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NACA 24112 (naca24112-jf) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 24112 (naca24112-jf)
Reynolds number: 50,000
Max Cl/Cd: 19.92 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca24112-jf-50000.txt
Download as CSV file: xf-naca24112-jf-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 24112                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4616   0.10048   0.09373   0.0186   1.0000   0.3703
  -8.250  -0.4610   0.09799   0.09132   0.0202   1.0000   0.3983
  -8.000  -0.4659   0.09643   0.08984   0.0223   1.0000   0.4285
  -7.750  -0.4419   0.09281   0.08624   0.0247   1.0000   0.4628
  -7.500  -0.4055   0.08898   0.08236   0.0270   1.0000   0.5047
  -7.250  -0.3900   0.08628   0.07970   0.0296   1.0000   0.5482
  -7.000  -0.3650   0.08308   0.07650   0.0311   1.0000   0.5896
  -6.750  -0.3625   0.08137   0.07486   0.0341   1.0000   0.6279
  -6.000  -0.5351   0.05131   0.04376  -0.0092   1.0000   0.2097
  -5.750  -0.5243   0.04707   0.03876  -0.0081   1.0000   0.1821
  -5.500  -0.5080   0.04417   0.03558  -0.0065   1.0000   0.1759
  -5.250  -0.4927   0.04125   0.03237  -0.0048   1.0000   0.1710
  -5.000  -0.4771   0.03945   0.02971  -0.0022   1.0000   0.1631
  -4.750  -0.4596   0.03715   0.02713  -0.0005   1.0000   0.1632
  -4.500  -0.4413   0.03464   0.02462   0.0008   1.0000   0.1663
  -4.250  -0.4221   0.03282   0.02260   0.0023   1.0000   0.1682
  -4.000  -0.4024   0.03123   0.02083   0.0038   1.0000   0.1711
  -3.750  -0.3830   0.02999   0.01933   0.0053   1.0000   0.1766
  -3.500  -0.3626   0.02875   0.01786   0.0066   1.0000   0.1811
  -3.250  -0.3412   0.02745   0.01666   0.0075   1.0000   0.1892
  -3.000  -0.3195   0.02658   0.01568   0.0084   1.0000   0.1985
  -2.500   0.0056   0.02103   0.01295  -0.0257   1.0000   1.0000
  -2.000  -0.0164   0.02162   0.01354  -0.0172   1.0000   1.0000
  -1.750  -0.0466   0.02240   0.01436  -0.0111   1.0000   1.0000
  -1.500   0.0398   0.02264   0.01422  -0.0240   0.9723   1.0000
  -1.250   0.1485   0.02226   0.01352  -0.0396   0.9396   1.0000
  -1.000   0.2179   0.02188   0.01292  -0.0471   0.8986   1.0000
  -0.750   0.2579   0.02171   0.01256  -0.0486   0.8597   1.0000
  -0.500   0.2824   0.02177   0.01243  -0.0472   0.8253   1.0000
  -0.250   0.3024   0.02195   0.01243  -0.0451   0.7943   1.0000
   0.000   0.3220   0.02216   0.01247  -0.0431   0.7678   1.0000
   0.250   0.3416   0.02247   0.01263  -0.0413   0.7431   1.0000
   0.500   0.3616   0.02275   0.01275  -0.0394   0.7220   1.0000
   0.750   0.3824   0.02314   0.01300  -0.0380   0.7021   1.0000
   1.000   0.4032   0.02360   0.01337  -0.0367   0.6832   1.0000
   1.250   0.4240   0.02408   0.01375  -0.0354   0.6660   1.0000
   1.500   0.4449   0.02458   0.01414  -0.0341   0.6505   1.0000
   1.750   0.4661   0.02506   0.01452  -0.0327   0.6364   1.0000
   2.000   0.4866   0.02573   0.01516  -0.0318   0.6215   1.0000
   2.250   0.5069   0.02648   0.01589  -0.0308   0.6077   1.0000
   2.500   0.5270   0.02726   0.01665  -0.0298   0.5951   1.0000
   2.750   0.5481   0.02788   0.01719  -0.0285   0.5840   1.0000
   3.000   0.5679   0.02873   0.01807  -0.0274   0.5721   1.0000
   3.250   0.5862   0.02982   0.01920  -0.0266   0.5604   1.0000
   3.500   0.6075   0.03050   0.01982  -0.0252   0.5509   1.0000
   3.750   0.6247   0.03171   0.02111  -0.0243   0.5397   1.0000
   4.000   0.6418   0.03298   0.02244  -0.0232   0.5296   1.0000
   4.250   0.6629   0.03375   0.02318  -0.0219   0.5205   1.0000
   4.500   0.6750   0.03562   0.02519  -0.0210   0.5102   1.0000
   4.750   0.6996   0.03609   0.02560  -0.0195   0.5024   1.0000
   5.000   0.7053   0.03859   0.02830  -0.0186   0.4917   1.0000
   5.250   0.7248   0.03969   0.02940  -0.0173   0.4838   1.0000
   5.500   0.7300   0.04225   0.03211  -0.0163   0.4742   1.0000
   5.750   0.7446   0.04389   0.03380  -0.0150   0.4661   1.0000
   6.000   0.7458   0.04693   0.03698  -0.0140   0.4573   1.0000
   6.250   0.7580   0.04895   0.03905  -0.0129   0.4497   1.0000
   6.500   0.7425   0.05378   0.04400  -0.0126   0.4416   1.0000
   6.750   0.7631   0.05505   0.04531  -0.0113   0.4341   1.0000
   7.000   0.7056   0.06452   0.05479  -0.0134   0.4306   1.0000
   7.250   0.6709   0.07105   0.06127  -0.0144   0.4290   1.0000
   7.500   0.6537   0.07624   0.06643  -0.0155   0.4284   1.0000
   7.750   0.6427   0.08126   0.07146  -0.0168   0.4310   1.0000
   8.000   0.6413   0.08572   0.07597  -0.0179   0.4334   1.0000
   8.250   0.6549   0.08982   0.08014  -0.0190   0.4359   1.0000
   9.750   0.5986   0.11591   0.10638  -0.0273   0.4729   1.0000
  10.750   0.6222   0.12788   0.11852  -0.0271   0.4258   1.0000
  11.000   0.6360   0.13194   0.12266  -0.0275   0.4171   1.0000
  11.250   0.6681   0.13711   0.12796  -0.0278   0.4030   1.0000
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