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GOE 364 AIRFOIL (goe364-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 364 AIRFOIL (goe364-il)
Reynolds number: 1,000,000
Max Cl/Cd: 124.47 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe364-il-1000000-n5.txt
Download as CSV file: xf-goe364-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 364 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.0441   0.08626   0.08367  -0.0916   0.7946   0.0089
  -9.750  -0.0433   0.08327   0.08059  -0.0921   0.7728   0.0091
  -9.500  -0.0405   0.08066   0.07791  -0.0925   0.7550   0.0091
  -9.250  -0.0284   0.07967   0.07688  -0.0927   0.7425   0.0094
  -9.000  -0.0241   0.07730   0.07446  -0.0932   0.7286   0.0094
  -8.750  -0.0187   0.07519   0.07232  -0.0936   0.7177   0.0097
  -8.500  -0.0148   0.07274   0.06985  -0.0941   0.7089   0.0099
  -8.250  -0.0144   0.07006   0.06715  -0.0946   0.7011   0.0100
  -7.750  -0.0312   0.06267   0.05977  -0.0967   0.6865   0.0113
  -7.500  -0.0229   0.06017   0.05725  -0.0986   0.6800   0.0114
  -7.250  -0.0102   0.05828   0.05534  -0.1001   0.6729   0.0117
  -7.000   0.0016   0.05577   0.05279  -0.1021   0.6668   0.0119
  -6.500   0.0187   0.04436   0.04119  -0.1109   0.6555   0.0138
  -6.250   0.0379   0.04221   0.03898  -0.1122   0.6492   0.0140
  -6.000   0.0589   0.04060   0.03730  -0.1131   0.6429   0.0142
  -5.500   0.0913   0.02870   0.02487  -0.1170   0.6318   0.0167
  -5.250   0.1147   0.02756   0.02365  -0.1169   0.6251   0.0169
  -4.750   0.1445   0.01629   0.01129  -0.1149   0.6156   0.0199
  -4.500   0.1702   0.01593   0.01085  -0.1145   0.6089   0.0201
  -4.250   0.1953   0.01542   0.01023  -0.1140   0.6022   0.0203
  -4.000   0.2208   0.01480   0.00949  -0.1135   0.5958   0.0206
  -3.750   0.2460   0.01420   0.00874  -0.1130   0.5882   0.0209
  -3.500   0.2712   0.01347   0.00784  -0.1124   0.5808   0.0214
  -3.250   0.2964   0.01280   0.00697  -0.1118   0.5716   0.0220
  -3.000   0.3220   0.01212   0.00610  -0.1112   0.5625   0.0225
  -2.750   0.3474   0.01165   0.00545  -0.1105   0.5495   0.0228
  -2.500   0.3731   0.01134   0.00498  -0.1099   0.5354   0.0230
  -2.250   0.3987   0.01113   0.00462  -0.1093   0.5181   0.0232
  -2.000   0.4237   0.01064   0.00402  -0.1087   0.5049   0.0236
  -1.750   0.4495   0.01046   0.00379  -0.1082   0.4918   0.0239
  -1.500   0.4753   0.01038   0.00363  -0.1076   0.4776   0.0242
  -1.250   0.5007   0.01029   0.00345  -0.1070   0.4630   0.0245
  -1.000   0.5263   0.01017   0.00326  -0.1065   0.4517   0.0248
  -0.750   0.5521   0.01007   0.00309  -0.1059   0.4424   0.0252
  -0.500   0.5781   0.00996   0.00294  -0.1054   0.4348   0.0255
  -0.250   0.6039   0.00988   0.00281  -0.1049   0.4271   0.0258
   0.000   0.6298   0.00981   0.00270  -0.1044   0.4203   0.0261
   0.250   0.6558   0.00974   0.00261  -0.1039   0.4138   0.0265
   0.500   0.6816   0.00971   0.00254  -0.1034   0.4085   0.0267
   0.750   0.7079   0.00966   0.00248  -0.1030   0.4045   0.0270
   1.000   0.7342   0.00964   0.00244  -0.1026   0.3995   0.0273
   1.250   0.7597   0.00958   0.00236  -0.1020   0.3940   0.0280
   1.500   0.7856   0.00957   0.00233  -0.1015   0.3896   0.0286
   1.750   0.8119   0.00955   0.00232  -0.1012   0.3857   0.0292
   2.000   0.8380   0.00956   0.00233  -0.1007   0.3810   0.0298
   2.250   0.8637   0.00961   0.00236  -0.1002   0.3762   0.0304
   2.500   0.8897   0.00964   0.00239  -0.0998   0.3720   0.0311
   2.750   0.9158   0.00968   0.00243  -0.0994   0.3671   0.0318
   3.000   0.9412   0.00976   0.00248  -0.0989   0.3609   0.0325
   3.250   0.9668   0.00982   0.00253  -0.0985   0.3555   0.0347
   3.500   0.9920   0.00991   0.00261  -0.0979   0.3471   0.0373
   3.750   1.0170   0.01000   0.00270  -0.0974   0.3401   0.0453
   4.000   1.0818   0.00870   0.00323  -0.1065   0.3272   1.0000
   4.250   1.1053   0.00888   0.00335  -0.1056   0.3157   1.0000
   4.500   1.1278   0.00911   0.00349  -0.1046   0.3016   1.0000
   4.750   1.1492   0.00940   0.00368  -0.1035   0.2852   1.0000
   5.000   1.1707   0.00968   0.00388  -0.1023   0.2713   1.0000
   5.250   1.1923   0.00995   0.00407  -0.1012   0.2601   1.0000
   5.500   1.2134   0.01024   0.00430  -0.0999   0.2491   1.0000
   5.750   1.2345   0.01052   0.00452  -0.0987   0.2391   1.0000
   6.000   1.2553   0.01081   0.00475  -0.0975   0.2290   1.0000
   6.250   1.2755   0.01112   0.00501  -0.0962   0.2204   1.0000
   6.500   1.2977   0.01132   0.00520  -0.0952   0.2166   1.0000
   6.750   1.3196   0.01152   0.00540  -0.0942   0.2132   1.0000
   7.000   1.3407   0.01175   0.00562  -0.0930   0.2098   1.0000
   7.250   1.3611   0.01201   0.00587  -0.0918   0.2060   1.0000
   7.500   1.3821   0.01223   0.00610  -0.0906   0.2031   1.0000
   7.750   1.4019   0.01243   0.00632  -0.0892   0.2004   1.0000
   8.000   1.4204   0.01267   0.00656  -0.0876   0.1971   1.0000
   8.250   1.4383   0.01293   0.00683  -0.0859   0.1939   1.0000
   8.500   1.4558   0.01322   0.00712  -0.0842   0.1907   1.0000
   8.750   1.4745   0.01347   0.00740  -0.0827   0.1884   1.0000
   9.000   1.4936   0.01372   0.00768  -0.0813   0.1854   1.0000
   9.250   1.5109   0.01406   0.00801  -0.0797   0.1802   1.0000
   9.500   1.5269   0.01447   0.00840  -0.0780   0.1740   1.0000
   9.750   1.5436   0.01486   0.00878  -0.0764   0.1667   1.0000
  10.000   1.5582   0.01536   0.00925  -0.0745   0.1584   1.0000
  10.250   1.5710   0.01596   0.00980  -0.0725   0.1481   1.0000
  10.500   1.5836   0.01659   0.01040  -0.0705   0.1379   1.0000
  10.750   1.5960   0.01726   0.01104  -0.0686   0.1297   1.0000
  11.000   1.6059   0.01808   0.01183  -0.0664   0.1203   1.0000
  11.250   1.6150   0.01899   0.01271  -0.0643   0.1111   1.0000
  11.500   1.6243   0.01993   0.01364  -0.0624   0.1030   1.0000
  11.750   1.6317   0.02104   0.01472  -0.0603   0.0949   1.0000
  12.000   1.6389   0.02223   0.01590  -0.0585   0.0878   1.0000
  12.250   1.6469   0.02343   0.01711  -0.0568   0.0814   1.0000
  12.500   1.6517   0.02492   0.01857  -0.0551   0.0744   1.0000
  12.750   1.6557   0.02656   0.02021  -0.0535   0.0665   1.0000
  13.000   1.6557   0.02859   0.02220  -0.0518   0.0566   1.0000
  13.250   1.6436   0.03176   0.02528  -0.0497   0.0399   1.0000
  13.500   1.6238   0.03583   0.02930  -0.0476   0.0205   1.0000
  13.750   1.6188   0.03870   0.03222  -0.0465   0.0155   1.0000
  14.000   1.6192   0.04114   0.03471  -0.0457   0.0137   1.0000
  14.250   1.6210   0.04348   0.03713  -0.0451   0.0126   1.0000
  14.500   1.6215   0.04601   0.03973  -0.0446   0.0116   1.0000
  14.750   1.6216   0.04866   0.04245  -0.0442   0.0110   1.0000
  15.000   1.6205   0.05148   0.04534  -0.0438   0.0102   1.0000
  15.250   1.6202   0.05428   0.04823  -0.0436   0.0098   1.0000
  15.500   1.6182   0.05736   0.05137  -0.0435   0.0091   1.0000
  15.750   1.6157   0.06054   0.05464  -0.0435   0.0088   1.0000
  16.000   1.6104   0.06411   0.05829  -0.0436   0.0082   1.0000
  16.500   1.6018   0.07123   0.06558  -0.0441   0.0077   1.0000
  16.750   1.5970   0.07494   0.06938  -0.0445   0.0075   1.0000
  17.000   1.5906   0.07888   0.07341  -0.0451   0.0072   1.0000
  17.250   1.5838   0.08292   0.07753  -0.0456   0.0070   1.0000
  17.500   1.5756   0.08722   0.08193  -0.0464   0.0068   1.0000
  17.750   1.5673   0.09159   0.08638  -0.0472   0.0066   1.0000
  18.000   1.5567   0.09629   0.09118  -0.0482   0.0064   1.0000
  18.250   1.5478   0.10080   0.09577  -0.0492   0.0062   1.0000
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