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TRAINER60 (trainer60-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: TRAINER60 (trainer60-il)
Reynolds number: 50,000
Max Cl/Cd: 15.35 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-trainer60-il-50000.txt
Download as CSV file: xf-trainer60-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: TRAINER60                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.5183   0.14396   0.13549   0.0298   1.0000   0.4053
 -11.500  -0.4824   0.13776   0.12922   0.0289   1.0000   0.4165
 -11.250  -0.5175   0.13903   0.13053   0.0294   1.0000   0.4274
 -11.000  -0.4646   0.13173   0.12312   0.0280   1.0000   0.4407
 -10.750  -0.4838   0.13069   0.12211   0.0282   1.0000   0.4503
 -10.500  -0.4473   0.12594   0.11729   0.0272   1.0000   0.4639
 -10.250  -0.4571   0.12398   0.11533   0.0273   1.0000   0.4727
 -10.000  -0.4278   0.12008   0.11137   0.0264   1.0000   0.4853
  -9.750  -0.4405   0.11845   0.10976   0.0268   1.0000   0.4940
  -9.500  -0.4061   0.11416   0.10541   0.0255   1.0000   0.5046
  -9.250  -0.4378   0.11447   0.10577   0.0272   1.0000   0.5144
  -9.000  -0.3869   0.10851   0.09974   0.0247   1.0000   0.5230
  -8.750  -0.4052   0.10830   0.09956   0.0262   1.0000   0.5353
  -8.250  -0.4554   0.09242   0.08360   0.0165   1.0000   0.4466
  -8.000  -0.4454   0.08836   0.07952   0.0151   1.0000   0.4431
  -7.750  -0.4468   0.08409   0.07525   0.0136   1.0000   0.4402
  -7.500  -0.4539   0.07959   0.07076   0.0123   1.0000   0.4386
  -7.250  -0.4618   0.07529   0.06649   0.0112   1.0000   0.4405
  -7.000  -0.4811   0.07030   0.06155   0.0103   1.0000   0.4439
  -6.750  -0.5594   0.06053   0.05192   0.0093   1.0000   0.4477
  -6.500  -0.4987   0.06224   0.05361   0.0099   1.0000   0.4549
  -6.250  -0.5094   0.05879   0.05023   0.0107   1.0000   0.4631
  -6.000  -0.5815   0.05093   0.04247   0.0129   1.0000   0.4729
  -5.750  -0.5457   0.05183   0.04344   0.0143   1.0000   0.4804
  -5.500  -0.6405   0.04553   0.03712   0.0216   1.0000   0.4909
  -5.250  -0.6260   0.04601   0.03770   0.0245   1.0000   0.4975
  -5.000  -0.6364   0.04488   0.03656   0.0281   1.0000   0.5073
  -4.750  -0.6476   0.04320   0.03484   0.0312   1.0000   0.5183
  -4.500  -0.6421   0.04288   0.03453   0.0338   1.0000   0.5292
  -4.250  -0.6427   0.04172   0.03332   0.0361   1.0000   0.5414
  -4.000  -0.6213   0.04046   0.03193   0.0341   0.9943   0.5598
  -3.750  -0.5570   0.04149   0.03303   0.0295   0.9803   0.5750
  -3.500  -0.4980   0.04155   0.03304   0.0241   0.9669   0.5931
  -3.250  -0.4402   0.04134   0.03277   0.0185   0.9537   0.6125
  -3.000  -0.3991   0.04075   0.03208   0.0147   0.9388   0.6315
  -2.750  -0.3284   0.04151   0.03284   0.0091   0.9262   0.6480
  -2.500  -0.2624   0.04185   0.03317   0.0037   0.9134   0.6635
  -2.250  -0.2304   0.04145   0.03270   0.0017   0.8987   0.6801
  -2.000  -0.1815   0.04195   0.03320  -0.0007   0.8844   0.6943
  -1.750  -0.1506   0.04199   0.03323  -0.0011   0.8693   0.7078
  -1.500  -0.1472   0.04164   0.03284   0.0012   0.8545   0.7224
  -1.250  -0.1045   0.04210   0.03333  -0.0001   0.8412   0.7339
  -1.000  -0.0938   0.04158   0.03275   0.0013   0.8294   0.7485
  -0.750  -0.0526   0.04190   0.03310  -0.0001   0.8160   0.7591
  -0.500  -0.0576   0.04160   0.03278   0.0033   0.8043   0.7719
  -0.250  -0.0083   0.04168   0.03286   0.0006   0.7933   0.7829
   0.000  -0.0152   0.04169   0.03287   0.0043   0.7813   0.7951
   0.250   0.0303   0.04162   0.03279   0.0021   0.7709   0.8069
   0.500   0.0299   0.04195   0.03314   0.0048   0.7592   0.8186
   0.750   0.0524   0.04176   0.03293   0.0055   0.7491   0.8326
   1.000   0.0769   0.04227   0.03348   0.0050   0.7361   0.8440
   1.250   0.1205   0.04186   0.03306   0.0034   0.7247   0.8570
   1.500   0.1204   0.04238   0.03361   0.0060   0.7108   0.8714
   1.750   0.1802   0.04151   0.03270   0.0032   0.6992   0.8852
   2.000   0.1910   0.04217   0.03343   0.0036   0.6829   0.9001
   2.250   0.2343   0.04207   0.03335   0.0011   0.6685   0.9139
   2.500   0.3007   0.04133   0.03261  -0.0036   0.6535   0.9263
   2.750   0.3387   0.04187   0.03323  -0.0071   0.6355   0.9407
   3.000   0.4023   0.04193   0.03336  -0.0131   0.6174   0.9517
   3.250   0.4712   0.04113   0.03255  -0.0182   0.6010   0.9629
   3.500   0.5305   0.04077   0.03223  -0.0231   0.5827   0.9748
   3.750   0.5784   0.04126   0.03282  -0.0278   0.5624   0.9883
   4.000   0.6280   0.04160   0.03323  -0.0327   0.5428   0.9999
   4.250   0.6387   0.04161   0.03319  -0.0305   0.5317   1.0000
   4.500   0.6400   0.04240   0.03402  -0.0283   0.5183   1.0000
   4.750   0.6364   0.04351   0.03516  -0.0256   0.5068   1.0000
   5.000   0.6319   0.04426   0.03592  -0.0224   0.4963   1.0000
   5.250   0.6322   0.04455   0.03614  -0.0190   0.4885   1.0000
   5.500   0.5832   0.04843   0.04004  -0.0142   0.4769   1.0000
   5.750   0.6277   0.04638   0.03786  -0.0126   0.4700   1.0000
   6.000   0.5552   0.05467   0.04617  -0.0103   0.4561   1.0000
   6.250   0.6079   0.05257   0.04401  -0.0090   0.4492   1.0000
   6.500   0.5187   0.06403   0.05538  -0.0097   0.4397   1.0000
   6.750   0.5042   0.06858   0.05987  -0.0101   0.4328   1.0000
   7.000   0.5823   0.06508   0.05643  -0.0085   0.4245   1.0000
   7.250   0.5150   0.07524   0.06647  -0.0110   0.4220   1.0000
   7.500   0.4961   0.08097   0.07217  -0.0129   0.4207   1.0000
   7.750   0.4878   0.08585   0.07704  -0.0146   0.4204   1.0000
   8.000   0.4892   0.09033   0.08153  -0.0162   0.4221   1.0000
   8.250   0.5002   0.09472   0.08596  -0.0181   0.4265   1.0000
   8.500   0.2546   0.10300   0.09495  -0.0091   0.5201   1.0000
   8.750   0.3014   0.10869   0.10068  -0.0119   0.5134   1.0000
   9.000   0.2683   0.10852   0.10047  -0.0096   0.5034   1.0000
   9.250   0.2952   0.11213   0.10410  -0.0108   0.4938   1.0000
   9.500   0.2932   0.11478   0.10675  -0.0107   0.4872   1.0000
   9.750   0.2990   0.11683   0.10882  -0.0107   0.4751   1.0000
  10.000   0.3353   0.12268   0.11469  -0.0127   0.4684   1.0000
  10.250   0.3100   0.12205   0.11408  -0.0111   0.4561   1.0000
  10.500   0.3652   0.12974   0.12181  -0.0138   0.4471   1.0000
  10.750   0.3232   0.12737   0.11945  -0.0117   0.4364   1.0000
  11.000   0.3798   0.13555   0.12769  -0.0142   0.4253   1.0000
  11.250   0.3368   0.13264   0.12478  -0.0124   0.4152   1.0000
  11.500   0.3828   0.14023   0.13242  -0.0141   0.4035   1.0000
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