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GOE 335 (D.F.W.) AIRFOIL (goe335-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 335 (D.F.W.) AIRFOIL (goe335-il)
Reynolds number: 1,000,000
Max Cl/Cd: 119.15 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe335-il-1000000-n5.txt
Download as CSV file: xf-goe335-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 335 (D.F.W.) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3371   0.10745   0.10584  -0.0213   1.0000   0.0034
  -9.250  -0.3344   0.10419   0.10260  -0.0218   1.0000   0.0034
  -9.000  -0.3334   0.10063   0.09906  -0.0224   1.0000   0.0033
  -8.750  -0.3278   0.09807   0.09652  -0.0232   0.9998   0.0034
  -8.500  -0.3155   0.09282   0.09127  -0.0279   0.9972   0.0032
  -8.250  -0.3019   0.09023   0.08869  -0.0304   0.9900   0.0038
  -8.000  -0.2905   0.08639   0.08485  -0.0338   0.9819   0.0037
  -7.750  -0.2759   0.08213   0.08059  -0.0386   0.9722   0.0040
  -7.500  -0.2452   0.07612   0.07455  -0.0490   0.9567   0.0042
  -6.500  -0.2028   0.01409   0.00984  -0.1008   0.8018   0.0052
  -6.250  -0.1785   0.01282   0.00832  -0.1005   0.7918   0.0056
  -6.000  -0.1533   0.01198   0.00726  -0.1001   0.7822   0.0059
  -5.750  -0.1276   0.01129   0.00638  -0.0998   0.7728   0.0064
  -5.500  -0.1015   0.01070   0.00562  -0.0995   0.7647   0.0068
  -5.250  -0.0753   0.01021   0.00496  -0.0991   0.7557   0.0073
  -5.000  -0.0489   0.00972   0.00438  -0.0988   0.7469   0.0087
  -4.750  -0.0225   0.00935   0.00388  -0.0985   0.7374   0.0099
  -4.250   0.0315   0.00905   0.00350  -0.0980   0.7169   0.0143
  -4.000   0.0585   0.00895   0.00333  -0.0977   0.7057   0.0160
  -3.750   0.0861   0.00919   0.00359  -0.0975   0.6918   0.0177
  -3.500   0.1134   0.00938   0.00375  -0.0973   0.6778   0.0196
  -3.250   0.1405   0.00938   0.00367  -0.0970   0.6651   0.0214
  -3.000   0.1676   0.00944   0.00367  -0.0968   0.6527   0.0232
  -2.750   0.1947   0.00950   0.00365  -0.0965   0.6397   0.0243
  -2.500   0.2219   0.00962   0.00370  -0.0963   0.6259   0.0250
  -2.250   0.2489   0.00970   0.00371  -0.0961   0.6106   0.0254
  -2.000   0.2750   0.00930   0.00317  -0.0957   0.5921   0.0264
  -1.750   0.3007   0.00889   0.00260  -0.0953   0.5698   0.0274
  -1.500   0.3264   0.00874   0.00230  -0.0948   0.5399   0.0279
  -1.250   0.3519   0.00870   0.00208  -0.0943   0.5021   0.0281
  -1.000   0.3772   0.00871   0.00190  -0.0938   0.4654   0.0282
  -0.750   0.4031   0.00871   0.00177  -0.0934   0.4395   0.0286
  -0.500   0.4294   0.00869   0.00165  -0.0930   0.4219   0.0289
  -0.250   0.4559   0.00866   0.00153  -0.0927   0.4085   0.0287
   0.000   0.4827   0.00864   0.00144  -0.0925   0.3974   0.0286
   0.250   0.5095   0.00862   0.00138  -0.0922   0.3881   0.0285
   0.500   0.5362   0.00863   0.00132  -0.0920   0.3789   0.0285
   0.750   0.5630   0.00864   0.00128  -0.0917   0.3690   0.0286
   1.000   0.5898   0.00867   0.00126  -0.0915   0.3596   0.0290
   1.500   0.6436   0.00872   0.00125  -0.0910   0.3461   0.0321
   1.750   0.6705   0.00875   0.00129  -0.0908   0.3412   0.0374
   2.000   0.6972   0.00874   0.00136  -0.0906   0.3364   0.0792
   2.250   0.7240   0.00871   0.00143  -0.0904   0.3327   0.1202
   2.500   0.7501   0.00853   0.00157  -0.0903   0.3280   0.2788
   3.000   0.8079   0.00734   0.00188  -0.0913   0.3114   1.0000
   3.250   0.8341   0.00746   0.00197  -0.0910   0.3056   1.0000
   3.500   0.8606   0.00756   0.00206  -0.0907   0.3015   1.0000
   3.750   0.8868   0.00769   0.00217  -0.0904   0.2961   1.0000
   4.000   0.9130   0.00781   0.00228  -0.0901   0.2913   1.0000
   4.250   0.9394   0.00792   0.00240  -0.0898   0.2868   1.0000
   4.500   0.9651   0.00810   0.00254  -0.0895   0.2762   1.0000
   4.750   0.9902   0.00832   0.00268  -0.0891   0.2572   1.0000
   5.000   1.0137   0.00871   0.00290  -0.0884   0.2233   1.0000
   5.250   1.0336   0.00948   0.00334  -0.0872   0.1635   1.0000
   5.500   1.0517   0.01047   0.00395  -0.0857   0.0908   1.0000
   5.750   1.0737   0.01104   0.00439  -0.0848   0.0617   1.0000
   6.000   1.0936   0.01186   0.00497  -0.0836   0.0165   1.0000
   6.250   1.1180   0.01216   0.00529  -0.0831   0.0122   1.0000
   6.500   1.1415   0.01254   0.00570  -0.0824   0.0093   1.0000
   6.750   1.1654   0.01287   0.00607  -0.0818   0.0080   1.0000
   7.000   1.1890   0.01322   0.00644  -0.0811   0.0069   1.0000
   7.250   1.2116   0.01366   0.00690  -0.0804   0.0059   1.0000
   7.500   1.2341   0.01410   0.00739  -0.0795   0.0054   1.0000
   7.750   1.2567   0.01452   0.00787  -0.0788   0.0050   1.0000
   8.000   1.2788   0.01495   0.00834  -0.0779   0.0045   1.0000
   8.250   1.3005   0.01541   0.00883  -0.0771   0.0041   1.0000
   8.500   1.3197   0.01610   0.00957  -0.0758   0.0036   1.0000
   8.750   1.3402   0.01662   0.01015  -0.0747   0.0035   1.0000
   9.000   1.3599   0.01718   0.01078  -0.0736   0.0033   1.0000
   9.250   1.3786   0.01780   0.01147  -0.0722   0.0031   1.0000
   9.500   1.3964   0.01845   0.01218  -0.0708   0.0029   1.0000
   9.750   1.4134   0.01911   0.01294  -0.0693   0.0027   1.0000
  10.000   1.4292   0.01982   0.01371  -0.0676   0.0026   1.0000
  10.250   1.4437   0.02056   0.01451  -0.0657   0.0025   1.0000
  10.500   1.4534   0.02140   0.01543  -0.0630   0.0024   1.0000
  10.750   1.4557   0.02256   0.01669  -0.0592   0.0022   1.0000
  11.000   1.4571   0.02382   0.01807  -0.0556   0.0022   1.0000
  11.250   1.4623   0.02493   0.01928  -0.0528   0.0021   1.0000
  11.500   1.4673   0.02612   0.02056  -0.0502   0.0021   1.0000
  11.750   1.4713   0.02746   0.02201  -0.0478   0.0020   1.0000
  12.000   1.4726   0.02911   0.02377  -0.0454   0.0020   1.0000
  12.250   1.4759   0.03074   0.02550  -0.0437   0.0019   1.0000
  12.500   1.4747   0.03292   0.02781  -0.0419   0.0018   1.0000
  12.750   1.4728   0.03534   0.03036  -0.0405   0.0018   1.0000
  13.000   1.4755   0.03743   0.03254  -0.0397   0.0017   1.0000
  13.250   1.4712   0.04043   0.03567  -0.0389   0.0017   1.0000
  13.500   1.4735   0.04282   0.03818  -0.0385   0.0016   1.0000
  13.750   1.4678   0.04630   0.04180  -0.0383   0.0016   1.0000
  14.000   1.4607   0.05011   0.04575  -0.0385   0.0016   1.0000
  14.250   1.4528   0.05425   0.05003  -0.0390   0.0016   1.0000
  14.500   1.4485   0.05809   0.05398  -0.0398   0.0015   1.0000
  14.750   1.4446   0.06204   0.05805  -0.0408   0.0015   1.0000
  15.000   1.4338   0.06719   0.06335  -0.0423   0.0015   1.0000
  15.250   1.4276   0.07190   0.06818  -0.0439   0.0015   1.0000
  15.500   1.4207   0.07689   0.07328  -0.0459   0.0015   1.0000
  15.750   1.4145   0.08193   0.07843  -0.0480   0.0014   1.0000
  16.000   1.4024   0.08806   0.08471  -0.0505   0.0014   1.0000
  16.250   1.3929   0.09386   0.09063  -0.0530   0.0014   1.0000
  16.500   1.3842   0.09967   0.09655  -0.0557   0.0014   1.0000
  16.750   1.3754   0.10560   0.10259  -0.0585   0.0014   1.0000
  17.000   1.3625   0.11237   0.10950  -0.0617   0.0014   1.0000
  17.250   1.3543   0.11844   0.11567  -0.0648   0.0014   1.0000
  17.500   1.3420   0.12543   0.12279  -0.0684   0.0014   1.0000
  17.750   1.3302   0.13250   0.12999  -0.0721   0.0014   1.0000
  18.000   1.3178   0.13984   0.13745  -0.0762   0.0014   1.0000
  18.250   1.3051   0.14746   0.14521  -0.0805   0.0014   1.0000
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