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GOE 509 AIRFOIL (goe509-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 509 AIRFOIL (goe509-il)
Reynolds number: 1,000,000
Max Cl/Cd: 97.22 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe509-il-1000000-n5.txt
Download as CSV file: xf-goe509-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 509 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.6799   0.02884   0.02598  -0.1128   0.9681   0.0067
 -12.000  -0.6743   0.02447   0.02124  -0.1130   0.9642   0.0069
 -11.750  -0.6620   0.02231   0.01886  -0.1119   0.9608   0.0071
 -11.500  -0.6505   0.02093   0.01731  -0.1098   0.9568   0.0072
 -11.250  -0.6334   0.01978   0.01601  -0.1085   0.9534   0.0073
 -11.000  -0.6123   0.01878   0.01490  -0.1078   0.9502   0.0076
 -10.750  -0.5942   0.01798   0.01398  -0.1062   0.9463   0.0078
 -10.500  -0.5768   0.01721   0.01310  -0.1045   0.9416   0.0080
 -10.250  -0.5557   0.01652   0.01230  -0.1034   0.9375   0.0082
 -10.000  -0.5336   0.01587   0.01153  -0.1024   0.9335   0.0085
  -9.750  -0.5152   0.01528   0.01085  -0.1006   0.9264   0.0087
  -9.500  -0.4933   0.01473   0.01020  -0.0994   0.9178   0.0089
  -9.250  -0.4723   0.01420   0.00956  -0.0980   0.9019   0.0091
  -9.000  -0.4483   0.01353   0.00863  -0.0972   0.8536   0.0096
  -8.750  -0.4283   0.01321   0.00808  -0.0955   0.8202   0.0099
  -8.250  -0.3837   0.01255   0.00717  -0.0931   0.7934   0.0107
  -8.000  -0.3607   0.01223   0.00674  -0.0921   0.7837   0.0112
  -7.750  -0.3372   0.01194   0.00634  -0.0911   0.7736   0.0116
  -7.500  -0.3136   0.01164   0.00594  -0.0902   0.7638   0.0121
  -7.000  -0.2655   0.01109   0.00526  -0.0884   0.7450   0.0135
  -6.750  -0.2411   0.01089   0.00497  -0.0876   0.7370   0.0145
  -6.500  -0.2159   0.01065   0.00468  -0.0869   0.7297   0.0152
  -6.250  -0.1912   0.01045   0.00445  -0.0861   0.7219   0.0166
  -6.000  -0.1659   0.01028   0.00422  -0.0855   0.7135   0.0178
  -5.750  -0.1413   0.01014   0.00400  -0.0847   0.7041   0.0188
  -5.500  -0.1158   0.00997   0.00381  -0.0840   0.6954   0.0202
  -5.250  -0.0907   0.00986   0.00365  -0.0833   0.6865   0.0215
  -5.000  -0.0652   0.00975   0.00349  -0.0827   0.6771   0.0228
  -4.750  -0.0403   0.00963   0.00331  -0.0819   0.6662   0.0239
  -4.500  -0.0157   0.00953   0.00316  -0.0811   0.6546   0.0252
  -4.250   0.0093   0.00946   0.00304  -0.0804   0.6419   0.0266
  -4.000   0.0342   0.00940   0.00291  -0.0796   0.6279   0.0279
  -3.750   0.0589   0.00935   0.00279  -0.0788   0.6129   0.0286
  -3.500   0.0829   0.00926   0.00261  -0.0779   0.5961   0.0300
  -3.250   0.1068   0.00922   0.00250  -0.0770   0.5764   0.0315
  -3.000   0.1299   0.00924   0.00241  -0.0759   0.5470   0.0327
  -2.750   0.1504   0.00942   0.00236  -0.0743   0.4940   0.0340
  -2.500   0.1724   0.00954   0.00232  -0.0730   0.4592   0.0349
  -2.250   0.1952   0.00961   0.00226  -0.0719   0.4364   0.0362
  -2.000   0.2197   0.00957   0.00218  -0.0710   0.4273   0.0383
  -1.750   0.2444   0.00954   0.00212  -0.0703   0.4203   0.0403
  -1.500   0.2692   0.00952   0.00207  -0.0696   0.4143   0.0423
  -1.250   0.2942   0.00950   0.00202  -0.0689   0.4084   0.0447
  -1.000   0.3188   0.00946   0.00198  -0.0681   0.4035   0.0493
  -0.750   0.3435   0.00945   0.00195  -0.0673   0.3992   0.0531
  -0.500   0.3686   0.00941   0.00192  -0.0667   0.3961   0.0598
  -0.250   0.3935   0.00938   0.00190  -0.0660   0.3925   0.0667
   0.000   0.4177   0.00936   0.00190  -0.0651   0.3879   0.0787
   0.250   0.4415   0.00934   0.00190  -0.0643   0.3841   0.0951
   0.500   0.4646   0.00921   0.00189  -0.0632   0.3813   0.1373
   0.750   0.4866   0.00904   0.00192  -0.0620   0.3780   0.2147
   1.000   0.5107   0.00903   0.00196  -0.0612   0.3742   0.2417
   1.250   0.5348   0.00905   0.00201  -0.0604   0.3705   0.2609
   1.500   0.5588   0.00910   0.00206  -0.0595   0.3668   0.2749
   1.750   0.5837   0.00911   0.00209  -0.0589   0.3638   0.2872
   2.000   0.6080   0.00914   0.00214  -0.0581   0.3592   0.2989
   2.250   0.6315   0.00920   0.00219  -0.0572   0.3526   0.3093
   2.500   0.6551   0.00923   0.00224  -0.0563   0.3463   0.3262
   3.000   0.7020   0.00934   0.00236  -0.0545   0.3353   0.3472
   3.250   0.7254   0.00938   0.00242  -0.0536   0.3285   0.3618
   3.500   0.7475   0.00944   0.00249  -0.0524   0.3208   0.3843
   3.750   0.7664   0.00946   0.00259  -0.0507   0.3048   0.4479
   4.250   0.9090   0.00935   0.00350  -0.0713   0.2526   0.9761
   4.500   0.9325   0.00986   0.00382  -0.0707   0.2206   0.9820
   4.750   0.9569   0.01032   0.00413  -0.0704   0.1957   0.9862
   5.000   0.9887   0.01071   0.00442  -0.0716   0.1793   0.9889
   5.250   1.0193   0.01098   0.00464  -0.0725   0.1726   0.9913
   5.500   1.0491   0.01122   0.00487  -0.0732   0.1678   0.9937
   5.750   1.0830   0.01150   0.00510  -0.0749   0.1621   0.9955
   6.000   1.1167   0.01173   0.00531  -0.0766   0.1572   0.9972
   6.250   1.1491   0.01194   0.00552  -0.0780   0.1529   0.9985
   6.500   1.1809   0.01219   0.00574  -0.0792   0.1484   0.9997
   6.750   1.2034   0.01245   0.00597  -0.0784   0.1435   1.0000
   7.000   1.2217   0.01263   0.00618  -0.0766   0.1404   1.0000
   7.250   1.2372   0.01293   0.00643  -0.0743   0.1320   1.0000
   7.500   1.2477   0.01329   0.00672  -0.0711   0.1178   1.0000
   7.750   1.2493   0.01393   0.00719  -0.0661   0.0892   1.0000
   8.000   1.2582   0.01435   0.00758  -0.0626   0.0792   1.0000
   8.250   1.2692   0.01475   0.00796  -0.0596   0.0727   1.0000
   8.500   1.2828   0.01506   0.00829  -0.0571   0.0680   1.0000
   8.750   1.2822   0.01603   0.00910  -0.0523   0.0377   1.0000
   9.000   1.2938   0.01652   0.00958  -0.0496   0.0339   1.0000
   9.250   1.3067   0.01695   0.01004  -0.0472   0.0313   1.0000
   9.500   1.3203   0.01739   0.01051  -0.0450   0.0300   1.0000
   9.750   1.3335   0.01785   0.01101  -0.0428   0.0291   1.0000
  10.000   1.3458   0.01838   0.01157  -0.0405   0.0279   1.0000
  10.250   1.3578   0.01894   0.01217  -0.0383   0.0269   1.0000
  10.500   1.3694   0.01956   0.01282  -0.0361   0.0258   1.0000
  10.750   1.3821   0.02013   0.01343  -0.0341   0.0248   1.0000
  11.000   1.3950   0.02071   0.01406  -0.0322   0.0242   1.0000
  11.250   1.4074   0.02135   0.01474  -0.0304   0.0237   1.0000
  11.500   1.4189   0.02206   0.01550  -0.0285   0.0229   1.0000
  11.750   1.4296   0.02285   0.01633  -0.0266   0.0219   1.0000
  12.000   1.4389   0.02377   0.01729  -0.0247   0.0208   1.0000
  12.250   1.4483   0.02472   0.01829  -0.0230   0.0198   1.0000
  12.500   1.4589   0.02564   0.01926  -0.0214   0.0190   1.0000
  12.750   1.4685   0.02666   0.02033  -0.0199   0.0179   1.0000
  13.000   1.4766   0.02784   0.02152  -0.0185   0.0163   1.0000
  13.250   1.4842   0.02910   0.02282  -0.0170   0.0149   1.0000
  13.500   1.4913   0.03046   0.02422  -0.0157   0.0139   1.0000
  13.750   1.4970   0.03198   0.02578  -0.0144   0.0129   1.0000
  14.000   1.5020   0.03359   0.02744  -0.0132   0.0120   1.0000
  14.250   1.5062   0.03534   0.02925  -0.0121   0.0108   1.0000
  14.500   1.5095   0.03725   0.03122  -0.0111   0.0102   1.0000
  14.750   1.5111   0.03938   0.03341  -0.0101   0.0095   1.0000
  15.000   1.5128   0.04157   0.03567  -0.0094   0.0092   1.0000
  15.250   1.5136   0.04392   0.03810  -0.0087   0.0086   1.0000
  15.500   1.5131   0.04651   0.04076  -0.0082   0.0082   1.0000
  15.750   1.5109   0.04936   0.04370  -0.0078   0.0079   1.0000
  16.000   1.5077   0.05241   0.04682  -0.0077   0.0075   1.0000
  16.250   1.5021   0.05588   0.05038  -0.0077   0.0071   1.0000
  16.500   1.4981   0.05928   0.05388  -0.0079   0.0069   1.0000
  16.750   1.4926   0.06296   0.05765  -0.0083   0.0067   1.0000
  17.000   1.4854   0.06696   0.06175  -0.0088   0.0065   1.0000
  17.250   1.4777   0.07114   0.06603  -0.0096   0.0063   1.0000
  17.500   1.4686   0.07561   0.07060  -0.0105   0.0062   1.0000
  17.750   1.4586   0.08020   0.07528  -0.0115   0.0060   1.0000
  18.000   1.4478   0.08494   0.08012  -0.0126   0.0059   1.0000
  18.250   1.4374   0.08967   0.08494  -0.0138   0.0059   1.0000
  18.500   1.4243   0.09484   0.09021  -0.0152   0.0056   1.0000
  18.750   1.4106   0.10014   0.09560  -0.0167   0.0054   1.0000
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