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GOE 123 AIRFOIL (goe123-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 123 AIRFOIL (goe123-il)
Reynolds number: 200,000
Max Cl/Cd: 92.03 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe123-il-200000.txt
Download as CSV file: xf-goe123-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 123 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3176   0.09649   0.09322  -0.0214   1.0000   0.0275
  -7.250  -0.3355   0.09623   0.09304  -0.0169   1.0000   0.0277
  -7.000  -0.3472   0.09529   0.09217  -0.0142   1.0000   0.0280
  -6.750  -0.3510   0.09362   0.09054  -0.0136   0.9994   0.0284
  -6.500  -0.3214   0.08943   0.08632  -0.0219   0.9950   0.0301
  -6.250  -0.2617   0.08680   0.08355  -0.0444   0.9869   0.0313
  -6.000  -0.2440   0.08062   0.07737  -0.0466   0.9843   0.0318
  -5.750  -0.2297   0.07612   0.07289  -0.0462   0.9814   0.0324
  -5.500  -0.2074   0.07249   0.06923  -0.0494   0.9764   0.0334
  -5.250  -0.1751   0.06867   0.06535  -0.0556   0.9727   0.0350
  -5.000  -0.1329   0.06470   0.06129  -0.0643   0.9699   0.0378
  -4.750  -0.0688   0.06181   0.05811  -0.0793   0.9620   0.0402
  -4.500  -0.0513   0.05663   0.05300  -0.0802   0.9588   0.0413
  -4.250  -0.0169   0.05302   0.04933  -0.0846   0.9565   0.0431
  -4.000   0.0172   0.05008   0.04631  -0.0890   0.9510   0.0459
  -3.750   0.0824   0.04747   0.04329  -0.0997   0.9465   0.0512
  -3.500   0.1076   0.04339   0.03928  -0.1020   0.9437   0.0527
  -3.250   0.1434   0.04067   0.03649  -0.1056   0.9413   0.0555
  -3.000   0.1920   0.04063   0.03603  -0.1097   0.9347   0.0627
  -2.750   0.2209   0.03620   0.03156  -0.1126   0.9302   0.0643
  -2.500   0.2503   0.03377   0.02916  -0.1145   0.9270   0.0676
  -2.250   0.2931   0.03468   0.02957  -0.1161   0.9204   0.0764
  -2.000   0.3176   0.03038   0.02535  -0.1178   0.9150   0.0784
  -1.750   0.3482   0.02840   0.02336  -0.1192   0.9111   0.0819
  -1.500   0.3814   0.02800   0.02255  -0.1192   0.9018   0.0915
  -1.250   0.4085   0.02538   0.01998  -0.1198   0.8958   0.0945
  -1.000   0.4380   0.02518   0.01944  -0.1191   0.8852   0.1058
  -0.750   0.4622   0.02293   0.01729  -0.1191   0.8786   0.1103
  -0.500   0.4907   0.02211   0.01626  -0.1189   0.8703   0.1214
  -0.250   0.5176   0.02085   0.01495  -0.1186   0.8638   0.1274
   0.000   0.5450   0.01988   0.01384  -0.1183   0.8551   0.1374
   0.250   0.5821   0.01800   0.01121  -0.1169   0.8493   0.0767
   0.500   0.6092   0.01619   0.00930  -0.1166   0.8403   0.0697
   0.750   0.6375   0.01495   0.00777  -0.1158   0.8328   0.0653
   1.000   0.6639   0.01444   0.00724  -0.1151   0.8235   0.0685
   1.250   0.6904   0.01382   0.00656  -0.1143   0.8136   0.0688
   1.500   0.7173   0.01323   0.00591  -0.1135   0.8049   0.0691
   1.750   0.7436   0.01279   0.00548  -0.1128   0.7936   0.0709
   2.000   0.7699   0.01244   0.00515  -0.1120   0.7815   0.0741
   2.250   0.7964   0.01210   0.00483  -0.1114   0.7689   0.0811
   2.500   0.8228   0.01185   0.00465  -0.1106   0.7541   0.1060
   2.750   0.8484   0.01122   0.00452  -0.1100   0.7376   0.3655
   3.000   0.8705   0.01013   0.00437  -0.1081   0.7201   1.0000
   3.250   0.8964   0.01018   0.00429  -0.1073   0.6998   1.0000
   3.500   0.9220   0.01027   0.00426  -0.1066   0.6767   1.0000
   3.750   0.9473   0.01040   0.00427  -0.1058   0.6507   1.0000
   4.000   0.9722   0.01058   0.00433  -0.1050   0.6213   1.0000
   4.250   0.9967   0.01083   0.00441  -0.1041   0.5896   1.0000
   4.500   1.0209   0.01116   0.00458  -0.1033   0.5587   1.0000
   4.750   1.0448   0.01156   0.00481  -0.1025   0.5288   1.0000
   5.000   1.0685   0.01200   0.00512  -0.1017   0.4999   1.0000
   5.250   1.0922   0.01244   0.00546  -0.1009   0.4729   1.0000
   5.500   1.1155   0.01290   0.00581  -0.1002   0.4458   1.0000
   5.750   1.1383   0.01338   0.00616  -0.0993   0.4180   1.0000
   6.000   1.1611   0.01386   0.00656  -0.0985   0.3929   1.0000
   6.250   1.1841   0.01433   0.00698  -0.0978   0.3707   1.0000
   6.500   1.2063   0.01485   0.00741  -0.0969   0.3478   1.0000
   6.750   1.2287   0.01533   0.00787  -0.0962   0.3247   1.0000
   7.000   1.2503   0.01587   0.00836  -0.0953   0.3017   1.0000
   7.250   1.2719   0.01638   0.00885  -0.0944   0.2749   1.0000
   7.500   1.2924   0.01697   0.00936  -0.0934   0.2382   1.0000
   7.750   1.3075   0.01814   0.01013  -0.0917   0.1654   1.0000
   8.000   1.3109   0.02078   0.01197  -0.0886   0.0668   1.0000
   8.250   1.3259   0.02207   0.01321  -0.0867   0.0496   1.0000
   8.500   1.3394   0.02340   0.01457  -0.0846   0.0439   1.0000
   8.750   1.3525   0.02464   0.01592  -0.0825   0.0404   1.0000
   9.000   1.3601   0.02625   0.01758  -0.0798   0.0373   1.0000
   9.250   1.3644   0.02801   0.01941  -0.0765   0.0354   1.0000
   9.500   1.3732   0.02944   0.02096  -0.0739   0.0342   1.0000
   9.750   1.3818   0.03103   0.02268  -0.0713   0.0330   1.0000
  10.000   1.3916   0.03273   0.02447  -0.0690   0.0319   1.0000
  10.250   1.4025   0.03448   0.02631  -0.0669   0.0307   1.0000
  10.500   1.4139   0.03641   0.02826  -0.0651   0.0292   1.0000
  10.750   1.4429   0.04067   0.03258  -0.0655   0.0274   1.0000
  11.000   1.4563   0.04283   0.03497  -0.0638   0.0271   1.0000
  11.250   1.4674   0.04514   0.03755  -0.0618   0.0268   1.0000
  11.500   1.4759   0.04782   0.04052  -0.0597   0.0266   1.0000
  11.750   1.4805   0.05086   0.04386  -0.0574   0.0265   1.0000
  12.000   1.4800   0.05402   0.04731  -0.0548   0.0265   1.0000
  12.250   1.4746   0.05708   0.05065  -0.0520   0.0264   1.0000
  12.500   1.4657   0.06021   0.05406  -0.0494   0.0263   1.0000
  12.750   1.4544   0.06360   0.05772  -0.0472   0.0261   1.0000
  13.000   1.4410   0.06730   0.06168  -0.0455   0.0260   1.0000
  13.250   1.4257   0.07145   0.06609  -0.0443   0.0259   1.0000
  13.500   1.4087   0.07613   0.07101  -0.0438   0.0260   1.0000
  13.750   1.3901   0.08125   0.07637  -0.0440   0.0261   1.0000
  14.000   1.3702   0.08694   0.08227  -0.0449   0.0263   1.0000
  14.250   1.3495   0.09316   0.08869  -0.0466   0.0265   1.0000
  14.500   1.3278   0.10001   0.09573  -0.0491   0.0267   1.0000
  14.750   1.1598   0.09519   0.09102  -0.0303   0.0280   1.0000
  15.000   1.1308   0.10029   0.09632  -0.0327   0.0283   1.0000
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