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J5012 12% (j5012-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: J5012 12% (j5012-il)
Reynolds number: 50,000
Max Cl/Cd: 28.21 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-j5012-il-50000-n5.txt
Download as CSV file: xf-j5012-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: J5012   12%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.6645   0.10268   0.09477  -0.0275   1.0000   0.0639
 -12.250  -0.7772   0.07862   0.07044  -0.0451   1.0000   0.0596
 -12.000  -0.8027   0.07301   0.06468  -0.0470   1.0000   0.0595
 -11.750  -0.8270   0.06831   0.05979  -0.0474   1.0000   0.0595
 -11.500  -0.8489   0.06434   0.05560  -0.0463   1.0000   0.0595
 -11.250  -0.8645   0.06098   0.05208  -0.0443   1.0000   0.0599
 -11.000  -0.8712   0.05818   0.04916  -0.0421   1.0000   0.0606
 -10.750  -0.8768   0.05564   0.04647  -0.0394   1.0000   0.0613
 -10.500  -0.8783   0.05329   0.04398  -0.0370   1.0000   0.0626
 -10.250  -0.8784   0.05106   0.04157  -0.0345   1.0000   0.0645
 -10.000  -0.8780   0.04873   0.03899  -0.0318   1.0000   0.0668
  -9.750  -0.8766   0.04624   0.03611  -0.0290   1.0000   0.0693
  -9.500  -0.8694   0.04382   0.03334  -0.0267   1.0000   0.0716
  -9.250  -0.8551   0.04195   0.03144  -0.0252   1.0000   0.0743
  -9.000  -0.8430   0.04027   0.02960  -0.0233   1.0000   0.0784
  -8.750  -0.8300   0.03842   0.02734  -0.0213   1.0000   0.0833
  -8.500  -0.8134   0.03687   0.02591  -0.0199   1.0000   0.0880
  -8.250  -0.7977   0.03540   0.02422  -0.0181   1.0000   0.0948
  -8.000  -0.7818   0.03401   0.02284  -0.0165   1.0000   0.1017
  -7.750  -0.7646   0.03269   0.02134  -0.0148   1.0000   0.1106
  -7.500  -0.7499   0.03150   0.02020  -0.0129   1.0000   0.1203
  -7.250  -0.7347   0.03031   0.01903  -0.0109   1.0000   0.1317
  -7.000  -0.7204   0.02920   0.01794  -0.0089   1.0000   0.1458
  -6.750  -0.7065   0.02813   0.01688  -0.0067   1.0000   0.1628
  -6.500  -0.6931   0.02709   0.01592  -0.0045   1.0000   0.1840
  -6.250  -0.6808   0.02608   0.01505  -0.0021   1.0000   0.2088
  -6.000  -0.6689   0.02513   0.01426   0.0004   1.0000   0.2390
  -5.750  -0.6576   0.02425   0.01357   0.0030   1.0000   0.2756
  -5.500  -0.6464   0.02345   0.01295   0.0058   1.0000   0.3177
  -5.250  -0.6352   0.02275   0.01246   0.0086   1.0000   0.3632
  -5.000  -0.6233   0.02214   0.01206   0.0115   1.0000   0.4112
  -4.750  -0.6106   0.02164   0.01176   0.0144   1.0000   0.4593
  -4.500  -0.5966   0.02125   0.01153   0.0173   1.0000   0.5065
  -4.250  -0.5814   0.02096   0.01135   0.0200   1.0000   0.5523
  -4.000  -0.5648   0.02076   0.01127   0.0227   1.0000   0.5958
  -3.750  -0.5466   0.02067   0.01127   0.0251   1.0000   0.6364
  -3.500  -0.5285   0.02064   0.01126   0.0276   1.0000   0.6750
  -3.250  -0.5071   0.02071   0.01135   0.0296   1.0000   0.7106
  -3.000  -0.4843   0.02085   0.01147   0.0312   1.0000   0.7436
  -2.750  -0.4598   0.02103   0.01162   0.0326   1.0000   0.7743
  -2.500  -0.4339   0.02124   0.01175   0.0335   1.0000   0.8029
  -2.250  -0.4045   0.02150   0.01193   0.0337   1.0000   0.8292
  -2.000  -0.3698   0.02182   0.01215   0.0328   1.0000   0.8525
  -1.750  -0.3347   0.02210   0.01233   0.0315   1.0000   0.8747
  -1.500  -0.2978   0.02237   0.01250   0.0297   1.0000   0.8951
  -1.250  -0.2531   0.02266   0.01268   0.0262   1.0000   0.9121
  -1.000  -0.2089   0.02289   0.01282   0.0226   1.0000   0.9283
  -0.750  -0.1657   0.02307   0.01294   0.0189   1.0000   0.9444
  -0.500  -0.1187   0.02322   0.01303   0.0142   0.9978   0.9589
  -0.250  -0.0605   0.02335   0.01312   0.0074   0.9889   0.9702
   0.000   0.0000   0.02339   0.01314   0.0000   0.9800   0.9800
   0.250   0.0605   0.02335   0.01311  -0.0073   0.9702   0.9889
   0.500   0.1185   0.02322   0.01303  -0.0142   0.9590   0.9978
   0.750   0.1657   0.02307   0.01293  -0.0189   0.9444   1.0000
   1.000   0.2089   0.02288   0.01281  -0.0226   0.9283   1.0000
   1.250   0.2531   0.02265   0.01267  -0.0262   0.9121   1.0000
   1.500   0.2976   0.02237   0.01250  -0.0297   0.8951   1.0000
   1.750   0.3347   0.02210   0.01232  -0.0315   0.8747   1.0000
   2.000   0.3697   0.02182   0.01215  -0.0328   0.8526   1.0000
   2.250   0.4045   0.02150   0.01193  -0.0337   0.8293   1.0000
   2.500   0.4338   0.02124   0.01174  -0.0335   0.8029   1.0000
   2.750   0.4598   0.02103   0.01161  -0.0326   0.7743   1.0000
   3.000   0.4843   0.02085   0.01147  -0.0312   0.7435   1.0000
   3.250   0.5071   0.02071   0.01135  -0.0296   0.7106   1.0000
   3.500   0.5286   0.02063   0.01126  -0.0276   0.6753   1.0000
   3.750   0.5466   0.02067   0.01126  -0.0251   0.6365   1.0000
   4.000   0.5648   0.02076   0.01127  -0.0227   0.5959   1.0000
   4.250   0.5814   0.02095   0.01135  -0.0200   0.5524   1.0000
   4.500   0.5965   0.02125   0.01153  -0.0173   0.5066   1.0000
   4.750   0.6105   0.02164   0.01175  -0.0144   0.4592   1.0000
   5.000   0.6233   0.02214   0.01206  -0.0115   0.4111   1.0000
   5.250   0.6352   0.02274   0.01246  -0.0086   0.3632   1.0000
   5.500   0.6464   0.02345   0.01295  -0.0058   0.3173   1.0000
   5.750   0.6576   0.02425   0.01357  -0.0030   0.2755   1.0000
   6.000   0.6690   0.02513   0.01426  -0.0004   0.2393   1.0000
   6.250   0.6808   0.02608   0.01505   0.0021   0.2088   1.0000
   6.500   0.6930   0.02709   0.01592   0.0045   0.1838   1.0000
   6.750   0.7065   0.02812   0.01688   0.0067   0.1629   1.0000
   7.000   0.7204   0.02920   0.01794   0.0089   0.1458   1.0000
   7.250   0.7348   0.03031   0.01903   0.0109   0.1317   1.0000
   7.500   0.7499   0.03149   0.02020   0.0129   0.1202   1.0000
   7.750   0.7646   0.03269   0.02134   0.0148   0.1106   1.0000
   8.000   0.7816   0.03400   0.02283   0.0165   0.1015   1.0000
   8.250   0.7975   0.03539   0.02422   0.0182   0.0946   1.0000
   8.500   0.8134   0.03686   0.02590   0.0199   0.0880   1.0000
   8.750   0.8300   0.03842   0.02734   0.0213   0.0833   1.0000
   9.000   0.8429   0.04027   0.02961   0.0233   0.0783   1.0000
   9.250   0.8552   0.04196   0.03144   0.0252   0.0743   1.0000
   9.500   0.8696   0.04382   0.03333   0.0267   0.0715   1.0000
   9.750   0.8758   0.04626   0.03615   0.0291   0.0690   1.0000
  10.000   0.8778   0.04871   0.03896   0.0318   0.0666   1.0000
  10.250   0.8785   0.05104   0.04154   0.0345   0.0644   1.0000
  10.500   0.8785   0.05330   0.04399   0.0369   0.0626   1.0000
  10.750   0.8774   0.05562   0.04644   0.0394   0.0612   1.0000
  11.000   0.8727   0.05817   0.04912   0.0419   0.0604   1.0000
  11.250   0.8657   0.06098   0.05206   0.0442   0.0598   1.0000
  11.500   0.8487   0.06438   0.05565   0.0463   0.0595   1.0000
  11.750   0.8278   0.06828   0.05976   0.0473   0.0595   1.0000
  12.000   0.8038   0.07297   0.06464   0.0469   0.0595   1.0000
  12.250   0.7774   0.07867   0.07049   0.0449   0.0596   1.0000
  12.500   0.6664   0.10240   0.09448   0.0276   0.0636   1.0000
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