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GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il)
Reynolds number: 1,000,000
Max Cl/Cd: 113.96 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe319-il-1000000.txt
Download as CSV file: xf-goe319-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 319 (HANSA-BRANDENBURG II) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2409   0.09493   0.09300  -0.0302   0.8730   0.0205
  -8.500  -0.2399   0.09129   0.08928  -0.0340   0.8528   0.0206
  -8.250  -0.2357   0.08772   0.08564  -0.0371   0.8324   0.0206
  -8.000  -0.2305   0.08391   0.08176  -0.0393   0.8126   0.0207
  -7.750  -0.2202   0.08128   0.07907  -0.0393   0.7953   0.0208
  -7.500  -0.2091   0.07876   0.07648  -0.0406   0.7800   0.0209
  -7.000  -0.1814   0.07331   0.07093  -0.0457   0.7559   0.0212
  -6.750  -0.1654   0.07044   0.06800  -0.0490   0.7462   0.0214
  -6.500  -0.1478   0.06743   0.06495  -0.0526   0.7377   0.0217
  -6.250  -0.1288   0.06434   0.06179  -0.0564   0.7299   0.0220
  -6.000  -0.1080   0.06107   0.05848  -0.0604   0.7228   0.0225
  -5.750  -0.0720   0.05451   0.05173  -0.0714   0.7161   0.0240
  -5.500  -0.0462   0.05035   0.04745  -0.0754   0.7093   0.0240
  -5.250  -0.0279   0.04645   0.04348  -0.0776   0.7019   0.0243
  -5.000  -0.0063   0.04439   0.04133  -0.0787   0.6941   0.0244
  -4.750   0.0170   0.04235   0.03925  -0.0799   0.6873   0.0246
  -4.500   0.0412   0.04031   0.03713  -0.0811   0.6800   0.0248
  -4.250   0.0665   0.03818   0.03490  -0.0824   0.6724   0.0252
  -4.000   0.0927   0.03595   0.03256  -0.0836   0.6640   0.0256
  -3.750   0.1198   0.03355   0.03003  -0.0848   0.6562   0.0264
  -3.500   0.1526   0.02707   0.02313  -0.0866   0.6495   0.0281
  -3.250   0.1772   0.02588   0.02184  -0.0867   0.6398   0.0284
  -3.000   0.2026   0.02475   0.02062  -0.0869   0.6280   0.0287
  -2.750   0.2286   0.02355   0.01931  -0.0870   0.6165   0.0291
  -2.500   0.2552   0.02214   0.01773  -0.0869   0.6064   0.0299
  -2.250   0.2834   0.01789   0.01292  -0.0863   0.5986   0.0325
  -2.000   0.3096   0.01713   0.01208  -0.0862   0.5890   0.0328
  -1.750   0.3364   0.01646   0.01132  -0.0861   0.5788   0.0333
  -1.500   0.3633   0.01580   0.01055  -0.0859   0.5693   0.0339
  -1.250   0.3924   0.01565   0.01007  -0.0853   0.5598   0.0368
  -1.000   0.0313   0.02657   0.02306  -0.0755   0.5923   0.0286
  -0.750   0.4459   0.01160   0.00539  -0.0842   0.5446   0.0324
  -0.500   0.4736   0.01116   0.00489  -0.0839   0.5369   0.0317
  -0.250   0.5012   0.01056   0.00421  -0.0837   0.5293   0.0314
   0.000   0.5287   0.01020   0.00376  -0.0834   0.5216   0.0314
   0.250   0.5565   0.00986   0.00338  -0.0832   0.5143   0.0314
   0.500   0.5840   0.00975   0.00320  -0.0829   0.5062   0.0318
   0.750   0.6119   0.00954   0.00296  -0.0827   0.4989   0.0322
   1.000   0.6387   0.00921   0.00260  -0.0824   0.4902   0.0326
   1.250   0.6662   0.00902   0.00241  -0.0821   0.4813   0.0332
   1.500   0.6934   0.00897   0.00232  -0.0819   0.4706   0.0340
   1.750   0.7211   0.00891   0.00225  -0.0817   0.4596   0.0348
   2.000   0.7485   0.00891   0.00220  -0.0815   0.4474   0.0356
   2.250   0.7757   0.00894   0.00218  -0.0813   0.4324   0.0364
   2.500   0.8026   0.00899   0.00216  -0.0810   0.4133   0.0376
   2.750   0.8288   0.00913   0.00220  -0.0807   0.3884   0.0400
   3.000   0.8547   0.00936   0.00229  -0.0803   0.3590   0.0423
   3.250   0.8800   0.00962   0.00242  -0.0798   0.3288   0.0486
   3.500   0.9047   0.00968   0.00268  -0.0794   0.3035   0.2128
   3.750   0.9404   0.00846   0.00304  -0.0818   0.2824   1.0000
   4.000   0.9655   0.00872   0.00319  -0.0812   0.2690   1.0000
   4.250   0.9906   0.00898   0.00336  -0.0807   0.2577   1.0000
   4.500   1.0166   0.00916   0.00349  -0.0803   0.2514   1.0000
   4.750   1.0421   0.00938   0.00366  -0.0799   0.2452   1.0000
   5.000   1.0680   0.00958   0.00382  -0.0795   0.2404   1.0000
   5.250   1.0941   0.00975   0.00397  -0.0792   0.2368   1.0000
   5.500   1.1198   0.00995   0.00414  -0.0788   0.2329   1.0000
   5.750   1.1451   0.01019   0.00434  -0.0784   0.2286   1.0000
   6.000   1.1706   0.01040   0.00454  -0.0780   0.2253   1.0000
   6.250   1.1968   0.01056   0.00470  -0.0777   0.2230   1.0000
   6.500   1.2225   0.01074   0.00488  -0.0774   0.2201   1.0000
   6.750   1.2478   0.01096   0.00509  -0.0770   0.2170   1.0000
   7.000   1.2726   0.01122   0.00533  -0.0766   0.2136   1.0000
   7.250   1.2968   0.01151   0.00561  -0.0761   0.2101   1.0000
   7.500   1.3226   0.01167   0.00579  -0.0758   0.2086   1.0000
   7.750   1.3481   0.01185   0.00599  -0.0755   0.2066   1.0000
   8.000   1.3732   0.01205   0.00621  -0.0751   0.2041   1.0000
   8.250   1.3977   0.01230   0.00646  -0.0747   0.2013   1.0000
   8.500   1.4211   0.01261   0.00675  -0.0741   0.1974   1.0000
   8.750   1.4449   0.01288   0.00703  -0.0736   0.1941   1.0000
   9.000   1.4702   0.01304   0.00722  -0.0733   0.1914   1.0000
   9.250   1.4944   0.01327   0.00746  -0.0729   0.1879   1.0000
   9.500   1.5174   0.01357   0.00775  -0.0723   0.1839   1.0000
   9.750   1.5395   0.01391   0.00809  -0.0716   0.1797   1.0000
  10.000   1.5639   0.01410   0.00831  -0.0712   0.1758   1.0000
  10.250   1.5861   0.01441   0.00860  -0.0706   0.1704   1.0000
  10.500   1.6072   0.01478   0.00897  -0.0697   0.1654   1.0000
  10.750   1.6293   0.01506   0.00928  -0.0690   0.1611   1.0000
  11.000   1.6489   0.01548   0.00968  -0.0680   0.1551   1.0000
  11.250   1.6671   0.01588   0.01008  -0.0667   0.1497   1.0000
  11.500   1.6838   0.01635   0.01054  -0.0653   0.1440   1.0000
  11.750   1.6992   0.01689   0.01109  -0.0637   0.1387   1.0000
  12.000   1.7150   0.01743   0.01164  -0.0622   0.1340   1.0000
  12.250   1.7278   0.01816   0.01235  -0.0605   0.1283   1.0000
  12.500   1.7429   0.01878   0.01301  -0.0592   0.1246   1.0000
  12.750   1.7564   0.01953   0.01377  -0.0577   0.1207   1.0000
  13.000   1.7672   0.02048   0.01473  -0.0561   0.1160   1.0000
  13.250   1.7813   0.02125   0.01555  -0.0550   0.1130   1.0000
  13.500   1.7933   0.02220   0.01651  -0.0537   0.1094   1.0000
  13.750   1.8024   0.02338   0.01772  -0.0523   0.1053   1.0000
  14.000   1.8142   0.02442   0.01880  -0.0512   0.1023   1.0000
  14.250   1.8250   0.02556   0.01998  -0.0502   0.0987   1.0000
  14.500   1.8318   0.02706   0.02150  -0.0490   0.0944   1.0000
  14.750   1.8408   0.02845   0.02293  -0.0480   0.0903   1.0000
  15.000   1.8459   0.03019   0.02467  -0.0470   0.0848   1.0000
  15.250   1.8507   0.03202   0.02654  -0.0461   0.0797   1.0000
  15.500   1.8507   0.03435   0.02885  -0.0451   0.0732   1.0000
  15.750   1.8499   0.03678   0.03129  -0.0442   0.0671   1.0000
  16.000   1.8471   0.03949   0.03402  -0.0434   0.0619   1.0000
  16.250   1.8409   0.04258   0.03714  -0.0427   0.0572   1.0000
  16.500   1.8374   0.04550   0.04011  -0.0421   0.0534   1.0000
  16.750   1.8288   0.04909   0.04374  -0.0418   0.0494   1.0000
  17.000   1.8228   0.05249   0.04720  -0.0416   0.0455   1.0000
  17.250   1.8111   0.05669   0.05144  -0.0416   0.0414   1.0000
  17.500   1.7963   0.06141   0.05620  -0.0419   0.0365   1.0000
  17.750   1.7788   0.06660   0.06144  -0.0425   0.0313   1.0000
  18.000   1.7577   0.07245   0.06735  -0.0434   0.0264   1.0000
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