.0447   0.01841   0.00992  -0.0890   0.5160   1.0000
   5.500   1.0688   0.01875   0.01033  -0.0881   0.4991   1.0000
   5.750   1.0923   0.01900   0.01058  -0.0870   0.4799   1.0000
   6.000   1.1160   0.01925   0.01076  -0.0859   0.4607   1.0000
   6.250   1.1389   0.01963   0.01119  -0.0848   0.4420   1.0000
   6.500   1.1618   0.02004   0.01171  -0.0838   0.4239   1.0000
   6.750   1.1846   0.02043   0.01216  -0.0827   0.4053   1.0000
   7.000   1.2069   0.02081   0.01256  -0.0816   0.3861   1.0000
   7.250   1.2273   0.02112   0.01306  -0.0802   0.3632   1.0000
   7.500   1.2472   0.02140   0.01349  -0.0786   0.3382   1.0000
   7.750   1.2645   0.02166   0.01384  -0.0767   0.3037   1.0000
   8.000   1.2778   0.02233   0.01440  -0.0744   0.2514   1.0000
   8.250   1.2867   0.02396   0.01563  -0.0717   0.1965   1.0000
   8.500   1.2977   0.02573   0.01714  -0.0694   0.1642   1.0000
   8.750   1.3100   0.02739   0.01867  -0.0674   0.1423   1.0000
   9.000   1.3221   0.02896   0.02020  -0.0655   0.1242   1.0000
   9.250   1.3334   0.03070   0.02187  -0.0635   0.1091   1.0000
   9.500   1.3448   0.03277   0.02384  -0.0617   0.0953   1.0000
   9.750   1.3583   0.03542   0.02637  -0.0601   0.0818   1.0000
  10.000   1.3684   0.03744   0.02857  -0.0580   0.0711   1.0000
  10.250   1.3842   0.04041   0.03177  -0.0564   0.0633   1.0000
  10.500   1.4024   0.04381   0.03509  -0.0558   0.0566   1.0000
  10.750   1.4094   0.04605   0.03781  -0.0533   0.0528   1.0000
  11.000   1.4201   0.04901   0.04105  -0.0515   0.0499   1.0000
  11.250   1.4300   0.05225   0.04446  -0.0501   0.0477   1.0000
  11.500   1.4363   0.05772   0.05014  -0.0491   0.0458   1.0000
  11.750   1.4253   0.06028   0.05311  -0.0455   0.0452   1.0000
  12.000   1.4105   0.06315   0.05633  -0.0422   0.0446   1.0000
  12.250   1.3944   0.06657   0.06008  -0.0399   0.0442   1.0000
  12.500   1.3764   0.07050   0.06431  -0.0386   0.0439   1.0000
  12.750   1.3572   0.07507   0.06917  -0.0383   0.0438   1.0000
  13.000   1.3369   0.08020   0.07455  -0.0390   0.0439   1.0000
  13.250   1.3158   0.08597   0.08055  -0.0407   0.0441   1.0000
  13.500   1.2935   0.09239   0.08719  -0.0433   0.0443   1.0000
  13.750   1.2707   0.09949   0.09448  -0.0468   0.0447   1.0000
  14.000   1.2491   0.10714   0.10227  -0.0509   0.0452   1.0000
  14.250   1.2284   0.11532   0.11057  -0.0554   0.0457   1.0000
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