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GOE 711 AIRFOIL (goe711-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 711 AIRFOIL (goe711-il)
Reynolds number: 500,000
Max Cl/Cd: 83.11 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe711-il-500000-n5.txt
Download as CSV file: xf-goe711-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.0618   0.09047   0.08801  -0.0974   0.9466   0.0136
  -9.250  -0.0591   0.08715   0.08469  -0.0987   0.9405   0.0140
  -9.000  -0.0577   0.08347   0.08101  -0.1002   0.9345   0.0143
  -8.750  -0.0745   0.07580   0.07334  -0.1044   0.9272   0.0155
  -8.500  -0.0683   0.07354   0.07108  -0.1054   0.9198   0.0156
  -8.250  -0.0629   0.07122   0.06876  -0.1066   0.9126   0.0158
  -8.000  -0.0600   0.06849   0.06603  -0.1086   0.9035   0.0161
  -7.750  -0.0527   0.06493   0.06244  -0.1124   0.8947   0.0164
  -7.500  -0.0449   0.06054   0.05797  -0.1169   0.8858   0.0168
  -7.000  -0.0354   0.04395   0.04093  -0.1295   0.8644   0.0191
  -6.750  -0.0154   0.04240   0.03926  -0.1301   0.8521   0.0193
  -6.500   0.0046   0.04041   0.03712  -0.1308   0.8377   0.0197
  -6.000   0.0356   0.02676   0.02233  -0.1329   0.8119   0.0229
  -5.750   0.0595   0.02558   0.02095  -0.1330   0.7972   0.0232
  -5.500   0.0844   0.02462   0.01981  -0.1331   0.7824   0.0236
  -5.250   0.1095   0.02361   0.01860  -0.1332   0.7674   0.0240
  -5.000   0.1348   0.02248   0.01723  -0.1332   0.7518   0.0246
  -4.750   0.1604   0.02093   0.01537  -0.1331   0.7370   0.0255
  -4.500   0.1861   0.01894   0.01297  -0.1330   0.7228   0.0262
  -4.250   0.2124   0.01741   0.01105  -0.1328   0.7077   0.0268
  -4.000   0.2393   0.01661   0.00993  -0.1327   0.6918   0.0274
  -3.750   0.2657   0.01570   0.00881  -0.1327   0.6764   0.0280
  -3.500   0.2926   0.01518   0.00814  -0.1327   0.6616   0.0283
  -3.250   0.3194   0.01480   0.00762  -0.1326   0.6457   0.0287
  -3.000   0.3462   0.01446   0.00714  -0.1325   0.6290   0.0290
  -2.750   0.3729   0.01416   0.00670  -0.1324   0.6124   0.0295
  -2.500   0.3996   0.01387   0.00628  -0.1323   0.5968   0.0299
  -2.250   0.4263   0.01362   0.00591  -0.1322   0.5818   0.0303
  -2.000   0.4529   0.01341   0.00558  -0.1320   0.5661   0.0308
  -1.750   0.4793   0.01327   0.00534  -0.1319   0.5499   0.0315
  -1.500   0.5056   0.01315   0.00511  -0.1317   0.5343   0.0322
  -1.250   0.5320   0.01303   0.00489  -0.1315   0.5197   0.0326
  -1.000   0.5585   0.01294   0.00470  -0.1314   0.5061   0.0330
  -0.750   0.5850   0.01287   0.00455  -0.1313   0.4925   0.0334
  -0.500   0.6112   0.01272   0.00433  -0.1312   0.4789   0.0342
  -0.250   0.6374   0.01269   0.00424  -0.1311   0.4658   0.0349
   0.000   0.6636   0.01271   0.00419  -0.1309   0.4536   0.0357
   0.250   0.6899   0.01274   0.00416  -0.1308   0.4424   0.0367
   0.500   0.7163   0.01279   0.00416  -0.1307   0.4320   0.0381
   0.750   0.7422   0.01287   0.00417  -0.1305   0.4216   0.0396
   1.000   0.7682   0.01294   0.00418  -0.1303   0.4110   0.0408
   1.250   0.7942   0.01299   0.00419  -0.1302   0.4018   0.0431
   1.500   0.8199   0.01310   0.00425  -0.1299   0.3932   0.0460
   1.750   0.8459   0.01319   0.00430  -0.1298   0.3859   0.0497
   2.000   0.8714   0.01329   0.00438  -0.1295   0.3784   0.0597
   2.250   0.8890   0.01139   0.00475  -0.1280   0.3726   1.0000
   2.500   0.9143   0.01158   0.00485  -0.1277   0.3654   1.0000
   2.750   0.9389   0.01180   0.00498  -0.1273   0.3589   1.0000
   3.000   0.9641   0.01198   0.00511  -0.1270   0.3531   1.0000
   3.250   0.9886   0.01220   0.00525  -0.1266   0.3475   1.0000
   3.500   1.0128   0.01242   0.00542  -0.1261   0.3428   1.0000
   3.750   1.0375   0.01260   0.00557  -0.1258   0.3383   1.0000
   4.000   1.0611   0.01284   0.00575  -0.1252   0.3328   1.0000
   4.250   1.0838   0.01310   0.00596  -0.1245   0.3269   1.0000
   4.500   1.1070   0.01332   0.00615  -0.1238   0.3213   1.0000
   4.750   1.1276   0.01359   0.00638  -0.1227   0.3152   1.0000
   5.000   1.1487   0.01387   0.00662  -0.1217   0.3095   1.0000
   5.250   1.1704   0.01413   0.00686  -0.1208   0.3037   1.0000
   5.500   1.1910   0.01445   0.00714  -0.1197   0.2987   1.0000
   5.750   1.2126   0.01473   0.00741  -0.1189   0.2952   1.0000
   6.000   1.2349   0.01499   0.00768  -0.1181   0.2918   1.0000
   6.250   1.2565   0.01528   0.00797  -0.1174   0.2882   1.0000
   6.500   1.2775   0.01561   0.00829  -0.1165   0.2846   1.0000
   6.750   1.2977   0.01598   0.00865  -0.1155   0.2812   1.0000
   7.000   1.3198   0.01627   0.00897  -0.1148   0.2782   1.0000
   7.250   1.3412   0.01659   0.00930  -0.1141   0.2745   1.0000
   7.500   1.3615   0.01696   0.00969  -0.1132   0.2703   1.0000
   7.750   1.3803   0.01742   0.01012  -0.1120   0.2643   1.0000
   8.000   1.4000   0.01783   0.01052  -0.1111   0.2560   1.0000
   8.250   1.4177   0.01836   0.01101  -0.1099   0.2472   1.0000
   8.500   1.4352   0.01891   0.01153  -0.1086   0.2379   1.0000
   8.750   1.4529   0.01945   0.01206  -0.1075   0.2301   1.0000
   9.000   1.4684   0.02012   0.01268  -0.1060   0.2203   1.0000
   9.250   1.4843   0.02077   0.01332  -0.1046   0.2100   1.0000
   9.500   1.4976   0.02161   0.01410  -0.1030   0.1965   1.0000
   9.750   1.5062   0.02274   0.01512  -0.1007   0.1769   1.0000
  10.000   1.4975   0.02504   0.01711  -0.0962   0.1321   1.0000
  10.250   1.4980   0.02683   0.01879  -0.0931   0.1114   1.0000
  10.500   1.4929   0.02908   0.02090  -0.0896   0.0750   1.0000
  10.750   1.4877   0.03145   0.02321  -0.0864   0.0547   1.0000
  11.000   1.4960   0.03288   0.02470  -0.0848   0.0500   1.0000
  11.250   1.5037   0.03440   0.02628  -0.0832   0.0460   1.0000
  11.500   1.5121   0.03589   0.02784  -0.0819   0.0409   1.0000
  12.000   1.5154   0.04030   0.03224  -0.0786   0.0169   1.0000
  12.250   1.5204   0.04233   0.03437  -0.0774   0.0153   1.0000
  12.500   1.5237   0.04460   0.03673  -0.0763   0.0141   1.0000
  12.750   1.5264   0.04700   0.03922  -0.0753   0.0132   1.0000
  13.000   1.5300   0.04938   0.04169  -0.0745   0.0126   1.0000
  13.250   1.5319   0.05201   0.04443  -0.0737   0.0120   1.0000
  13.500   1.5323   0.05489   0.04742  -0.0731   0.0116   1.0000
  13.750   1.5308   0.05808   0.05070  -0.0726   0.0112   1.0000
  14.000   1.5269   0.06163   0.05437  -0.0721   0.0108   1.0000
  14.250   1.5199   0.06566   0.05853  -0.0718   0.0104   1.0000
  14.500   1.5160   0.06940   0.06238  -0.0717   0.0102   1.0000
  14.750   1.5107   0.07340   0.06650  -0.0718   0.0099   1.0000
  15.000   1.5040   0.07768   0.07090  -0.0720   0.0097   1.0000
  15.250   1.4956   0.08221   0.07555  -0.0723   0.0094   1.0000
  15.500   1.4860   0.08702   0.08048  -0.0727   0.0092   1.0000
  15.750   1.4752   0.09206   0.08565  -0.0733   0.0090   1.0000
  16.000   1.4639   0.09724   0.09095  -0.0741   0.0089   1.0000
  16.250   1.4519   0.10257   0.09639  -0.0749   0.0087   1.0000
  16.500   1.4394   0.10803   0.10198  -0.0760   0.0086   1.0000
  16.750   1.4270   0.11355   0.10761  -0.0772   0.0085   1.0000
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