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GOE 407 AIRFOIL (goe407-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 407 AIRFOIL (goe407-il)
Reynolds number: 100,000
Max Cl/Cd: 57.72 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe407-il-100000-n5.txt
Download as CSV file: xf-goe407-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 407 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3322   0.10521   0.10037  -0.0335   1.0000   0.0556
  -8.250  -0.3475   0.10391   0.09918  -0.0330   1.0000   0.0557
  -8.000  -0.3614   0.10243   0.09779  -0.0321   1.0000   0.0557
  -7.750  -0.3363   0.09689   0.09225  -0.0289   1.0000   0.0567
  -7.500  -0.3406   0.09482   0.09025  -0.0266   1.0000   0.0574
  -7.250  -0.3313   0.09183   0.08729  -0.0280   0.9964   0.0588
  -7.000  -0.3099   0.08787   0.08330  -0.0344   0.9880   0.0622
  -6.750  -0.2803   0.08334   0.07857  -0.0529   0.9721   0.0649
  -6.500  -0.2648   0.07863   0.07391  -0.0532   0.9648   0.0656
  -6.250  -0.2436   0.07470   0.06998  -0.0541   0.9600   0.0667
  -6.000  -0.2259   0.07138   0.06664  -0.0559   0.9494   0.0682
  -5.750  -0.2061   0.06801   0.06321  -0.0589   0.9382   0.0701
  -5.500  -0.1784   0.06476   0.05968  -0.0663   0.9240   0.0750
  -5.250  -0.1545   0.06050   0.05527  -0.0700   0.9154   0.0764
  -5.000  -0.1398   0.05741   0.05224  -0.0692   0.9045   0.0778
  -4.750  -0.1193   0.05458   0.04933  -0.0700   0.8948   0.0797
  -4.500  -0.0922   0.05149   0.04610  -0.0724   0.8873   0.0820
  -4.250  -0.0601   0.04980   0.04380  -0.0756   0.8756   0.0878
  -3.500   0.0215   0.03670   0.02974  -0.0783   0.8535   0.0555
  -3.250   0.0489   0.03441   0.02732  -0.0790   0.8457   0.0548
  -3.000   0.0784   0.03219   0.02486  -0.0798   0.8389   0.0535
  -2.750   0.1065   0.03004   0.02240  -0.0800   0.8308   0.0523
  -2.500   0.1378   0.02792   0.01990  -0.0806   0.8242   0.0512
  -2.250   0.1659   0.02613   0.01772  -0.0803   0.8152   0.0505
  -2.000   0.1972   0.02455   0.01577  -0.0807   0.8063   0.0503
  -1.750   0.2290   0.02341   0.01433  -0.0811   0.7961   0.0518
  -1.500   0.2568   0.02243   0.01306  -0.0807   0.7846   0.0530
  -1.250   0.2882   0.02140   0.01175  -0.0810   0.7750   0.0534
  -1.000   0.3168   0.02055   0.01068  -0.0808   0.7648   0.0537
  -0.750   0.3450   0.01984   0.00979  -0.0805   0.7550   0.0541
  -0.500   0.3758   0.01915   0.00895  -0.0807   0.7461   0.0549
  -0.250   0.4013   0.01868   0.00838  -0.0800   0.7359   0.0557
   0.000   0.4301   0.01817   0.00788  -0.0800   0.7273   0.0571
   0.250   0.4550   0.01790   0.00762  -0.0793   0.7171   0.0606
   0.500   0.4813   0.01762   0.00727  -0.0787   0.7076   0.0641
   0.750   0.5083   0.01730   0.00692  -0.0783   0.6983   0.0670
   1.000   0.5355   0.01711   0.00669  -0.0780   0.6880   0.0714
   1.250   0.5668   0.01690   0.00639  -0.0784   0.6785   0.0794
   1.500   0.5961   0.01668   0.00623  -0.0786   0.6678   0.1041
   2.000   0.7575   0.01500   0.00625  -0.1016   0.6402   1.0000
   2.250   0.7812   0.01516   0.00629  -0.1006   0.6292   1.0000
   2.500   0.8039   0.01533   0.00636  -0.0993   0.6172   1.0000
   2.750   0.8258   0.01552   0.00649  -0.0980   0.6046   1.0000
   3.000   0.8478   0.01570   0.00662  -0.0967   0.5917   1.0000
   3.250   0.8697   0.01590   0.00674  -0.0953   0.5785   1.0000
   3.500   0.8911   0.01609   0.00688  -0.0939   0.5644   1.0000
   3.750   0.9121   0.01629   0.00704  -0.0924   0.5496   1.0000
   4.000   0.9325   0.01650   0.00724  -0.0908   0.5342   1.0000
   4.250   0.9528   0.01673   0.00742  -0.0892   0.5183   1.0000
   4.500   0.9729   0.01697   0.00761  -0.0875   0.5021   1.0000
   4.750   0.9927   0.01723   0.00783  -0.0858   0.4856   1.0000
   5.000   1.0118   0.01753   0.00804  -0.0840   0.4682   1.0000
   5.250   1.0305   0.01787   0.00829  -0.0822   0.4513   1.0000
   5.500   1.0491   0.01824   0.00857  -0.0804   0.4358   1.0000
   5.750   1.0681   0.01864   0.00891  -0.0787   0.4228   1.0000
   6.000   1.0873   0.01905   0.00930  -0.0770   0.4108   1.0000
   6.250   1.1066   0.01947   0.00971  -0.0755   0.4002   1.0000
   6.500   1.1253   0.01991   0.01013  -0.0738   0.3894   1.0000
   6.750   1.1432   0.02036   0.01058  -0.0720   0.3779   1.0000
   7.000   1.1614   0.02080   0.01106  -0.0703   0.3676   1.0000
   7.250   1.1799   0.02127   0.01151  -0.0686   0.3593   1.0000
   7.500   1.1977   0.02171   0.01207  -0.0668   0.3497   1.0000
   7.750   1.2142   0.02218   0.01256  -0.0649   0.3397   1.0000
   8.000   1.2299   0.02266   0.01308  -0.0628   0.3296   1.0000
   8.250   1.2453   0.02314   0.01364  -0.0606   0.3195   1.0000
   8.500   1.2601   0.02366   0.01420  -0.0584   0.3105   1.0000
   8.750   1.2743   0.02416   0.01483  -0.0562   0.3006   1.0000
   9.000   1.2871   0.02470   0.01545  -0.0536   0.2907   1.0000
   9.250   1.2969   0.02526   0.01604  -0.0506   0.2807   1.0000
   9.500   1.3059   0.02581   0.01672  -0.0475   0.2692   1.0000
   9.750   1.3139   0.02642   0.01744  -0.0443   0.2578   1.0000
  10.000   1.3207   0.02711   0.01818  -0.0411   0.2458   1.0000
  10.250   1.3261   0.02790   0.01902  -0.0378   0.2323   1.0000
  10.500   1.3303   0.02880   0.01997  -0.0346   0.2169   1.0000
  10.750   1.3338   0.02984   0.02105  -0.0315   0.1996   1.0000
  11.000   1.3360   0.03104   0.02226  -0.0285   0.1817   1.0000
  11.250   1.3365   0.03244   0.02365  -0.0256   0.1655   1.0000
  11.500   1.3358   0.03405   0.02522  -0.0229   0.1523   1.0000
  11.750   1.3341   0.03585   0.02699  -0.0204   0.1418   1.0000
  12.000   1.3304   0.03794   0.02904  -0.0182   0.1334   1.0000
  12.250   1.3309   0.03987   0.03105  -0.0164   0.1264   1.0000
  12.500   1.3259   0.04232   0.03349  -0.0146   0.1197   1.0000
  12.750   1.3264   0.04446   0.03576  -0.0133   0.1136   1.0000
  13.000   1.3219   0.04712   0.03850  -0.0121   0.1071   1.0000
  13.250   1.3192   0.04973   0.04120  -0.0111   0.1016   1.0000
  13.500   1.3185   0.05225   0.04390  -0.0104   0.0962   1.0000
  13.750   1.3113   0.05555   0.04725  -0.0099   0.0910   1.0000
  14.000   1.3103   0.05833   0.05025  -0.0096   0.0848   1.0000
  14.250   1.3042   0.06181   0.05384  -0.0096   0.0795   1.0000
  14.500   1.2984   0.06540   0.05759  -0.0098   0.0725   1.0000
  14.750   1.2886   0.06964   0.06193  -0.0103   0.0672   1.0000
  15.000   1.2802   0.07389   0.06632  -0.0110   0.0608   1.0000
  15.250   1.2679   0.07883   0.07132  -0.0121   0.0566   1.0000
  15.500   1.2569   0.08376   0.07636  -0.0133   0.0514   1.0000
  15.750   1.2435   0.08923   0.08191  -0.0149   0.0478   1.0000
  16.000   1.2326   0.09439   0.08715  -0.0164   0.0446   1.0000
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