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GOE 392 AIRFOIL (goe392-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 392 AIRFOIL (goe392-il)
Reynolds number: 200,000
Max Cl/Cd: 77.55 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe392-il-200000-n5.txt
Download as CSV file: xf-goe392-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 392 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2947   0.11297   0.10966  -0.0390   1.0000   0.0135
  -9.250  -0.2942   0.11043   0.10717  -0.0384   1.0000   0.0144
  -9.000  -0.2949   0.10797   0.10476  -0.0380   1.0000   0.0146
  -8.750  -0.2941   0.10539   0.10222  -0.0381   0.9996   0.0149
  -8.500  -0.2777   0.10097   0.09780  -0.0429   0.9962   0.0155
  -8.250  -0.2622   0.09669   0.09353  -0.0475   0.9918   0.0163
  -8.000  -0.2456   0.09249   0.08932  -0.0525   0.9874   0.0169
  -7.750  -0.2315   0.08839   0.08523  -0.0570   0.9807   0.0177
  -7.500  -0.2185   0.08441   0.08127  -0.0613   0.9727   0.0185
  -7.250  -0.2066   0.08042   0.07727  -0.0663   0.9621   0.0198
  -7.000  -0.1930   0.07635   0.07322  -0.0724   0.9489   0.0206
  -6.750  -0.1722   0.07135   0.06821  -0.0810   0.9364   0.0210
  -6.500  -0.1472   0.06577   0.06257  -0.0901   0.9259   0.0212
  -6.250  -0.1187   0.05983   0.05653  -0.0990   0.9168   0.0213
  -6.000  -0.0922   0.05428   0.05080  -0.1060   0.9059   0.0213
  -5.750  -0.0656   0.04915   0.04543  -0.1118   0.8960   0.0214
  -5.500  -0.0370   0.04436   0.04036  -0.1169   0.8870   0.0214
  -5.250  -0.0152   0.03699   0.03281  -0.1198   0.8770   0.0109
  -5.000   0.0111   0.03239   0.02783  -0.1230   0.8665   0.0103
  -4.750   0.0395   0.02846   0.02343  -0.1250   0.8567   0.0099
  -4.250   0.0974   0.02310   0.01708  -0.1265   0.8374   0.0109
  -4.000   0.1257   0.02124   0.01470  -0.1266   0.8278   0.0117
  -3.750   0.1534   0.01890   0.01187  -0.1267   0.8192   0.0119
  -3.500   0.1794   0.01686   0.00944  -0.1262   0.8099   0.0123
  -3.250   0.2059   0.01545   0.00779  -0.1259   0.8010   0.0132
  -3.000   0.2331   0.01470   0.00686  -0.1257   0.7924   0.0161
  -2.750   0.2585   0.01392   0.00592  -0.1251   0.7831   0.0188
  -2.500   0.2847   0.01329   0.00514  -0.1246   0.7746   0.0217
  -2.250   0.3099   0.01267   0.00439  -0.1243   0.7656   0.0293
  -2.000   0.3355   0.01225   0.00380  -0.1239   0.7566   0.0401
  -1.750   0.3617   0.01184   0.00331  -0.1236   0.7482   0.0649
  -1.500   0.3837   0.01092   0.00325  -0.1231   0.7388   0.3449
  -1.250   0.4094   0.01084   0.00314  -0.1227   0.7296   0.3972
  -1.000   0.4344   0.01067   0.00304  -0.1222   0.7201   0.4515
  -0.750   0.4586   0.01051   0.00293  -0.1215   0.7090   0.4925
  -0.500   0.4813   0.01025   0.00290  -0.1205   0.6976   0.5744
  -0.250   0.5022   0.00971   0.00293  -0.1187   0.6870   0.7937
   0.250   0.5828   0.00963   0.00274  -0.1242   0.6656   1.0000
   0.500   0.6079   0.00974   0.00273  -0.1238   0.6554   1.0000
   0.750   0.6332   0.00985   0.00274  -0.1233   0.6458   1.0000
   1.000   0.6584   0.00998   0.00276  -0.1229   0.6361   1.0000
   1.250   0.6835   0.01010   0.00281  -0.1225   0.6260   1.0000
   1.500   0.7086   0.01023   0.00289  -0.1220   0.6166   1.0000
   2.000   0.7587   0.01052   0.00307  -0.1211   0.5974   1.0000
   2.250   0.7836   0.01067   0.00320  -0.1207   0.5881   1.0000
   2.500   0.8085   0.01084   0.00336  -0.1202   0.5792   1.0000
   2.750   0.8335   0.01100   0.00354  -0.1198   0.5703   1.0000
   3.000   0.8584   0.01118   0.00373  -0.1193   0.5620   1.0000
   3.250   0.8825   0.01138   0.00392  -0.1187   0.5506   1.0000
   3.500   0.8983   0.01172   0.00407  -0.1163   0.5040   1.0000
   3.750   0.9153   0.01212   0.00429  -0.1142   0.4593   1.0000
   4.000   0.9187   0.01326   0.00470  -0.1098   0.3400   1.0000
   4.250   0.9048   0.01611   0.00615  -0.1031   0.0842   1.0000
   4.500   0.9186   0.01710   0.00700  -0.1007   0.0196   1.0000
   4.750   0.9364   0.01776   0.00789  -0.0988   0.0161   1.0000
   5.000   0.9546   0.01834   0.00863  -0.0972   0.0141   1.0000
   5.250   0.9707   0.01903   0.00950  -0.0951   0.0123   1.0000
   5.500   0.9830   0.01987   0.01050  -0.0924   0.0115   1.0000
   5.750   0.9907   0.02083   0.01161  -0.0889   0.0109   1.0000
   6.000   0.9956   0.02196   0.01284  -0.0852   0.0106   1.0000
   6.250   0.9978   0.02330   0.01424  -0.0813   0.0096   1.0000
   6.500   0.9936   0.02519   0.01616  -0.0768   0.0087   1.0000
   6.750   0.9979   0.02684   0.01790  -0.0735   0.0081   1.0000
   7.000   1.0087   0.02823   0.01935  -0.0712   0.0080   1.0000
   7.250   1.0240   0.02982   0.02097  -0.0694   0.0079   1.0000
   7.500   1.0483   0.03156   0.02275  -0.0687   0.0079   1.0000
   7.750   1.1112   0.03513   0.02632  -0.0736   0.0082   1.0000
   8.000   1.1506   0.03709   0.02838  -0.0754   0.0089   1.0000
   8.250   1.1673   0.03795   0.02954  -0.0727   0.0099   1.0000
   8.750   1.2129   0.04382   0.03600  -0.0716   0.0072   1.0000
  11.250   1.2201   0.07190   0.06665  -0.0428   0.0105   1.0000
  11.500   1.2057   0.07537   0.07032  -0.0409   0.0105   1.0000
  11.750   1.1911   0.07900   0.07414  -0.0396   0.0104   1.0000
  12.000   1.1749   0.08300   0.07834  -0.0389   0.0104   1.0000
  12.250   1.1577   0.08743   0.08293  -0.0388   0.0103   1.0000
  12.500   1.1402   0.09210   0.08778  -0.0393   0.0103   1.0000
  12.750   1.1225   0.09713   0.09298  -0.0405   0.0104   1.0000
  13.000   1.1045   0.10255   0.09857  -0.0423   0.0104   1.0000
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