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ULTIMATE (ultimate-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: ULTIMATE (ultimate-il)
Reynolds number: 50,000
Max Cl/Cd: 27.54 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ultimate-il-50000-n5.txt
Download as CSV file: xf-ultimate-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ULTIMATE                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.7467   0.11642   0.10925  -0.0052   1.0000   0.0496
 -13.000  -0.7642   0.10783   0.10066  -0.0103   1.0000   0.0493
 -12.750  -0.7838   0.09958   0.09235  -0.0154   1.0000   0.0489
 -12.500  -0.8063   0.09172   0.08439  -0.0203   1.0000   0.0485
 -12.250  -0.8291   0.08474   0.07727  -0.0243   1.0000   0.0481
 -12.000  -0.8520   0.07863   0.07098  -0.0272   1.0000   0.0479
 -11.750  -0.8730   0.07344   0.06557  -0.0287   1.0000   0.0478
 -11.500  -0.8924   0.06897   0.06085  -0.0289   1.0000   0.0479
 -11.250  -0.9098   0.06511   0.05670  -0.0279   1.0000   0.0482
 -11.000  -0.9243   0.06172   0.05299  -0.0258   1.0000   0.0486
 -10.750  -0.9359   0.05872   0.04963  -0.0229   1.0000   0.0491
 -10.500  -0.9394   0.05561   0.04621  -0.0205   1.0000   0.0499
 -10.250  -0.9310   0.05258   0.04301  -0.0193   1.0000   0.0510
  -9.750  -0.9086   0.04741   0.03738  -0.0166   1.0000   0.0540
  -9.500  -0.8953   0.04516   0.03486  -0.0153   1.0000   0.0568
  -9.250  -0.8792   0.04296   0.03226  -0.0140   1.0000   0.0600
  -9.000  -0.8574   0.04072   0.02994  -0.0135   1.0000   0.0629
  -8.750  -0.8374   0.03888   0.02803  -0.0126   1.0000   0.0664
  -8.500  -0.8186   0.03725   0.02614  -0.0114   1.0000   0.0718
  -8.250  -0.8026   0.03559   0.02449  -0.0101   1.0000   0.0771
  -8.000  -0.7867   0.03407   0.02285  -0.0084   1.0000   0.0833
  -7.750  -0.7739   0.03254   0.02132  -0.0066   1.0000   0.0914
  -7.500  -0.7618   0.03104   0.01982  -0.0045   1.0000   0.1031
  -7.250  -0.7509   0.02946   0.01834  -0.0023   1.0000   0.1199
  -7.000  -0.7417   0.02776   0.01687   0.0000   1.0000   0.1529
  -6.750  -0.7343   0.02610   0.01565   0.0027   1.0000   0.2103
  -6.500  -0.7266   0.02490   0.01489   0.0057   1.0000   0.2820
  -6.250  -0.7162   0.02418   0.01436   0.0086   1.0000   0.3437
  -6.000  -0.7051   0.02365   0.01391   0.0116   1.0000   0.3944
  -5.750  -0.6950   0.02322   0.01367   0.0151   1.0000   0.4449
  -5.500  -0.6830   0.02290   0.01347   0.0184   1.0000   0.4892
  -5.250  -0.6669   0.02262   0.01323   0.0210   1.0000   0.5227
  -5.000  -0.6485   0.02233   0.01290   0.0230   1.0000   0.5495
  -4.750  -0.6297   0.02206   0.01257   0.0250   1.0000   0.5749
  -4.500  -0.6093   0.02186   0.01232   0.0267   1.0000   0.5988
  -4.250  -0.5903   0.02165   0.01204   0.0285   1.0000   0.6235
  -4.000  -0.5697   0.02150   0.01185   0.0302   1.0000   0.6475
  -3.750  -0.5496   0.02136   0.01166   0.0319   1.0000   0.6719
  -3.500  -0.5295   0.02123   0.01146   0.0335   1.0000   0.6966
  -3.250  -0.5077   0.02116   0.01136   0.0349   1.0000   0.7202
  -3.000  -0.4880   0.02107   0.01121   0.0365   1.0000   0.7450
  -2.750  -0.4629   0.02108   0.01119   0.0373   1.0000   0.7674
  -2.500  -0.4408   0.02105   0.01108   0.0383   1.0000   0.7915
  -2.250  -0.4116   0.02115   0.01114   0.0382   1.0000   0.8131
  -2.000  -0.3851   0.02123   0.01116   0.0382   1.0000   0.8364
  -1.750  -0.3520   0.02139   0.01125   0.0370   1.0000   0.8575
  -1.500  -0.3096   0.02160   0.01139   0.0337   0.9969   0.8776
  -1.250  -0.2524   0.02186   0.01155   0.0275   0.9887   0.8947
  -1.000  -0.1923   0.02211   0.01170   0.0206   0.9803   0.9087
  -0.750  -0.1290   0.02233   0.01185   0.0131   0.9723   0.9201
  -0.500  -0.0695   0.02248   0.01196   0.0063   0.9620   0.9312
  -0.250  -0.0121   0.02255   0.01202  -0.0002   0.9507   0.9423
   0.000   0.0466   0.02257   0.01205  -0.0068   0.9385   0.9516
   0.250   0.1014   0.02252   0.01204  -0.0127   0.9250   0.9621
   0.500   0.1537   0.02242   0.01200  -0.0180   0.9108   0.9731
   0.750   0.2040   0.02231   0.01197  -0.0229   0.8960   0.9847
   1.000   0.2537   0.02217   0.01190  -0.0277   0.8804   0.9959
   1.250   0.2886   0.02200   0.01179  -0.0295   0.8622   1.0000
   1.500   0.3113   0.02188   0.01171  -0.0289   0.8430   1.0000
   1.750   0.3313   0.02182   0.01170  -0.0277   0.8231   1.0000
   2.000   0.3506   0.02179   0.01172  -0.0264   0.8031   1.0000
   2.250   0.3703   0.02176   0.01173  -0.0250   0.7845   1.0000
   2.500   0.3901   0.02172   0.01176  -0.0235   0.7669   1.0000
   2.750   0.4098   0.02171   0.01179  -0.0219   0.7496   1.0000
   3.000   0.4291   0.02176   0.01190  -0.0203   0.7311   1.0000
   3.250   0.4488   0.02181   0.01201  -0.0186   0.7128   1.0000
   3.500   0.4688   0.02184   0.01212  -0.0169   0.6941   1.0000
   3.750   0.4892   0.02188   0.01219  -0.0151   0.6754   1.0000
   4.000   0.5098   0.02199   0.01237  -0.0134   0.6556   1.0000
   4.250   0.5306   0.02215   0.01262  -0.0118   0.6352   1.0000
   4.500   0.5520   0.02231   0.01290  -0.0103   0.6153   1.0000
   4.750   0.5734   0.02250   0.01319  -0.0087   0.5947   1.0000
   5.000   0.5933   0.02261   0.01337  -0.0067   0.5668   1.0000
   5.250   0.6088   0.02258   0.01322  -0.0035   0.5170   1.0000
   5.500   0.6223   0.02272   0.01314  -0.0003   0.4490   1.0000
   5.750   0.6376   0.02315   0.01341   0.0021   0.3820   1.0000
   6.000   0.6500   0.02402   0.01383   0.0046   0.2817   1.0000
   6.250   0.6574   0.02591   0.01489   0.0070   0.1731   1.0000
   6.500   0.6673   0.02783   0.01636   0.0091   0.1217   1.0000
   6.750   0.6790   0.02945   0.01780   0.0111   0.1014   1.0000
   7.000   0.6914   0.03093   0.01920   0.0131   0.0896   1.0000
   7.250   0.7057   0.03228   0.02067   0.0150   0.0821   1.0000
   7.500   0.7194   0.03376   0.02212   0.0169   0.0760   1.0000
   7.750   0.7363   0.03510   0.02362   0.0186   0.0699   1.0000
   8.000   0.7541   0.03665   0.02516   0.0200   0.0661   1.0000
   8.250   0.7761   0.03839   0.02704   0.0211   0.0630   1.0000
   8.500   0.7969   0.04012   0.02903   0.0223   0.0592   1.0000
   8.750   0.8153   0.04195   0.03100   0.0234   0.0558   1.0000
   9.000   0.8348   0.04417   0.03330   0.0243   0.0538   1.0000
   9.250   0.8529   0.04692   0.03623   0.0253   0.0525   1.0000
   9.500   0.8631   0.04954   0.03934   0.0271   0.0512   1.0000
   9.750   0.8689   0.05234   0.04256   0.0292   0.0497   1.0000
  10.000   0.8709   0.05523   0.04582   0.0313   0.0483   1.0000
  10.250   0.8693   0.05823   0.04912   0.0334   0.0472   1.0000
  10.500   0.8636   0.06137   0.05254   0.0356   0.0465   1.0000
  10.750   0.8516   0.06465   0.05606   0.0380   0.0462   1.0000
  11.000   0.8340   0.06818   0.05980   0.0400   0.0462   1.0000
  11.250   0.8132   0.07239   0.06422   0.0406   0.0463   1.0000
  11.500   0.7892   0.07757   0.06960   0.0396   0.0466   1.0000
  11.750   0.7620   0.08407   0.07625   0.0366   0.0471   1.0000
  12.000   0.7324   0.09225   0.08455   0.0317   0.0478   1.0000
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