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GOE 385 AIRFOIL (goe385-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 385 AIRFOIL (goe385-il)
Reynolds number: 200,000
Max Cl/Cd: 73.03 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe385-il-200000.txt
Download as CSV file: xf-goe385-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 385 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3476   0.08901   0.08573  -0.0269   1.0000   0.0359
  -7.750  -0.3462   0.08598   0.08275  -0.0282   1.0000   0.0367
  -7.500  -0.3472   0.08303   0.07986  -0.0297   1.0000   0.0375
  -7.250  -0.3481   0.07998   0.07688  -0.0315   1.0000   0.0384
  -7.000  -0.3521   0.07723   0.07417  -0.0327   1.0000   0.0394
  -6.750  -0.2844   0.05780   0.05488  -0.0495   0.9857   0.0427
  -6.500  -0.2635   0.05349   0.05060  -0.0497   0.9820   0.0441
  -6.250  -0.2407   0.04878   0.04585  -0.0538   0.9755   0.0459
  -6.000  -0.2124   0.04316   0.04012  -0.0606   0.9712   0.0487
  -5.750  -0.1748   0.03856   0.03484  -0.0703   0.9600   0.0536
  -5.500  -0.1600   0.03134   0.02774  -0.0726   0.9535   0.0555
  -5.250  -0.1360   0.02831   0.02473  -0.0740   0.9442   0.0586
  -5.000  -0.1024   0.02678   0.02250  -0.0761   0.9293   0.0672
  -4.750  -0.0897   0.02119   0.01696  -0.0769   0.9176   0.0695
  -4.500  -0.0703   0.01894   0.01470  -0.0766   0.9038   0.0725
  -4.250  -0.0464   0.01679   0.01200  -0.0764   0.8885   0.0834
  -4.000  -0.0281   0.01466   0.00997  -0.0760   0.8755   0.0875
  -3.750  -0.0057   0.01293   0.00786  -0.0755   0.8611   0.0998
  -3.500   0.0159   0.01160   0.00647  -0.0749   0.8478   0.1074
  -3.250   0.0381   0.01021   0.00488  -0.0745   0.8349   0.1204
  -3.000   0.0611   0.00917   0.00363  -0.0740   0.8223   0.1382
  -2.750   0.0826   0.00811   0.00245  -0.0736   0.8093   0.1643
  -2.500   0.1113   0.02202   0.01599  -0.0775   0.8237   0.1939
  -2.250   0.1348   0.02086   0.01473  -0.0769   0.8079   0.2243
  -2.000   0.1833   0.01768   0.01002  -0.0742   0.7960   0.0741
  -1.750   0.2111   0.01676   0.00882  -0.0735   0.7823   0.0718
  -1.500   0.2393   0.01619   0.00802  -0.0729   0.7700   0.0690
  -1.250   0.2671   0.01582   0.00753  -0.0725   0.7586   0.0678
  -1.000   0.2946   0.01527   0.00686  -0.0720   0.7481   0.0674
  -0.750   0.3218   0.01458   0.00614  -0.0717   0.7373   0.0675
  -0.500   0.3487   0.01387   0.00544  -0.0713   0.7264   0.0687
  -0.250   0.3756   0.01337   0.00495  -0.0711   0.7163   0.0724
   0.000   0.4028   0.01307   0.00460  -0.0708   0.7064   0.0750
   0.250   0.4305   0.01284   0.00434  -0.0706   0.6956   0.0780
   0.750   0.4859   0.01254   0.00387  -0.0702   0.6760   0.0967
   1.000   0.5144   0.01016   0.00384  -0.0700   0.6655   1.0000
   1.250   0.5416   0.01030   0.00380  -0.0697   0.6551   1.0000
   1.500   0.5687   0.01047   0.00379  -0.0695   0.6454   1.0000
   1.750   0.5958   0.01062   0.00383  -0.0693   0.6345   1.0000
   2.000   0.6228   0.01078   0.00391  -0.0691   0.6235   1.0000
   2.250   0.6498   0.01096   0.00399  -0.0688   0.6125   1.0000
   2.500   0.6768   0.01115   0.00406  -0.0686   0.6013   1.0000
   2.750   0.7036   0.01129   0.00416  -0.0684   0.5884   1.0000
   3.000   0.7304   0.01143   0.00426  -0.0681   0.5750   1.0000
   3.250   0.7570   0.01157   0.00436  -0.0679   0.5609   1.0000
   3.500   0.7836   0.01170   0.00444  -0.0676   0.5461   1.0000
   3.750   0.8101   0.01183   0.00453  -0.0673   0.5303   1.0000
   4.000   0.8364   0.01197   0.00463  -0.0670   0.5135   1.0000
   4.250   0.8625   0.01214   0.00473  -0.0667   0.4954   1.0000
   4.500   0.8885   0.01233   0.00489  -0.0664   0.4764   1.0000
   4.750   0.9143   0.01259   0.00507  -0.0661   0.4590   1.0000
   5.000   0.9399   0.01289   0.00532  -0.0658   0.4430   1.0000
   5.250   0.9655   0.01322   0.00559  -0.0655   0.4283   1.0000
   5.500   0.9909   0.01357   0.00589  -0.0652   0.4141   1.0000
   5.750   1.0161   0.01392   0.00621  -0.0649   0.4000   1.0000
   6.000   1.0412   0.01429   0.00655  -0.0645   0.3872   1.0000
   6.250   1.0664   0.01469   0.00692  -0.0642   0.3765   1.0000
   6.500   1.0914   0.01509   0.00730  -0.0639   0.3665   1.0000
   6.750   1.1165   0.01545   0.00774  -0.0636   0.3560   1.0000
   7.000   1.1411   0.01587   0.00816  -0.0633   0.3461   1.0000
   7.250   1.1651   0.01628   0.00855  -0.0628   0.3349   1.0000
   7.500   1.1886   0.01664   0.00894  -0.0623   0.3221   1.0000
   7.750   1.2120   0.01698   0.00938  -0.0618   0.3096   1.0000
   8.000   1.2352   0.01734   0.00982  -0.0612   0.2977   1.0000
   8.250   1.2578   0.01771   0.01027  -0.0606   0.2850   1.0000
   8.500   1.2800   0.01809   0.01071  -0.0599   0.2712   1.0000
   8.750   1.3016   0.01847   0.01119  -0.0592   0.2561   1.0000
   9.000   1.3226   0.01891   0.01169  -0.0583   0.2388   1.0000
   9.250   1.3420   0.01943   0.01223  -0.0573   0.2144   1.0000
   9.500   1.3569   0.02031   0.01295  -0.0558   0.1687   1.0000
   9.750   1.3585   0.02233   0.01451  -0.0528   0.1104   1.0000
  10.000   1.3516   0.02494   0.01664  -0.0488   0.0538   1.0000
  10.250   1.3482   0.02685   0.01858  -0.0449   0.0424   1.0000
  10.500   1.3503   0.02850   0.02033  -0.0420   0.0370   1.0000
  10.750   1.3492   0.03051   0.02243  -0.0394   0.0342   1.0000
  11.000   1.3520   0.03235   0.02442  -0.0375   0.0322   1.0000
  11.250   1.3535   0.03446   0.02665  -0.0360   0.0305   1.0000
  11.500   1.3529   0.03690   0.02920  -0.0347   0.0290   1.0000
  11.750   1.3467   0.04005   0.03243  -0.0337   0.0279   1.0000
  12.000   1.3425   0.04317   0.03566  -0.0330   0.0270   1.0000
  12.250   1.3420   0.04602   0.03866  -0.0325   0.0262   1.0000
  12.500   1.3402   0.04909   0.04185  -0.0321   0.0256   1.0000
  12.750   1.3384   0.05220   0.04507  -0.0317   0.0250   1.0000
  13.000   1.3369   0.05528   0.04826  -0.0314   0.0245   1.0000
  13.250   1.3361   0.05829   0.05136  -0.0310   0.0240   1.0000
  13.500   1.3361   0.06119   0.05434  -0.0305   0.0235   1.0000
  13.750   1.3371   0.06397   0.05719  -0.0298   0.0231   1.0000
  14.000   1.3395   0.06656   0.05985  -0.0290   0.0227   1.0000
  14.250   1.3429   0.06906   0.06241  -0.0280   0.0223   1.0000
  14.500   1.3479   0.07144   0.06487  -0.0265   0.0218   1.0000
  14.750   1.3517   0.07432   0.06788  -0.0249   0.0213   1.0000
  15.000   1.3483   0.07802   0.07179  -0.0255   0.0211   1.0000
  15.250   1.3442   0.08195   0.07592  -0.0261   0.0208   1.0000
  15.500   1.3391   0.08613   0.08031  -0.0268   0.0207   1.0000
  15.750   1.3324   0.09068   0.08508  -0.0277   0.0206   1.0000
  16.000   1.3240   0.09559   0.09019  -0.0290   0.0206   1.0000
  16.250   1.3134   0.10099   0.09581  -0.0309   0.0206   1.0000
  16.500   1.3015   0.10678   0.10181  -0.0332   0.0207   1.0000
  16.750   1.2881   0.11304   0.10828  -0.0360   0.0208   1.0000
  17.000   1.2738   0.11967   0.11510  -0.0393   0.0209   1.0000
  17.250   1.2586   0.12675   0.12238  -0.0432   0.0210   1.0000
  17.500   1.2429   0.13424   0.13005  -0.0475   0.0211   1.0000
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