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ULTIMATE (ultimate-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: ULTIMATE (ultimate-il)
Reynolds number: 100,000
Max Cl/Cd: 38.96 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ultimate-il-100000.txt
Download as CSV file: xf-ultimate-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.7981   0.09191   0.08700  -0.0189   1.0000   0.0717
 -11.750  -0.8129   0.08522   0.08027  -0.0219   1.0000   0.0702
 -11.500  -0.8422   0.07786   0.07279  -0.0256   1.0000   0.0681
 -11.250  -0.8806   0.07117   0.06589  -0.0276   1.0000   0.0659
 -11.000  -0.9327   0.06560   0.05990  -0.0253   1.0000   0.0634
 -10.750  -0.9765   0.06397   0.05764  -0.0186   1.0000   0.0612
 -10.500  -0.9739   0.05936   0.05282  -0.0172   1.0000   0.0602
 -10.250  -0.9778   0.05553   0.04868  -0.0147   1.0000   0.0600
 -10.000  -0.9799   0.05228   0.04504  -0.0118   1.0000   0.0602
  -9.750  -0.9789   0.04943   0.04176  -0.0088   1.0000   0.0606
  -9.500  -0.9733   0.04655   0.03842  -0.0061   1.0000   0.0609
  -9.250  -0.9625   0.04326   0.03475  -0.0040   1.0000   0.0610
  -9.000  -0.9473   0.03939   0.03054  -0.0026   1.0000   0.0615
  -8.750  -0.9262   0.03603   0.02698  -0.0020   1.0000   0.0627
  -8.500  -0.9047   0.03383   0.02470  -0.0014   1.0000   0.0656
  -8.250  -0.8831   0.03205   0.02275  -0.0004   1.0000   0.0694
  -8.000  -0.8592   0.03027   0.02067   0.0005   1.0000   0.0723
  -7.750  -0.8324   0.02790   0.01837   0.0005   1.0000   0.0765
  -7.500  -0.8108   0.02654   0.01700   0.0015   1.0000   0.0830
  -7.250  -0.7905   0.02490   0.01542   0.0027   1.0000   0.0897
  -7.000  -0.7728   0.02370   0.01418   0.0046   1.0000   0.0992
  -6.750  -0.7598   0.02237   0.01298   0.0070   1.0000   0.1130
  -6.500  -0.7517   0.02086   0.01174   0.0104   1.0000   0.1371
  -6.250  -0.7539   0.01872   0.01045   0.0154   1.0000   0.2258
  -6.000  -0.7541   0.01763   0.01003   0.0205   1.0000   0.3484
  -5.750  -0.7447   0.01726   0.00979   0.0241   1.0000   0.4048
  -5.500  -0.7326   0.01696   0.00957   0.0272   1.0000   0.4452
  -5.250  -0.7190   0.01670   0.00933   0.0301   1.0000   0.4806
  -5.000  -0.7047   0.01646   0.00915   0.0329   1.0000   0.5142
  -4.750  -0.6902   0.01630   0.00911   0.0357   1.0000   0.5495
  -4.500  -0.6759   0.01625   0.00917   0.0387   1.0000   0.5865
  -4.250  -0.6601   0.01621   0.00920   0.0414   1.0000   0.6192
  -4.000  -0.6412   0.01611   0.00913   0.0434   1.0000   0.6452
  -3.750  -0.6223   0.01601   0.00903   0.0453   1.0000   0.6706
  -3.500  -0.6030   0.01593   0.00897   0.0471   1.0000   0.6965
  -3.250  -0.5823   0.01588   0.00897   0.0487   1.0000   0.7221
  -3.000  -0.5621   0.01586   0.00895   0.0503   1.0000   0.7493
  -2.750  -0.5419   0.01586   0.00899   0.0520   1.0000   0.7775
  -2.500  -0.5206   0.01593   0.00908   0.0535   1.0000   0.8061
  -2.250  -0.4964   0.01606   0.00923   0.0544   1.0000   0.8343
  -2.000  -0.4684   0.01623   0.00941   0.0545   1.0000   0.8630
  -1.750  -0.4310   0.01652   0.00967   0.0525   1.0000   0.8902
  -1.500  -0.3850   0.01694   0.01003   0.0485   1.0000   0.9143
  -1.250  -0.3106   0.01763   0.01062   0.0390   0.9952   0.9289
  -1.000  -0.2313   0.01829   0.01118   0.0284   0.9901   0.9373
  -0.750  -0.1549   0.01881   0.01162   0.0184   0.9847   0.9458
  -0.500  -0.0834   0.01911   0.01188   0.0092   0.9766   0.9548
  -0.250  -0.0084   0.01926   0.01201  -0.0007   0.9691   0.9613
   0.000   0.0644   0.01923   0.01200  -0.0102   0.9614   0.9692
   0.250   0.1316   0.01908   0.01189  -0.0185   0.9497   0.9766
   0.500   0.1959   0.01880   0.01166  -0.0262   0.9363   0.9838
   0.750   0.2538   0.01843   0.01137  -0.0324   0.9207   0.9916
   1.000   0.3058   0.01800   0.01100  -0.0372   0.9035   0.9996
   1.250   0.3250   0.01774   0.01076  -0.0358   0.8811   1.0000
   1.500   0.3405   0.01753   0.01055  -0.0334   0.8598   1.0000
   1.750   0.3557   0.01738   0.01038  -0.0310   0.8399   1.0000
   2.000   0.3723   0.01726   0.01027  -0.0291   0.8187   1.0000
   2.250   0.3887   0.01709   0.01010  -0.0269   0.7995   1.0000
   2.500   0.4053   0.01688   0.00989  -0.0245   0.7811   1.0000
   2.750   0.4234   0.01673   0.00975  -0.0226   0.7609   1.0000
   3.000   0.4422   0.01659   0.00961  -0.0208   0.7417   1.0000
   3.250   0.4618   0.01648   0.00950  -0.0190   0.7238   1.0000
   3.500   0.4820   0.01643   0.00946  -0.0174   0.7065   1.0000
   3.750   0.5026   0.01643   0.00946  -0.0158   0.6894   1.0000
   4.000   0.5236   0.01650   0.00957  -0.0144   0.6694   1.0000
   4.250   0.5433   0.01643   0.00944  -0.0122   0.6445   1.0000
   4.500   0.5623   0.01629   0.00922  -0.0097   0.6114   1.0000
   4.750   0.5817   0.01620   0.00909  -0.0076   0.5732   1.0000
   5.000   0.6022   0.01621   0.00904  -0.0058   0.5375   1.0000
   5.250   0.6228   0.01629   0.00912  -0.0042   0.4956   1.0000
   5.500   0.6420   0.01648   0.00919  -0.0023   0.4338   1.0000
   5.750   0.6493   0.01830   0.00968   0.0007   0.2016   1.0000
   6.000   0.6592   0.02063   0.01119   0.0030   0.1186   1.0000
   6.250   0.6750   0.02193   0.01237   0.0049   0.1006   1.0000
   6.500   0.6912   0.02325   0.01357   0.0068   0.0913   1.0000
   6.750   0.7103   0.02446   0.01482   0.0085   0.0841   1.0000
   7.000   0.7297   0.02612   0.01627   0.0097   0.0776   1.0000
   7.250   0.7530   0.02757   0.01784   0.0109   0.0744   1.0000
   7.500   0.7761   0.02911   0.01950   0.0119   0.0709   1.0000
   7.750   0.7981   0.03081   0.02121   0.0128   0.0668   1.0000
   8.000   0.8215   0.03386   0.02430   0.0134   0.0645   1.0000
   8.250   0.8414   0.03601   0.02680   0.0149   0.0639   1.0000
   8.500   0.8593   0.03859   0.02975   0.0165   0.0636   1.0000
   8.750   0.8737   0.04128   0.03285   0.0184   0.0632   1.0000
   9.000   0.8847   0.04398   0.03597   0.0206   0.0624   1.0000
   9.250   0.8922   0.04703   0.03943   0.0229   0.0620   1.0000
   9.500   0.8977   0.05079   0.04355   0.0251   0.0628   1.0000
   9.750   0.9036   0.05558   0.04853   0.0267   0.0641   1.0000
  10.000   0.8766   0.05978   0.05368   0.0321   0.0704   1.0000
  10.250   0.8617   0.06486   0.05901   0.0345   0.0741   1.0000
  10.500   0.8230   0.07029   0.06482   0.0381   0.0816   1.0000
  10.750   0.7797   0.06299   0.05753   0.0432   0.0780   1.0000
  11.000   0.7386   0.06637   0.06109   0.0460   0.0783   1.0000
  11.250   0.6948   0.07156   0.06643   0.0456   0.0785   1.0000
  11.500   0.6426   0.07944   0.07444   0.0420   0.0788   1.0000
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