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ULTIMATE (ultimate-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: ULTIMATE (ultimate-il)
Reynolds number: 500,000
Max Cl/Cd: 55.43 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ultimate-il-500000.txt
Download as CSV file: xf-ultimate-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.9809   0.08758   0.08465  -0.0080   1.0000   0.0142
 -14.500  -1.0066   0.07927   0.07618  -0.0129   1.0000   0.0142
 -14.250  -1.0290   0.07213   0.06884  -0.0168   1.0000   0.0141
 -14.000  -1.0492   0.06585   0.06238  -0.0199   1.0000   0.0141
 -13.750  -1.0652   0.06075   0.05707  -0.0220   1.0000   0.0142
 -13.500  -1.0781   0.05648   0.05261  -0.0232   1.0000   0.0142
 -13.250  -1.0915   0.05247   0.04838  -0.0236   1.0000   0.0143
 -12.750  -1.1171   0.04529   0.04073  -0.0217   1.0000   0.0144
 -12.500  -1.1293   0.04137   0.03653  -0.0196   1.0000   0.0145
 -12.250  -1.1343   0.03812   0.03304  -0.0174   1.0000   0.0147
 -12.000  -1.1329   0.03560   0.03037  -0.0153   1.0000   0.0149
 -11.750  -1.1273   0.03377   0.02842  -0.0133   1.0000   0.0152
 -11.500  -1.1197   0.03222   0.02676  -0.0112   1.0000   0.0154
 -11.250  -1.1107   0.03086   0.02529  -0.0091   1.0000   0.0157
 -11.000  -1.1005   0.02958   0.02390  -0.0070   1.0000   0.0161
 -10.750  -1.0889   0.02834   0.02254  -0.0050   1.0000   0.0164
 -10.500  -1.0753   0.02717   0.02126  -0.0032   1.0000   0.0169
 -10.250  -1.0598   0.02596   0.01993  -0.0017   1.0000   0.0173
 -10.000  -1.0429   0.02493   0.01879  -0.0003   1.0000   0.0179
  -9.750  -1.0245   0.02414   0.01788   0.0010   1.0000   0.0184
  -9.500  -1.0085   0.02270   0.01632   0.0025   1.0000   0.0191
  -9.250  -0.9942   0.02122   0.01479   0.0043   1.0000   0.0199
  -9.000  -0.9760   0.02037   0.01391   0.0056   1.0000   0.0207
  -8.750  -0.9569   0.01960   0.01309   0.0068   1.0000   0.0215
  -8.500  -0.9373   0.01887   0.01230   0.0080   1.0000   0.0225
  -8.250  -0.9171   0.01822   0.01158   0.0092   1.0000   0.0235
  -8.000  -0.8954   0.01773   0.01102   0.0101   1.0000   0.0242
  -7.750  -0.8835   0.01646   0.00971   0.0127   1.0000   0.0261
  -7.500  -0.8644   0.01596   0.00919   0.0141   1.0000   0.0278
  -7.250  -0.8470   0.01553   0.00872   0.0159   1.0000   0.0296
  -7.000  -0.8321   0.01520   0.00834   0.0183   1.0000   0.0309
  -6.750  -0.8259   0.01457   0.00766   0.0223   1.0000   0.0331
  -6.500  -0.7982   0.01403   0.00711   0.0219   0.9977   0.0366
  -6.250  -0.7641   0.01348   0.00651   0.0203   0.9953   0.0418
  -6.000  -0.7300   0.01290   0.00595   0.0186   0.9927   0.0506
  -5.750  -0.6992   0.01195   0.00526   0.0174   0.9891   0.0921
  -5.500  -0.6703   0.01084   0.00466   0.0163   0.9854   0.1875
  -5.250  -0.6436   0.01018   0.00431   0.0161   0.9791   0.2540
  -5.000  -0.6161   0.00970   0.00407   0.0158   0.9734   0.3122
  -4.750  -0.5929   0.00941   0.00391   0.0168   0.9647   0.3498
  -4.500  -0.5691   0.00921   0.00376   0.0177   0.9573   0.3777
  -4.250  -0.5471   0.00899   0.00360   0.0190   0.9485   0.4015
  -4.000  -0.5246   0.00880   0.00345   0.0202   0.9404   0.4242
  -3.750  -0.5037   0.00856   0.00328   0.0219   0.9324   0.4493
  -3.500  -0.4819   0.00831   0.00313   0.0233   0.9236   0.4806
  -3.250  -0.4615   0.00806   0.00298   0.0251   0.9158   0.5124
  -3.000  -0.4386   0.00785   0.00285   0.0262   0.9066   0.5389
  -2.750  -0.4160   0.00767   0.00273   0.0276   0.8983   0.5658
  -2.500  -0.3929   0.00752   0.00263   0.0287   0.8893   0.5948
  -2.250  -0.3688   0.00739   0.00256   0.0297   0.8801   0.6233
  -1.750  -0.3196   0.00719   0.00244   0.0315   0.8613   0.6736
  -1.500  -0.2943   0.00711   0.00240   0.0322   0.8515   0.6965
  -1.250  -0.2689   0.00704   0.00235   0.0329   0.8418   0.7172
  -1.000  -0.2425   0.00695   0.00230   0.0333   0.8303   0.7364
  -0.750  -0.2159   0.00687   0.00225   0.0338   0.8183   0.7540
  -0.500  -0.1892   0.00680   0.00219   0.0342   0.8058   0.7701
  -0.250  -0.1623   0.00673   0.00214   0.0345   0.7918   0.7855
   0.000  -0.1352   0.00667   0.00209   0.0348   0.7763   0.8007
   0.250  -0.1080   0.00663   0.00205   0.0351   0.7594   0.8159
   0.500  -0.0806   0.00661   0.00201   0.0354   0.7413   0.8310
   0.750  -0.0531   0.00661   0.00199   0.0356   0.7229   0.8462
   1.000  -0.0253   0.00663   0.00198   0.0357   0.7051   0.8612
   1.250   0.0035   0.00665   0.00198   0.0355   0.6875   0.8762
   1.500   0.0338   0.00666   0.00198   0.0350   0.6702   0.8913
   1.750   0.0680   0.00669   0.00200   0.0336   0.6522   0.9061
   2.000   0.1088   0.00676   0.00204   0.0305   0.6309   0.9193
   2.250   0.1553   0.00688   0.00213   0.0262   0.6111   0.9295
   2.500   0.2062   0.00702   0.00227   0.0208   0.5931   0.9351
   2.750   0.2522   0.00719   0.00243   0.0166   0.5762   0.9415
   3.000   0.2958   0.00740   0.00262   0.0130   0.5593   0.9463
   3.250   0.3355   0.00765   0.00280   0.0103   0.5345   0.9519
   3.500   0.3728   0.00789   0.00299   0.0082   0.5093   0.9581
   3.750   0.4080   0.00816   0.00319   0.0065   0.4818   0.9654
   4.000   0.4411   0.00846   0.00341   0.0052   0.4512   0.9766
   4.250   0.4754   0.00885   0.00369   0.0036   0.4163   0.9876
   4.500   0.5144   0.00928   0.00395   0.0008   0.3646   0.9932
   4.750   0.5514   0.01000   0.00426  -0.0018   0.2690   0.9962
   5.000   0.5852   0.01119   0.00477  -0.0043   0.1339   0.9982
   5.250   0.6192   0.01235   0.00547  -0.0065   0.0507   0.9999
   5.500   0.6408   0.01283   0.00592  -0.0057   0.0421   1.0000
   5.750   0.6626   0.01308   0.00620  -0.0048   0.0385   1.0000
   6.000   0.6840   0.01353   0.00664  -0.0038   0.0347   1.0000
   6.250   0.7052   0.01412   0.00729  -0.0028   0.0323   1.0000
   6.500   0.7277   0.01453   0.00774  -0.0020   0.0303   1.0000
   6.750   0.7499   0.01499   0.00820  -0.0011   0.0283   1.0000
   7.000   0.7685   0.01597   0.00920   0.0002   0.0261   1.0000
   7.250   0.7899   0.01656   0.00984   0.0012   0.0250   1.0000
   7.500   0.8112   0.01714   0.01049   0.0022   0.0239   1.0000
   7.750   0.8319   0.01779   0.01118   0.0033   0.0228   1.0000
   8.000   0.8524   0.01846   0.01187   0.0043   0.0218   1.0000
   8.250   0.8715   0.01932   0.01275   0.0056   0.0210   1.0000
   8.500   0.8857   0.02128   0.01476   0.0075   0.0200   1.0000
   8.750   0.9064   0.02189   0.01547   0.0085   0.0195   1.0000
   9.000   0.9264   0.02264   0.01632   0.0097   0.0188   1.0000
   9.250   0.9455   0.02358   0.01735   0.0109   0.0181   1.0000
   9.500   0.9638   0.02466   0.01853   0.0122   0.0176   1.0000
   9.750   0.9815   0.02579   0.01975   0.0135   0.0172   1.0000
  10.000   0.9983   0.02694   0.02100   0.0149   0.0167   1.0000
  10.250   1.0141   0.02818   0.02234   0.0164   0.0164   1.0000
  10.500   1.0287   0.02959   0.02384   0.0179   0.0160   1.0000
  10.750   1.0406   0.03168   0.02606   0.0196   0.0157   1.0000
  11.000   1.0464   0.03495   0.02958   0.0218   0.0155   1.0000
  11.250   1.0464   0.03844   0.03337   0.0246   0.0154   1.0000
  11.500   1.0433   0.04086   0.03606   0.0278   0.0153   1.0000
  11.750   1.0363   0.04251   0.03790   0.0318   0.0151   1.0000
  12.000   1.0252   0.04448   0.04007   0.0356   0.0150   1.0000
  12.250   1.0130   0.04704   0.04283   0.0384   0.0149   1.0000
  12.500   0.9974   0.05046   0.04647   0.0401   0.0149   1.0000
  12.750   0.9809   0.05430   0.05052   0.0408   0.0148   1.0000
  13.000   0.9620   0.05892   0.05535   0.0403   0.0148   1.0000
  13.250   0.9418   0.06428   0.06090   0.0386   0.0148   1.0000
  13.500   0.9186   0.07073   0.06753   0.0357   0.0149   1.0000
  13.750   0.8944   0.07798   0.07493   0.0318   0.0150   1.0000
  14.000   0.8684   0.08624   0.08333   0.0270   0.0151   1.0000
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