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GOE 479 AIRFOIL (goe479-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 479 AIRFOIL (goe479-il)
Reynolds number: 50,000
Max Cl/Cd: 31.56 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe479-il-50000.txt
Download as CSV file: xf-goe479-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 479 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3371   0.11635   0.10904  -0.0305   1.0000   0.2280
  -9.250  -0.3146   0.11080   0.10348  -0.0290   1.0000   0.2342
  -9.000  -0.3208   0.10945   0.10223  -0.0285   1.0000   0.2435
  -8.750  -0.3201   0.10643   0.09929  -0.0278   1.0000   0.2492
  -8.500  -0.3162   0.10405   0.09696  -0.0265   1.0000   0.2593
  -8.250  -0.3578   0.10577   0.09893  -0.0255   1.0000   0.2631
  -8.000  -0.3162   0.09914   0.09222  -0.0239   1.0000   0.2744
  -7.750  -0.3597   0.10070   0.09404  -0.0216   1.0000   0.2802
  -7.500  -0.3241   0.09494   0.08822  -0.0203   1.0000   0.2907
  -7.250  -0.3680   0.09621   0.08974  -0.0166   1.0000   0.2971
  -7.000  -0.3393   0.09138   0.08489  -0.0153   1.0000   0.3082
  -6.750  -0.3855   0.09249   0.08624  -0.0106   1.0000   0.3141
  -6.500  -0.3664   0.08868   0.08244  -0.0085   1.0000   0.3275
  -6.250  -0.4210   0.08997   0.08399  -0.0052   1.0000   0.3322
  -6.000  -0.4068   0.08671   0.08076  -0.0014   1.0000   0.3478
  -5.750  -0.4018   0.08410   0.07821   0.0019   1.0000   0.3611
  -5.500  -0.4114   0.08236   0.07657   0.0053   1.0000   0.3748
  -5.250  -0.4252   0.08087   0.07518   0.0086   1.0000   0.3895
  -5.000  -0.4326   0.07913   0.07353   0.0121   1.0000   0.4072
  -4.750  -0.4375   0.07734   0.07181   0.0157   1.0000   0.4261
  -4.500  -0.4429   0.07570   0.07024   0.0195   1.0000   0.4481
  -4.250  -0.4503   0.07399   0.06862   0.0238   1.0000   0.4757
  -3.750  -0.3812   0.05054   0.04296  -0.0298   1.0000   0.1954
  -3.500  -0.3639   0.04786   0.04015  -0.0298   1.0000   0.1912
  -3.250  -0.3442   0.04495   0.03691  -0.0305   1.0000   0.1853
  -3.000  -0.3184   0.04181   0.03286  -0.0320   1.0000   0.1770
  -2.750  -0.2984   0.03998   0.03065  -0.0319   1.0000   0.1771
  -2.500  -0.2801   0.03845   0.02896  -0.0315   1.0000   0.1799
  -2.250  -0.2616   0.03731   0.02769  -0.0310   1.0000   0.1835
  -2.000  -0.2277   0.03622   0.02624  -0.0329   0.9950   0.1872
  -1.750  -0.1807   0.03547   0.02504  -0.0370   0.9840   0.1973
  -1.500  -0.1367   0.03495   0.02427  -0.0405   0.9724   0.2100
  -1.250  -0.0962   0.03452   0.02372  -0.0433   0.9607   0.2291
  -1.000  -0.0575   0.03411   0.02339  -0.0457   0.9491   0.2551
  -0.750  -0.0098   0.03364   0.02302  -0.0494   0.9380   0.3131
  -0.500   0.0540   0.03019   0.02238  -0.0546   0.9291   1.0000
  -0.250   0.0919   0.03102   0.02248  -0.0571   0.9159   1.0000
   0.000   0.1286   0.03185   0.02291  -0.0594   0.9029   1.0000
   0.250   0.1697   0.03271   0.02345  -0.0623   0.8909   1.0000
   0.500   0.2016   0.03345   0.02396  -0.0638   0.8776   1.0000
   0.750   0.2277   0.03422   0.02453  -0.0643   0.8642   1.0000
   1.000   0.2563   0.03503   0.02518  -0.0652   0.8515   1.0000
   1.250   0.2909   0.03582   0.02581  -0.0668   0.8395   1.0000
   1.500   0.3263   0.03657   0.02643  -0.0686   0.8276   1.0000
   1.750   0.3457   0.03746   0.02723  -0.0680   0.8144   1.0000
   2.000   0.3691   0.03837   0.02805  -0.0680   0.8021   1.0000
   2.250   0.4031   0.03913   0.02873  -0.0693   0.7907   1.0000
   2.500   0.4339   0.03989   0.02943  -0.0701   0.7788   1.0000
   2.750   0.4500   0.04095   0.03045  -0.0691   0.7657   1.0000
   3.000   0.4723   0.04193   0.03139  -0.0688   0.7534   1.0000
   3.250   0.5088   0.04251   0.03195  -0.0700   0.7418   1.0000
   3.500   0.5385   0.04317   0.03260  -0.0703   0.7291   1.0000
   3.750   0.5527   0.04434   0.03376  -0.0690   0.7151   1.0000
   4.000   0.5718   0.04541   0.03482  -0.0681   0.7017   1.0000
   4.250   0.5998   0.04611   0.03555  -0.0680   0.6886   1.0000
   4.500   0.6521   0.04569   0.03519  -0.0698   0.6775   1.0000
   4.750   0.6603   0.04720   0.03672  -0.0679   0.6628   1.0000
   5.000   0.6720   0.04862   0.03816  -0.0664   0.6483   1.0000
   5.250   0.6873   0.04994   0.03953  -0.0652   0.6343   1.0000
   5.500   0.7115   0.05076   0.04041  -0.0645   0.6208   1.0000
   5.750   0.7742   0.04910   0.03889  -0.0658   0.6105   1.0000
   6.000   0.7776   0.05111   0.04094  -0.0637   0.5952   1.0000
   6.250   0.7827   0.05311   0.04298  -0.0619   0.5801   1.0000
   6.500   0.7883   0.05523   0.04515  -0.0603   0.5655   1.0000
   6.750   0.7976   0.05712   0.04709  -0.0589   0.5515   1.0000
   7.000   0.8188   0.05816   0.04824  -0.0579   0.5389   1.0000
   7.250   0.8696   0.05664   0.04688  -0.0574   0.5287   1.0000
   7.500   0.8499   0.06123   0.05147  -0.0557   0.5142   1.0000
   7.750   0.8340   0.06568   0.05593  -0.0545   0.5013   1.0000
   8.000   0.8451   0.06790   0.05823  -0.0537   0.4908   1.0000
   8.250   0.8734   0.06847   0.05894  -0.0529   0.4806   1.0000
   8.750   1.1230   0.04865   0.03986  -0.0527   0.4471   1.0000
   9.250   1.2218   0.04150   0.03272  -0.0502   0.3941   1.0000
   9.500   1.2360   0.04125   0.03255  -0.0472   0.3730   1.0000
   9.750   1.2612   0.03996   0.03119  -0.0448   0.3472   1.0000
  10.000   1.2614   0.04008   0.03137  -0.0402   0.3218   1.0000
  10.250   1.2555   0.04032   0.03151  -0.0349   0.2931   1.0000
  10.500   1.2460   0.04111   0.03198  -0.0294   0.2596   1.0000
  10.750   1.2409   0.04283   0.03318  -0.0252   0.2246   1.0000
  11.000   1.2367   0.04529   0.03556  -0.0219   0.2013   1.0000
  11.250   1.2452   0.04738   0.03746  -0.0199   0.1834   1.0000
  11.500   1.2528   0.04969   0.03980  -0.0181   0.1710   1.0000
  11.750   1.2671   0.05204   0.04219  -0.0169   0.1611   1.0000
  12.000   1.3000   0.05411   0.04409  -0.0171   0.1516   1.0000
  12.250   1.2927   0.05729   0.04766  -0.0148   0.1482   1.0000
  12.500   1.2903   0.06038   0.05102  -0.0130   0.1442   1.0000
  12.750   1.3189   0.06267   0.05319  -0.0130   0.1379   1.0000
  13.000   1.3015   0.06661   0.05750  -0.0109   0.1368   1.0000
  13.250   1.2804   0.07115   0.06237  -0.0095   0.1362   1.0000
  13.500   1.2538   0.07647   0.06798  -0.0089   0.1360   1.0000
  13.750   1.2211   0.08288   0.07465  -0.0095   0.1364   1.0000
  14.000   1.1826   0.09072   0.08271  -0.0116   0.1372   1.0000
  14.250   1.1417   0.10009   0.09224  -0.0152   0.1382   1.0000
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