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GOE 414 AIRFOIL (goe414-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 414 AIRFOIL (goe414-il)
Reynolds number: 100,000
Max Cl/Cd: 52.08 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe414-il-100000.txt
Download as CSV file: xf-goe414-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 414 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  -0.3591   0.11806   0.11390  -0.0309   1.0000   0.1055
  -8.750  -0.3857   0.11766   0.11363  -0.0302   1.0000   0.1062
  -8.500  -0.4128   0.11717   0.11325  -0.0289   1.0000   0.1065
  -8.250  -0.4332   0.11512   0.11128  -0.0344   0.9950   0.1068
  -8.000  -0.3743   0.10796   0.10402  -0.0278   0.9966   0.1117
  -7.750  -0.3599   0.10406   0.10010  -0.0323   0.9906   0.1161
  -7.500  -0.3748   0.10068   0.09677  -0.0448   0.9775   0.1209
  -7.250  -0.3574   0.09449   0.09058  -0.0502   0.9713   0.1230
  -7.000  -0.3313   0.09148   0.08752  -0.0478   0.9662   0.1271
  -6.750  -0.3323   0.08513   0.08095  -0.0693   0.9479   0.1367
  -6.500  -0.3010   0.08186   0.07782  -0.0614   0.9458   0.1404
  -6.000  -0.2751   0.05553   0.05048  -0.0887   0.9271   0.0939
  -5.750  -0.2560   0.05071   0.04539  -0.0902   0.9171   0.0896
  -5.500  -0.2202   0.04377   0.03765  -0.0958   0.9121   0.0897
  -5.250  -0.1976   0.03964   0.03289  -0.0966   0.9022   0.0900
  -5.000  -0.1560   0.03578   0.02825  -0.1002   0.8977   0.0942
  -4.750  -0.1313   0.03458   0.02699  -0.1002   0.8884   0.0987
  -4.500  -0.0902   0.03235   0.02414  -0.1026   0.8838   0.1048
  -4.250  -0.0617   0.03114   0.02279  -0.1031   0.8762   0.1128
  -4.000  -0.0245   0.02961   0.02095  -0.1047   0.8704   0.1244
  -3.750   0.0213   0.02828   0.01952  -0.1078   0.8672   0.1479
  -3.500   0.0426   0.02779   0.01887  -0.1067   0.8569   0.1675
  -3.250   0.0873   0.02680   0.01797  -0.1097   0.8533   0.1890
  -3.000   0.1099   0.02667   0.01783  -0.1090   0.8435   0.2064
  -2.750   0.1524   0.02607   0.01713  -0.1114   0.8393   0.2295
  -2.500   0.1802   0.02569   0.01675  -0.1113   0.8310   0.2451
  -2.250   0.2174   0.02486   0.01596  -0.1125   0.8253   0.2627
  -2.000   0.2605   0.02383   0.01500  -0.1146   0.8221   0.2929
  -1.750   0.2817   0.02351   0.01486  -0.1133   0.8112   0.3290
  -1.500   0.3213   0.02229   0.01396  -0.1148   0.8075   0.4103
  -1.250   0.3424   0.02177   0.01381  -0.1134   0.7968   0.4930
  -1.000   0.4186   0.01973   0.01303  -0.1208   0.7945   1.0000
  -0.750   0.4447   0.01972   0.01276  -0.1203   0.7849   1.0000
  -0.500   0.4817   0.01932   0.01210  -0.1214   0.7784   1.0000
  -0.250   0.5051   0.01936   0.01196  -0.1203   0.7673   1.0000
   0.000   0.5450   0.01885   0.01123  -0.1218   0.7617   1.0000
   0.250   0.5671   0.01893   0.01117  -0.1206   0.7495   1.0000
   0.500   0.5928   0.01892   0.01103  -0.1199   0.7385   1.0000
   0.750   0.6301   0.01855   0.01046  -0.1211   0.7316   1.0000
   1.000   0.6528   0.01870   0.01051  -0.1200   0.7193   1.0000
   1.250   0.6778   0.01882   0.01052  -0.1193   0.7081   1.0000
   1.500   0.7091   0.01875   0.01031  -0.1196   0.6994   1.0000
   1.750   0.7362   0.01885   0.01030  -0.1193   0.6889   1.0000
   2.000   0.7600   0.01911   0.01048  -0.1186   0.6779   1.0000
   2.250   0.7905   0.01918   0.01042  -0.1189   0.6698   1.0000
   2.500   0.8146   0.01952   0.01071  -0.1183   0.6600   1.0000
   2.750   0.8392   0.01990   0.01104  -0.1178   0.6514   1.0000
   3.000   0.8669   0.02018   0.01124  -0.1178   0.6439   1.0000
   3.250   0.8895   0.02069   0.01173  -0.1171   0.6359   1.0000
   3.500   0.9167   0.02100   0.01200  -0.1170   0.6289   1.0000
   3.750   0.9399   0.02154   0.01254  -0.1164   0.6220   1.0000
   4.000   0.9633   0.02206   0.01307  -0.1159   0.6153   1.0000
   4.250   0.9940   0.02231   0.01326  -0.1164   0.6100   1.0000
   4.500   1.0101   0.02304   0.01408  -0.1148   0.6015   1.0000
   4.750   1.0428   0.02313   0.01409  -0.1154   0.5958   1.0000
   5.000   1.0573   0.02387   0.01497  -0.1135   0.5871   1.0000
   5.250   1.0893   0.02393   0.01495  -0.1141   0.5809   1.0000
   5.500   1.1042   0.02473   0.01589  -0.1123   0.5733   1.0000
   5.750   1.1301   0.02515   0.01634  -0.1121   0.5679   1.0000
   6.000   1.1566   0.02561   0.01685  -0.1120   0.5631   1.0000
   6.250   1.1702   0.02654   0.01794  -0.1102   0.5562   1.0000
   6.500   1.1998   0.02679   0.01822  -0.1105   0.5513   1.0000
   6.750   1.2160   0.02766   0.01926  -0.1090   0.5452   1.0000
   7.000   1.2357   0.02834   0.02005  -0.1079   0.5391   1.0000
   7.250   1.2699   0.02846   0.02019  -0.1089   0.5348   1.0000
   7.500   1.2747   0.02979   0.02176  -0.1058   0.5273   1.0000
   7.750   1.3146   0.02899   0.02092  -0.1070   0.5186   1.0000
   8.000   1.3413   0.02833   0.02024  -0.1061   0.5051   1.0000
   8.250   1.3576   0.02832   0.02033  -0.1039   0.4925   1.0000
   8.500   1.3772   0.02814   0.02021  -0.1021   0.4795   1.0000
   8.750   1.3970   0.02800   0.02013  -0.1003   0.4664   1.0000
   9.000   1.4151   0.02763   0.01973  -0.0981   0.4495   1.0000
   9.250   1.4294   0.02768   0.01983  -0.0956   0.4350   1.0000
   9.500   1.4395   0.02764   0.01979  -0.0923   0.4173   1.0000
   9.750   1.4437   0.02775   0.01989  -0.0881   0.3988   1.0000
  10.000   1.4352   0.02829   0.02055  -0.0822   0.3820   1.0000
  10.250   1.4257   0.02916   0.02158  -0.0767   0.3636   1.0000
  10.500   1.4161   0.03031   0.02284  -0.0719   0.3406   1.0000
  10.750   1.4038   0.03201   0.02457  -0.0674   0.3055   1.0000
  11.000   1.3865   0.03443   0.02669  -0.0630   0.2591   1.0000
  11.250   1.3661   0.03774   0.02969  -0.0592   0.2214   1.0000
  11.500   1.3454   0.04160   0.03335  -0.0562   0.1761   1.0000
  11.750   1.3172   0.04654   0.03796  -0.0537   0.1241   1.0000
  12.000   1.2922   0.05165   0.04288  -0.0519   0.0998   1.0000
  12.250   1.2721   0.05664   0.04780  -0.0508   0.0807   1.0000
  12.500   1.2560   0.06144   0.05260  -0.0501   0.0698   1.0000
  12.750   1.2432   0.06607   0.05728  -0.0498   0.0637   1.0000
  13.000   1.2305   0.07084   0.06210  -0.0497   0.0599   1.0000
  13.250   1.2190   0.07560   0.06693  -0.0497   0.0571   1.0000
  13.500   1.2104   0.08008   0.07155  -0.0499   0.0545   1.0000
  13.750   1.2020   0.08458   0.07617  -0.0502   0.0524   1.0000
  14.000   1.1937   0.08907   0.08074  -0.0505   0.0507   1.0000
  14.250   1.1868   0.09329   0.08503  -0.0507   0.0493   1.0000
  14.500   1.1856   0.09642   0.08820  -0.0504   0.0481   1.0000
  14.750   1.1922   0.09832   0.09021  -0.0495   0.0468   1.0000
  15.000   1.2047   0.09901   0.09094  -0.0479   0.0454   1.0000
  15.250   1.2223   0.09876   0.09068  -0.0457   0.0438   1.0000
  15.500   1.2431   0.09805   0.08988  -0.0431   0.0418   1.0000
  15.750   1.2964   0.09273   0.08427  -0.0366   0.0394   1.0000
  16.000   1.3221   0.09298   0.08469  -0.0344   0.0391   1.0000
  16.250   1.3465   0.09393   0.08582  -0.0325   0.0390   1.0000
  16.500   1.3652   0.09595   0.08806  -0.0312   0.0391   1.0000
  16.750   1.3766   0.09896   0.09130  -0.0304   0.0392   1.0000
  17.000   1.3785   0.10275   0.09534  -0.0303   0.0393   1.0000
  17.250   1.3747   0.10702   0.09986  -0.0306   0.0394   1.0000
  17.500   1.3678   0.11166   0.10474  -0.0314   0.0394   1.0000
  17.750   1.3590   0.11660   0.10992  -0.0325   0.0395   1.0000
  18.000   1.3469   0.12160   0.11518  -0.0342   0.0397   1.0000
  18.250   1.3307   0.12689   0.12072  -0.0368   0.0399   1.0000
  18.500   1.3107   0.13301   0.12712  -0.0403   0.0402   1.0000
  18.750   1.2815   0.14144   0.13590  -0.0457   0.0411   1.0000
  19.000   1.2153   0.15895   0.15396  -0.0583   0.0435   1.0000
  19.250   1.1752   0.17345   0.16869  -0.0683   0.0453   1.0000
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