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GOE 711 AIRFOIL (goe711-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 711 AIRFOIL (goe711-il)
Reynolds number: 100,000
Max Cl/Cd: 48.31 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe711-il-100000.txt
Download as CSV file: xf-goe711-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 711 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3438   0.13443   0.13030  -0.0287   1.0000   0.0649
  -8.750  -0.3634   0.13378   0.12974  -0.0278   1.0000   0.0650
  -8.500  -0.3846   0.13308   0.12913  -0.0265   1.0000   0.0651
  -8.250  -0.3440   0.12445   0.12048  -0.0228   1.0000   0.0670
  -8.000  -0.3460   0.12227   0.11835  -0.0207   1.0000   0.0681
  -7.750  -0.3481   0.12006   0.11618  -0.0200   0.9992   0.0694
  -7.500  -0.3316   0.11606   0.11216  -0.0249   0.9938   0.0721
  -7.250  -0.3238   0.11252   0.10862  -0.0301   0.9861   0.0749
  -7.000  -0.3251   0.10919   0.10528  -0.0433   0.9738   0.0776
  -6.750  -0.3125   0.10317   0.09923  -0.0514   0.9643   0.0790
  -6.500  -0.2887   0.09939   0.09549  -0.0468   0.9606   0.0819
  -6.250  -0.2681   0.09545   0.09152  -0.0508   0.9528   0.0856
  -6.000  -0.2428   0.09083   0.08655  -0.0694   0.9388   0.0927
  -5.750  -0.2277   0.08497   0.08077  -0.0699   0.9313   0.0944
  -5.500  -0.1991   0.08108   0.07693  -0.0704   0.9274   0.0980
  -5.250  -0.1806   0.07778   0.07354  -0.0736   0.9161   0.1047
  -5.000  -0.1529   0.07281   0.06839  -0.0803   0.9080   0.1121
  -4.750  -0.1248   0.06959   0.06511  -0.0830   0.8999   0.1207
  -4.250  -0.0591   0.06156   0.05663  -0.0933   0.8842   0.1443
  -3.750   0.0050   0.05518   0.05003  -0.0989   0.8691   0.1787
  -3.500   0.0285   0.05266   0.04750  -0.0994   0.8589   0.1977
  -3.250   0.0686   0.04952   0.04429  -0.1029   0.8542   0.2313
  -3.000   0.0916   0.04739   0.04216  -0.1027   0.8439   0.2653
  -2.750   0.1270   0.04465   0.03950  -0.1039   0.8395   0.3182
  -2.000   0.3150   0.03345   0.02558  -0.1219   0.8238   0.1383
  -1.750   0.3524   0.03145   0.02312  -0.1222   0.8142   0.1211
  -1.500   0.4007   0.02912   0.02046  -0.1249   0.8091   0.1161
  -1.250   0.4389   0.02797   0.01885  -0.1254   0.7994   0.1097
  -1.000   0.4852   0.02618   0.01688  -0.1277   0.7928   0.1081
  -0.750   0.5189   0.02497   0.01554  -0.1280   0.7807   0.1080
  -0.500   0.5562   0.02355   0.01410  -0.1291   0.7698   0.1115
  -0.250   0.5970   0.02223   0.01276  -0.1307   0.7597   0.1153
   0.000   0.6277   0.02150   0.01199  -0.1306   0.7448   0.1189
   0.250   0.6585   0.02095   0.01131  -0.1305   0.7294   0.1242
   0.500   0.6887   0.02043   0.01070  -0.1305   0.7135   0.1376
   0.750   0.7190   0.01998   0.01022  -0.1306   0.6972   0.1668
   1.000   0.7487   0.01783   0.00995  -0.1297   0.6811   1.0000
   1.250   0.7765   0.01798   0.00971  -0.1293   0.6642   1.0000
   1.500   0.8023   0.01821   0.00966  -0.1287   0.6468   1.0000
   1.750   0.8281   0.01847   0.00967  -0.1283   0.6300   1.0000
   2.000   0.8541   0.01875   0.00971  -0.1278   0.6139   1.0000
   2.250   0.8803   0.01906   0.00980  -0.1275   0.5988   1.0000
   2.500   0.9072   0.01939   0.00989  -0.1274   0.5848   1.0000
   2.750   0.9316   0.01978   0.01013  -0.1269   0.5704   1.0000
   3.000   0.9559   0.02019   0.01041  -0.1263   0.5570   1.0000
   3.250   0.9806   0.02062   0.01071  -0.1259   0.5446   1.0000
   3.500   1.0074   0.02106   0.01098  -0.1259   0.5339   1.0000
   3.750   1.0331   0.02150   0.01130  -0.1257   0.5233   1.0000
   4.000   1.0567   0.02202   0.01176  -0.1252   0.5129   1.0000
   4.250   1.0855   0.02247   0.01202  -0.1256   0.5044   1.0000
   4.500   1.1071   0.02300   0.01258  -0.1248   0.4946   1.0000
   4.750   1.1347   0.02352   0.01297  -0.1250   0.4870   1.0000
   5.000   1.1572   0.02410   0.01358  -0.1244   0.4788   1.0000
   5.250   1.1866   0.02464   0.01396  -0.1251   0.4724   1.0000
   5.500   1.2064   0.02528   0.01471  -0.1240   0.4645   1.0000
   5.750   1.2352   0.02579   0.01511  -0.1245   0.4583   1.0000
   6.000   1.2556   0.02650   0.01592  -0.1236   0.4515   1.0000
   6.250   1.2800   0.02711   0.01652  -0.1234   0.4454   1.0000
   6.500   1.3098   0.02776   0.01708  -0.1242   0.4405   1.0000
   6.750   1.3263   0.02859   0.01810  -0.1227   0.4345   1.0000
   7.000   1.3510   0.02923   0.01876  -0.1226   0.4292   1.0000
   7.250   1.3804   0.02992   0.01936  -0.1233   0.4246   1.0000
   7.500   1.3941   0.03085   0.02054  -0.1214   0.4189   1.0000
   7.750   1.4171   0.03159   0.02133  -0.1211   0.4140   1.0000
   8.000   1.4478   0.03230   0.02197  -0.1221   0.4102   1.0000
   8.250   1.4605   0.03344   0.02336  -0.1201   0.4056   1.0000
   8.500   1.4766   0.03437   0.02444  -0.1186   0.4004   1.0000
   8.750   1.5049   0.03490   0.02493  -0.1192   0.3956   1.0000
   9.000   1.5209   0.03593   0.02610  -0.1178   0.3908   1.0000
   9.250   1.5313   0.03703   0.02742  -0.1154   0.3856   1.0000
   9.500   1.5568   0.03758   0.02798  -0.1155   0.3808   1.0000
   9.750   1.5790   0.03844   0.02889  -0.1152   0.3763   1.0000
  10.000   1.5796   0.03983   0.03056  -0.1113   0.3713   1.0000
  10.250   1.6057   0.03996   0.03069  -0.1114   0.3650   1.0000
  10.500   1.6173   0.04065   0.03147  -0.1092   0.3586   1.0000
  10.750   1.6274   0.04095   0.03185  -0.1066   0.3512   1.0000
  11.000   1.6470   0.04093   0.03179  -0.1055   0.3436   1.0000
  11.250   1.6447   0.04177   0.03283  -0.1010   0.3374   1.0000
  11.500   1.6804   0.04127   0.03217  -0.1025   0.3301   1.0000
  11.750   1.6602   0.04287   0.03408  -0.0955   0.3261   1.0000
  12.000   1.6611   0.04376   0.03512  -0.0918   0.3210   1.0000
  12.250   1.6867   0.04342   0.03469  -0.0917   0.3140   1.0000
  12.500   1.6655   0.04538   0.03696  -0.0854   0.3097   1.0000
  12.750   1.6774   0.04542   0.03701  -0.0834   0.3028   1.0000
  13.000   1.6763   0.04654   0.03825  -0.0802   0.2974   1.0000
  13.250   1.6596   0.04873   0.04070  -0.0757   0.2927   1.0000
  13.500   1.6733   0.04831   0.04018  -0.0740   0.2839   1.0000
  13.750   1.6483   0.05146   0.04365  -0.0695   0.2793   1.0000
  14.000   1.6567   0.05148   0.04358  -0.0677   0.2701   1.0000
  14.250   1.6294   0.05551   0.04797  -0.0642   0.2658   1.0000
  14.500   1.6179   0.05798   0.05057  -0.0621   0.2580   1.0000
  14.750   1.5994   0.06174   0.05452  -0.0602   0.2516   1.0000
  15.000   1.5810   0.06590   0.05886  -0.0591   0.2441   1.0000
  15.250   1.5601   0.07087   0.06402  -0.0585   0.2372   1.0000
  15.500   1.5353   0.07684   0.07018  -0.0585   0.2307   1.0000
  15.750   1.5115   0.08305   0.07655  -0.0590   0.2239   1.0000
  16.000   1.4776   0.09128   0.08502  -0.0602   0.2218   1.0000
  16.250   1.4364   0.10105   0.09499  -0.0620   0.2226   1.0000
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