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GOE 617 AIRFOIL (goe617-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 617 AIRFOIL (goe617-il)
Reynolds number: 500,000
Max Cl/Cd: 87.85 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe617-il-500000.txt
Download as CSV file: xf-goe617-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 617 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.8467   0.08089   0.07771  -0.0598   1.0000   0.0238
 -16.000  -0.8886   0.06962   0.06622  -0.0677   1.0000   0.0237
 -15.750  -0.9189   0.06120   0.05759  -0.0735   1.0000   0.0237
 -15.500  -0.9417   0.05477   0.05097  -0.0773   1.0000   0.0237
 -15.250  -0.9629   0.04928   0.04527  -0.0801   1.0000   0.0239
 -15.000  -0.9806   0.04483   0.04066  -0.0812   1.0000   0.0241
 -14.750  -0.9895   0.04174   0.03746  -0.0811   1.0000   0.0244
 -14.500  -0.9886   0.03994   0.03564  -0.0804   1.0000   0.0248
 -14.250  -0.9892   0.03818   0.03382  -0.0793   1.0000   0.0251
 -14.000  -0.9866   0.03693   0.03253  -0.0779   1.0000   0.0255
 -13.750  -0.9914   0.03507   0.03054  -0.0757   1.0000   0.0258
 -13.500  -0.9927   0.03376   0.02913  -0.0731   1.0000   0.0262
 -13.250  -0.9945   0.03249   0.02774  -0.0701   1.0000   0.0267
 -13.000  -0.9969   0.03131   0.02642  -0.0665   1.0000   0.0271
 -12.750  -0.9996   0.03034   0.02531  -0.0625   1.0000   0.0275
 -12.500  -1.0038   0.02959   0.02443  -0.0577   1.0000   0.0279
 -12.250  -1.0097   0.02895   0.02368  -0.0523   1.0000   0.0280
 -12.000  -1.0188   0.02741   0.02201  -0.0467   1.0000   0.0286
 -11.750  -1.0198   0.02659   0.02117  -0.0421   1.0000   0.0290
 -11.500  -1.0205   0.02610   0.02067  -0.0375   1.0000   0.0295
 -11.250  -1.0198   0.02588   0.02045  -0.0330   1.0000   0.0300
 -11.000  -0.9960   0.02513   0.01962  -0.0331   0.9982   0.0309
 -10.750  -0.9658   0.02427   0.01863  -0.0343   0.9955   0.0319
 -10.500  -0.9347   0.02346   0.01765  -0.0357   0.9929   0.0328
 -10.250  -0.9081   0.02200   0.01608  -0.0364   0.9893   0.0339
 -10.000  -0.8756   0.02127   0.01535  -0.0380   0.9861   0.0350
  -9.750  -0.8409   0.02065   0.01468  -0.0399   0.9837   0.0362
  -9.500  -0.8085   0.02000   0.01395  -0.0412   0.9811   0.0375
  -9.250  -0.7800   0.01944   0.01328  -0.0416   0.9764   0.0384
  -9.000  -0.7500   0.01828   0.01207  -0.0426   0.9734   0.0398
  -8.750  -0.7158   0.01775   0.01154  -0.0443   0.9712   0.0413
  -8.500  -0.6804   0.01720   0.01096  -0.0462   0.9697   0.0428
  -8.250  -0.6547   0.01674   0.01044  -0.0459   0.9637   0.0441
  -8.000  -0.6223   0.01616   0.00978  -0.0470   0.9606   0.0454
  -7.750  -0.5894   0.01539   0.00905  -0.0484   0.9583   0.0475
  -7.500  -0.5525   0.01495   0.00860  -0.0504   0.9566   0.0495
  -7.250  -0.5206   0.01455   0.00815  -0.0514   0.9527   0.0515
  -7.000  -0.4919   0.01400   0.00757  -0.0517   0.9471   0.0539
  -6.750  -0.4578   0.01359   0.00718  -0.0531   0.9433   0.0566
  -6.500  -0.4210   0.01324   0.00680  -0.0550   0.9402   0.0599
  -6.250  -0.3973   0.01282   0.00635  -0.0542   0.9318   0.0631
  -6.000  -0.3653   0.01246   0.00601  -0.0551   0.9264   0.0672
  -5.750  -0.3366   0.01229   0.00579  -0.0553   0.9194   0.0710
  -5.500  -0.3120   0.01179   0.00528  -0.0547   0.9115   0.0759
  -5.250  -0.2851   0.01153   0.00500  -0.0544   0.9041   0.0801
  -5.000  -0.2595   0.01137   0.00477  -0.0538   0.8957   0.0833
  -4.750  -0.2362   0.01096   0.00437  -0.0529   0.8877   0.0888
  -4.500  -0.2127   0.01074   0.00413  -0.0519   0.8788   0.0932
  -4.250  -0.1875   0.01057   0.00390  -0.0513   0.8706   0.0970
  -4.000  -0.1649   0.01030   0.00365  -0.0501   0.8613   0.1033
  -3.750  -0.1410   0.01011   0.00345  -0.0491   0.8521   0.1097
  -3.500  -0.1173   0.00987   0.00325  -0.0481   0.8427   0.1235
  -3.250  -0.0964   0.00955   0.00311  -0.0467   0.8320   0.1633
  -3.000  -0.0737   0.00927   0.00294  -0.0455   0.8214   0.2066
  -2.750  -0.0526   0.00897   0.00275  -0.0441   0.8092   0.2457
  -2.500  -0.0358   0.00845   0.00260  -0.0419   0.7965   0.3407
  -2.250  -0.0174   0.00809   0.00248  -0.0399   0.7846   0.4242
  -2.000   0.0018   0.00781   0.00237  -0.0380   0.7725   0.4858
  -1.750   0.0196   0.00753   0.00228  -0.0358   0.7594   0.5488
  -1.500   0.0359   0.00724   0.00222  -0.0332   0.7457   0.6190
  -1.250   0.0520   0.00697   0.00217  -0.0304   0.7321   0.6921
  -1.000   0.0707   0.00674   0.00220  -0.0281   0.7181   0.7682
  -0.750   0.0974   0.00671   0.00229  -0.0274   0.7043   0.8289
  -0.500   0.1271   0.00679   0.00237  -0.0274   0.6903   0.8619
  -0.250   0.1581   0.00692   0.00246  -0.0278   0.6767   0.8829
   0.000   0.1898   0.00706   0.00256  -0.0283   0.6634   0.8981
   0.250   0.2191   0.00722   0.00265  -0.0283   0.6493   0.9103
   0.500   0.2504   0.00741   0.00276  -0.0288   0.6348   0.9202
   0.750   0.2882   0.00769   0.00295  -0.0306   0.6203   0.9285
   1.000   0.3246   0.00797   0.00315  -0.0322   0.6087   0.9362
   1.250   0.3577   0.00815   0.00328  -0.0331   0.5973   0.9411
   1.500   0.4004   0.00840   0.00347  -0.0361   0.5854   0.9434
   1.750   0.4413   0.00867   0.00366  -0.0387   0.5719   0.9471
   2.000   0.4662   0.00888   0.00381  -0.0379   0.5602   0.9551
   2.250   0.5061   0.00903   0.00392  -0.0404   0.5482   0.9566
   2.500   0.5452   0.00920   0.00405  -0.0428   0.5372   0.9589
   2.750   0.5832   0.00941   0.00419  -0.0450   0.5260   0.9626
   3.000   0.6094   0.00958   0.00435  -0.0445   0.5143   0.9692
   3.250   0.6505   0.00973   0.00443  -0.0474   0.4980   0.9712
   3.500   0.6920   0.00990   0.00453  -0.0504   0.4802   0.9744
   3.750   0.7278   0.01006   0.00465  -0.0521   0.4649   0.9791
   4.000   0.7604   0.01021   0.00474  -0.0533   0.4481   0.9831
   4.250   0.7965   0.01030   0.00476  -0.0552   0.4311   0.9853
   4.500   0.8300   0.01042   0.00482  -0.0566   0.4140   0.9880
   4.750   0.8614   0.01055   0.00491  -0.0576   0.3979   0.9911
   5.000   0.8918   0.01072   0.00502  -0.0584   0.3810   0.9939
   5.250   0.9249   0.01084   0.00507  -0.0598   0.3619   0.9960
   5.500   0.9570   0.01100   0.00516  -0.0610   0.3420   0.9985
   5.750   0.9848   0.01121   0.00530  -0.0614   0.3217   1.0000
   6.000   1.0006   0.01148   0.00550  -0.0592   0.3024   1.0000
   6.250   1.0157   0.01178   0.00571  -0.0569   0.2783   1.0000
   6.500   1.0277   0.01221   0.00598  -0.0541   0.2435   1.0000
   6.750   1.0368   0.01277   0.00633  -0.0508   0.2065   1.0000
   7.000   1.0469   0.01325   0.00669  -0.0476   0.1855   1.0000
   7.250   1.0578   0.01365   0.00704  -0.0445   0.1735   1.0000
   7.500   1.0673   0.01408   0.00741  -0.0412   0.1638   1.0000
   7.750   1.0792   0.01437   0.00772  -0.0383   0.1563   1.0000
   8.000   1.0864   0.01481   0.00811  -0.0345   0.1482   1.0000
   8.250   1.0979   0.01506   0.00840  -0.0315   0.1414   1.0000
   8.500   1.1022   0.01549   0.00878  -0.0272   0.1338   1.0000
   8.750   1.1086   0.01570   0.00903  -0.0231   0.1277   1.0000
   9.000   1.1103   0.01605   0.00936  -0.0183   0.1214   1.0000
   9.250   1.1166   0.01637   0.00969  -0.0144   0.1158   1.0000
   9.500   1.1232   0.01676   0.01006  -0.0107   0.1103   1.0000
   9.750   1.1288   0.01727   0.01056  -0.0069   0.1056   1.0000
  10.000   1.1393   0.01766   0.01098  -0.0041   0.1013   1.0000
  10.250   1.1473   0.01820   0.01152  -0.0011   0.0975   1.0000
  10.500   1.1523   0.01893   0.01223   0.0023   0.0939   1.0000
  10.750   1.1645   0.01940   0.01278   0.0045   0.0916   1.0000
  11.000   1.1750   0.02000   0.01341   0.0068   0.0890   1.0000
  11.250   1.1840   0.02072   0.01414   0.0092   0.0862   1.0000
  11.500   1.1887   0.02172   0.01514   0.0119   0.0830   1.0000
  11.750   1.1997   0.02245   0.01593   0.0138   0.0812   1.0000
  12.000   1.2116   0.02317   0.01672   0.0155   0.0793   1.0000
  12.250   1.2225   0.02398   0.01759   0.0171   0.0772   1.0000
  12.500   1.2313   0.02496   0.01860   0.0188   0.0751   1.0000
  12.750   1.2357   0.02629   0.01993   0.0208   0.0724   1.0000
  13.000   1.2453   0.02733   0.02104   0.0222   0.0707   1.0000
  13.250   1.2576   0.02822   0.02202   0.0232   0.0691   1.0000
  13.500   1.2690   0.02921   0.02307   0.0243   0.0670   1.0000
  13.750   1.2780   0.03042   0.02432   0.0253   0.0651   1.0000
  14.000   1.2828   0.03199   0.02592   0.0265   0.0631   1.0000
  14.250   1.2892   0.03350   0.02750   0.0275   0.0612   1.0000
  14.500   1.3021   0.03453   0.02862   0.0280   0.0589   1.0000
  14.750   1.3118   0.03586   0.03000   0.0286   0.0562   1.0000
  15.000   1.3161   0.03771   0.03188   0.0292   0.0539   1.0000
  15.250   1.3261   0.03911   0.03336   0.0296   0.0506   1.0000
  15.500   1.3314   0.04099   0.03524   0.0299   0.0459   1.0000
  15.750   1.3369   0.04291   0.03720   0.0302   0.0404   1.0000
  16.000   1.3378   0.04534   0.03966   0.0304   0.0362   1.0000
  16.250   1.3343   0.04830   0.04263   0.0305   0.0309   1.0000
  16.500   1.3279   0.05170   0.04605   0.0304   0.0272   1.0000
  16.750   1.3231   0.05504   0.04945   0.0301   0.0255   1.0000
  17.000   1.3153   0.05879   0.05326   0.0296   0.0240   1.0000
  17.250   1.3088   0.06252   0.05708   0.0289   0.0229   1.0000
  17.500   1.3022   0.06636   0.06103   0.0281   0.0222   1.0000
  17.750   1.2936   0.07055   0.06531   0.0271   0.0215   1.0000
  18.000   1.2853   0.07480   0.06965   0.0259   0.0211   1.0000
  18.250   1.2722   0.07984   0.07478   0.0243   0.0206   1.0000
  18.500   1.2582   0.08511   0.08014   0.0225   0.0200   1.0000
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