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GOE 391 AIRFOIL (goe391-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 391 AIRFOIL (goe391-il)
Reynolds number: 100,000
Max Cl/Cd: 58.35 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe391-il-100000-n5.txt
Download as CSV file: xf-goe391-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 391 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4075   0.09516   0.09027  -0.0229   1.0000   0.0267
  -7.500  -0.4102   0.09287   0.08805  -0.0223   1.0000   0.0268
  -7.250  -0.4133   0.09038   0.08564  -0.0218   1.0000   0.0274
  -7.000  -0.4132   0.08769   0.08302  -0.0221   1.0000   0.0277
  -6.750  -0.4123   0.08498   0.08035  -0.0226   1.0000   0.0280
  -6.500  -0.4104   0.08220   0.07761  -0.0232   1.0000   0.0284
  -6.250  -0.4070   0.07939   0.07483  -0.0239   1.0000   0.0287
  -6.000  -0.4023   0.07641   0.07186  -0.0248   1.0000   0.0292
  -5.750  -0.3958   0.07334   0.06879  -0.0258   1.0000   0.0296
  -5.500  -0.3866   0.07020   0.06564  -0.0273   1.0000   0.0312
  -5.250  -0.3664   0.06732   0.06262  -0.0317   1.0000   0.0337
  -5.000  -0.3461   0.06438   0.05951  -0.0345   1.0000   0.0342
  -4.750  -0.3276   0.06128   0.05621  -0.0360   1.0000   0.0344
  -4.500  -0.3145   0.05714   0.05201  -0.0363   1.0000   0.0348
  -4.250  -0.3065   0.05306   0.04794  -0.0356   1.0000   0.0356
  -4.000  -0.2926   0.04975   0.04457  -0.0354   1.0000   0.0367
  -3.750  -0.2734   0.04659   0.04125  -0.0359   1.0000   0.0373
  -3.500  -0.2445   0.04257   0.03697  -0.0377   0.9984   0.0295
  -3.250  -0.1971   0.03752   0.03123  -0.0410   0.9952   0.0244
  -3.000  -0.1693   0.03464   0.02824  -0.0435   0.9912   0.0270
  -2.750  -0.1334   0.03186   0.02508  -0.0456   0.9878   0.0301
  -2.500  -0.0989   0.02884   0.02156  -0.0469   0.9841   0.0298
  -2.250  -0.0638   0.02611   0.01827  -0.0479   0.9808   0.0306
  -2.000  -0.0270   0.02404   0.01550  -0.0489   0.9780   0.0351
  -1.750   0.0033   0.02221   0.01341  -0.0496   0.9738   0.0378
  -1.500   0.0370   0.02108   0.01189  -0.0504   0.9700   0.0439
  -1.250   0.0717   0.01965   0.01018  -0.0517   0.9673   0.0482
  -1.000   0.1007   0.01892   0.00933  -0.0520   0.9619   0.0540
  -0.750   0.1339   0.01829   0.00852  -0.0530   0.9576   0.0579
  -0.500   0.1671   0.01763   0.00778  -0.0541   0.9537   0.0585
  -0.250   0.1951   0.01710   0.00721  -0.0542   0.9475   0.0597
   0.000   0.2294   0.01671   0.00676  -0.0555   0.9430   0.0624
   0.250   0.2602   0.01648   0.00645  -0.0562   0.9367   0.0679
   0.500   0.2957   0.01621   0.00614  -0.0577   0.9303   0.0827
   0.750   0.3499   0.01392   0.00607  -0.0634   0.9293   1.0000
   1.000   0.3823   0.01391   0.00593  -0.0642   0.9197   1.0000
   1.250   0.4212   0.01385   0.00578  -0.0664   0.9126   1.0000
   1.500   0.4542   0.01379   0.00569  -0.0672   0.9027   1.0000
   1.750   0.4864   0.01374   0.00564  -0.0679   0.8923   1.0000
   2.000   0.5204   0.01360   0.00552  -0.0688   0.8805   1.0000
   2.250   0.5531   0.01346   0.00542  -0.0694   0.8675   1.0000
   2.500   0.5842   0.01334   0.00535  -0.0696   0.8530   1.0000
   2.750   0.6150   0.01322   0.00534  -0.0697   0.8366   1.0000
   3.000   0.6468   0.01310   0.00530  -0.0700   0.8191   1.0000
   3.250   0.6763   0.01296   0.00525  -0.0696   0.7917   1.0000
   3.500   0.7060   0.01279   0.00511  -0.0690   0.7442   1.0000
   3.750   0.7373   0.01276   0.00496  -0.0687   0.6793   1.0000
   4.000   0.7644   0.01310   0.00493  -0.0677   0.5910   1.0000
   4.250   0.7815   0.01394   0.00516  -0.0652   0.4637   1.0000
   4.500   0.7958   0.01504   0.00563  -0.0627   0.3428   1.0000
   4.750   0.8136   0.01599   0.00623  -0.0610   0.2600   1.0000
   5.000   0.8303   0.01716   0.00691  -0.0593   0.1624   1.0000
   5.250   0.8477   0.01839   0.00777  -0.0577   0.0901   1.0000
   5.500   0.8666   0.01946   0.00877  -0.0561   0.0715   1.0000
   5.750   0.8864   0.02038   0.00990  -0.0546   0.0649   1.0000
   6.000   0.9052   0.02142   0.01107  -0.0530   0.0576   1.0000
   6.250   0.9242   0.02243   0.01221  -0.0515   0.0485   1.0000
   6.500   0.9408   0.02390   0.01378  -0.0497   0.0410   1.0000
   6.750   0.9564   0.02580   0.01564  -0.0480   0.0337   1.0000
   7.000   0.9774   0.02736   0.01751  -0.0465   0.0283   1.0000
   7.250   0.9961   0.02950   0.01976  -0.0453   0.0241   1.0000
   7.500   1.0183   0.03212   0.02272  -0.0441   0.0221   1.0000
   7.750   1.0387   0.03448   0.02557  -0.0425   0.0192   1.0000
   8.000   1.0559   0.03724   0.02878  -0.0407   0.0175   1.0000
   8.250   1.0692   0.04051   0.03253  -0.0385   0.0166   1.0000
   8.500   1.0784   0.04396   0.03647  -0.0360   0.0161   1.0000
   8.750   1.0832   0.04763   0.04060  -0.0332   0.0157   1.0000
   9.000   1.0842   0.05129   0.04469  -0.0304   0.0155   1.0000
   9.250   1.0824   0.05462   0.04835  -0.0276   0.0149   1.0000
   9.500   1.0760   0.05820   0.05226  -0.0248   0.0148   1.0000
   9.750   1.0669   0.06112   0.05538  -0.0219   0.0143   1.0000
  10.000   1.0531   0.06415   0.05857  -0.0191   0.0138   1.0000
  10.250   1.0332   0.06859   0.06332  -0.0168   0.0144   1.0000
  10.500   1.0151   0.07280   0.06771  -0.0163   0.0144   1.0000
  10.750   0.9833   0.08069   0.07588  -0.0188   0.0155   1.0000
  11.000   0.9574   0.08943   0.08475  -0.0243   0.0164   1.0000
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