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GOE 679 AIRFOIL (goe679-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 679 AIRFOIL (goe679-il)
Reynolds number: 50,000
Max Cl/Cd: 25.15 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe679-il-50000-n5.txt
Download as CSV file: xf-goe679-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 679 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3888   0.10413   0.09685  -0.0410   1.0000   0.0931
  -9.500  -0.4160   0.09898   0.09179  -0.0413   1.0000   0.0934
  -9.250  -0.4657   0.08892   0.08180  -0.0456   0.9984   0.0939
  -9.000  -0.5682   0.06941   0.06195  -0.0598   0.9837   0.0938
  -8.750  -0.6006   0.06205   0.05421  -0.0624   0.9721   0.0947
  -8.500  -0.5777   0.06134   0.05354  -0.0632   0.9651   0.0969
  -8.250  -0.5773   0.05751   0.04943  -0.0643   0.9559   0.0994
  -8.000  -0.5851   0.05291   0.04433  -0.0638   0.9455   0.1020
  -7.750  -0.5699   0.05065   0.04187  -0.0642   0.9376   0.1049
  -7.500  -0.5516   0.04917   0.04029  -0.0641   0.9291   0.1080
  -7.250  -0.5429   0.04611   0.03668  -0.0635   0.9201   0.1132
  -7.000  -0.5144   0.04570   0.03641  -0.0641   0.9124   0.1174
  -6.750  -0.5012   0.04363   0.03392  -0.0631   0.9029   0.1242
  -6.500  -0.4707   0.04319   0.03359  -0.0640   0.8955   0.1301
  -6.250  -0.4545   0.04196   0.03212  -0.0628   0.8854   0.1378
  -6.000  -0.4249   0.04090   0.03084  -0.0637   0.8783   0.1481
  -5.750  -0.4058   0.04061   0.03064  -0.0624   0.8675   0.1551
  -5.500  -0.3737   0.03978   0.02965  -0.0634   0.8606   0.1667
  -5.250  -0.3574   0.03922   0.02889  -0.0618   0.8494   0.1770
  -5.000  -0.3227   0.03884   0.02858  -0.0629   0.8426   0.1882
  -4.750  -0.3058   0.03839   0.02800  -0.0612   0.8312   0.1977
  -4.500  -0.2725   0.03773   0.02714  -0.0620   0.8243   0.2106
  -4.250  -0.2531   0.03750   0.02700  -0.0606   0.8132   0.2184
  -3.750  -0.1975   0.03631   0.02560  -0.0603   0.7957   0.2373
  -3.500  -0.1673   0.03561   0.02468  -0.0605   0.7874   0.2475
  -3.250  -0.1257   0.03467   0.02373  -0.0622   0.7828   0.2570
  -3.000  -0.1120   0.03452   0.02348  -0.0599   0.7689   0.2643
  -2.750  -0.0713   0.03361   0.02247  -0.0615   0.7636   0.2746
  -2.500  -0.0551   0.03350   0.02233  -0.0595   0.7504   0.2822
  -2.250  -0.0147   0.03267   0.02136  -0.0610   0.7442   0.2937
  -2.000   0.0053   0.03253   0.02122  -0.0596   0.7319   0.3025
  -1.750   0.0444   0.03184   0.02043  -0.0610   0.7248   0.3153
  -1.500   0.0697   0.03162   0.02020  -0.0603   0.7137   0.3270
  -1.250   0.1070   0.03106   0.01962  -0.0615   0.7052   0.3414
  -1.000   0.1357   0.03078   0.01927  -0.0613   0.6951   0.3571
  -0.750   0.1665   0.03040   0.01892  -0.0615   0.6854   0.3750
  -0.500   0.1971   0.03003   0.01860  -0.0616   0.6761   0.3945
  -0.250   0.2239   0.02976   0.01840  -0.0611   0.6655   0.4175
   0.000   0.2535   0.02941   0.01815  -0.0610   0.6564   0.4462
   0.250   0.2768   0.02917   0.01810  -0.0599   0.6460   0.4808
   0.500   0.3050   0.02872   0.01790  -0.0594   0.6371   0.5355
   0.750   0.3263   0.02840   0.01803  -0.0577   0.6267   0.6204
   1.000   0.4717   0.02774   0.01801  -0.0772   0.6170   0.9277
   1.250   0.5543   0.02792   0.01790  -0.0873   0.6055   1.0000
   1.500   0.5664   0.02819   0.01799  -0.0847   0.5953   1.0000
   1.750   0.5884   0.02827   0.01786  -0.0835   0.5860   1.0000
   2.000   0.6013   0.02859   0.01802  -0.0810   0.5762   1.0000
   2.250   0.6228   0.02875   0.01800  -0.0797   0.5671   1.0000
   2.500   0.6397   0.02905   0.01815  -0.0778   0.5581   1.0000
   2.750   0.6558   0.02936   0.01832  -0.0757   0.5488   1.0000
   3.000   0.6810   0.02954   0.01833  -0.0751   0.5406   1.0000
   3.250   0.6879   0.03009   0.01880  -0.0715   0.5313   1.0000
   3.500   0.7283   0.03001   0.01849  -0.0733   0.5239   1.0000
   3.750   0.7205   0.03088   0.01937  -0.0675   0.5143   1.0000
   4.000   0.7517   0.03099   0.01931  -0.0678   0.5066   1.0000
   4.250   0.7569   0.03168   0.01997  -0.0642   0.4982   1.0000
   4.500   0.7728   0.03215   0.02034  -0.0622   0.4900   1.0000
   4.750   0.8025   0.03234   0.02038  -0.0623   0.4828   1.0000
   5.000   0.7978   0.03334   0.02142  -0.0573   0.4741   1.0000
   5.250   0.8280   0.03351   0.02145  -0.0575   0.4672   1.0000
   5.500   0.8321   0.03440   0.02234  -0.0540   0.4594   1.0000
   5.750   0.8410   0.03516   0.02307  -0.0512   0.4515   1.0000
   6.000   0.8816   0.03506   0.02279  -0.0528   0.4454   1.0000
   6.250   0.8634   0.03672   0.02457  -0.0466   0.4370   1.0000
   6.500   0.8809   0.03731   0.02511  -0.0451   0.4301   1.0000
   6.750   0.9115   0.03747   0.02515  -0.0452   0.4241   1.0000
   7.000   0.8912   0.03950   0.02731  -0.0395   0.4157   1.0000
   7.250   0.9145   0.03987   0.02761  -0.0388   0.4094   1.0000
   7.500   0.9311   0.04060   0.02829  -0.0374   0.4034   1.0000
   7.750   0.9089   0.04312   0.03095  -0.0323   0.3952   1.0000
   8.000   0.9361   0.04329   0.03105  -0.0319   0.3896   1.0000
   8.250   0.9381   0.04483   0.03261  -0.0294   0.3833   1.0000
   8.500   0.9080   0.04840   0.03632  -0.0250   0.3748   1.0000
   8.750   0.9401   0.04820   0.03604  -0.0248   0.3703   1.0000
   9.000   0.8828   0.05447   0.04251  -0.0202   0.3602   1.0000
   9.250   0.8848   0.05656   0.04462  -0.0188   0.3539   1.0000
   9.500   0.9250   0.05539   0.04337  -0.0186   0.3510   1.0000
  10.000   0.8038   0.07337   0.06167  -0.0162   0.3273   1.0000
  10.250   0.8948   0.06565   0.05379  -0.0147   0.3315   1.0000
  10.750   0.8339   0.07863   0.06693  -0.0145   0.3139   1.0000
  11.250   0.7820   0.09272   0.08118  -0.0165   0.2973   1.0000
  11.750   0.7409   0.10556   0.09413  -0.0190   0.2827   1.0000
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