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ULTIMATE (ultimate-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: ULTIMATE (ultimate-il)
Reynolds number: 200,000
Max Cl/Cd: 41.95 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ultimate-il-200000-n5.txt
Download as CSV file: xf-ultimate-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.9695   0.08782   0.08343  -0.0102   1.0000   0.0143
 -14.250  -1.0060   0.07433   0.06955  -0.0180   1.0000   0.0144
 -14.000  -1.0207   0.06876   0.06380  -0.0206   1.0000   0.0145
 -13.750  -1.0315   0.06409   0.05898  -0.0225   1.0000   0.0146
 -13.500  -1.0415   0.05975   0.05445  -0.0239   1.0000   0.0147
 -13.250  -1.0467   0.05632   0.05090  -0.0246   1.0000   0.0149
 -13.000  -1.0512   0.05319   0.04762  -0.0250   1.0000   0.0152
 -12.750  -1.0552   0.05021   0.04448  -0.0249   1.0000   0.0154
 -12.500  -1.0577   0.04758   0.04168  -0.0244   1.0000   0.0157
 -12.250  -1.0591   0.04511   0.03902  -0.0234   1.0000   0.0160
 -12.000  -1.0592   0.04281   0.03652  -0.0221   1.0000   0.0163
 -11.750  -1.0576   0.04061   0.03411  -0.0205   1.0000   0.0166
 -11.500  -1.0536   0.03854   0.03182  -0.0186   1.0000   0.0170
 -11.250  -1.0474   0.03662   0.02969  -0.0167   1.0000   0.0174
 -11.000  -1.0391   0.03487   0.02773  -0.0149   1.0000   0.0178
 -10.750  -1.0289   0.03325   0.02589  -0.0130   1.0000   0.0182
 -10.500  -1.0172   0.03183   0.02427  -0.0112   1.0000   0.0187
 -10.250  -1.0065   0.03020   0.02257  -0.0093   1.0000   0.0192
 -10.000  -0.9951   0.02901   0.02133  -0.0073   1.0000   0.0198
  -9.750  -0.9820   0.02805   0.02031  -0.0056   1.0000   0.0207
  -9.500  -0.9667   0.02708   0.01926  -0.0040   1.0000   0.0217
  -9.250  -0.9507   0.02605   0.01812  -0.0025   1.0000   0.0228
  -9.000  -0.9342   0.02506   0.01698  -0.0010   1.0000   0.0237
  -8.750  -0.9191   0.02396   0.01580   0.0007   1.0000   0.0246
  -8.500  -0.9047   0.02288   0.01469   0.0025   1.0000   0.0257
  -8.250  -0.8877   0.02205   0.01382   0.0040   1.0000   0.0270
  -8.000  -0.8696   0.02132   0.01302   0.0054   1.0000   0.0289
  -7.750  -0.8507   0.02067   0.01225   0.0068   1.0000   0.0308
  -7.500  -0.8352   0.01977   0.01134   0.0086   1.0000   0.0329
  -7.250  -0.8177   0.01910   0.01062   0.0102   1.0000   0.0353
  -7.000  -0.7995   0.01855   0.00999   0.0118   1.0000   0.0385
  -6.750  -0.7837   0.01792   0.00934   0.0138   1.0000   0.0423
  -6.500  -0.7684   0.01740   0.00878   0.0160   1.0000   0.0472
  -6.250  -0.7543   0.01689   0.00826   0.0184   1.0000   0.0537
  -6.000  -0.7384   0.01633   0.00776   0.0204   0.9991   0.0668
  -5.750  -0.7092   0.01542   0.00710   0.0193   0.9947   0.1109
  -5.500  -0.6807   0.01453   0.00652   0.0184   0.9896   0.1744
  -5.250  -0.6509   0.01377   0.00606   0.0173   0.9847   0.2388
  -5.000  -0.6234   0.01320   0.00575   0.0168   0.9773   0.2987
  -4.750  -0.5937   0.01281   0.00550   0.0161   0.9704   0.3441
  -4.500  -0.5662   0.01246   0.00527   0.0160   0.9617   0.3864
  -4.250  -0.5417   0.01211   0.00507   0.0166   0.9517   0.4292
  -4.000  -0.5157   0.01182   0.00487   0.0169   0.9427   0.4600
  -3.750  -0.4895   0.01159   0.00466   0.0173   0.9334   0.4808
  -3.500  -0.4640   0.01137   0.00447   0.0179   0.9239   0.5015
  -3.250  -0.4385   0.01115   0.00430   0.0185   0.9155   0.5235
  -2.750  -0.3898   0.01077   0.00402   0.0204   0.8967   0.5734
  -2.500  -0.3660   0.01060   0.00391   0.0215   0.8878   0.6005
  -2.250  -0.3419   0.01046   0.00383   0.0225   0.8777   0.6273
  -2.000  -0.3178   0.01035   0.00374   0.0236   0.8681   0.6530
  -1.750  -0.2932   0.01024   0.00367   0.0246   0.8581   0.6755
  -1.500  -0.2679   0.01016   0.00361   0.0253   0.8469   0.6963
  -1.250  -0.2424   0.01008   0.00354   0.0260   0.8357   0.7150
  -1.000  -0.2165   0.01001   0.00348   0.0267   0.8242   0.7326
  -0.750  -0.1902   0.00993   0.00342   0.0272   0.8116   0.7493
  -0.500  -0.1634   0.00986   0.00337   0.0276   0.7979   0.7656
  -0.250  -0.1363   0.00980   0.00332   0.0280   0.7835   0.7811
   0.000  -0.1089   0.00974   0.00328   0.0283   0.7685   0.7965
   0.250  -0.0810   0.00970   0.00323   0.0285   0.7528   0.8118
   0.500  -0.0525   0.00967   0.00319   0.0285   0.7366   0.8270
   0.750  -0.0233   0.00966   0.00316   0.0284   0.7203   0.8422
   1.000   0.0069   0.00967   0.00315   0.0280   0.7038   0.8570
   1.250   0.0390   0.00970   0.00315   0.0272   0.6874   0.8716
   1.500   0.0732   0.00975   0.00318   0.0259   0.6712   0.8853
   1.750   0.1101   0.00983   0.00325   0.0239   0.6552   0.8981
   2.000   0.1513   0.00995   0.00335   0.0209   0.6390   0.9081
   2.250   0.1924   0.01008   0.00348   0.0180   0.6223   0.9174
   2.500   0.2341   0.01025   0.00362   0.0149   0.6018   0.9254
   2.750   0.2757   0.01044   0.00377   0.0118   0.5802   0.9321
   3.000   0.3168   0.01064   0.00399   0.0089   0.5612   0.9401
   3.250   0.3581   0.01088   0.00425   0.0060   0.5438   0.9488
   3.500   0.3963   0.01112   0.00450   0.0038   0.5268   0.9584
   3.750   0.4303   0.01137   0.00471   0.0024   0.5003   0.9679
   4.250   0.4932   0.01205   0.00512   0.0002   0.4164   0.9881
   4.500   0.5265   0.01255   0.00537  -0.0015   0.3479   0.9948
   5.000   0.5857   0.01416   0.00612  -0.0041   0.1709   1.0000
   5.250   0.6048   0.01510   0.00662  -0.0033   0.0893   1.0000
   5.500   0.6249   0.01584   0.00717  -0.0024   0.0583   1.0000
   5.750   0.6462   0.01638   0.00770  -0.0015   0.0487   1.0000
   6.000   0.6670   0.01699   0.00830  -0.0005   0.0427   1.0000
   6.250   0.6885   0.01749   0.00887   0.0004   0.0386   1.0000
   6.500   0.7094   0.01808   0.00950   0.0014   0.0353   1.0000
   6.750   0.7283   0.01891   0.01035   0.0027   0.0329   1.0000
   7.000   0.7487   0.01951   0.01104   0.0038   0.0309   1.0000
   7.250   0.7686   0.02016   0.01174   0.0049   0.0288   1.0000
   7.500   0.7876   0.02090   0.01251   0.0061   0.0270   1.0000
   7.750   0.8034   0.02203   0.01363   0.0077   0.0258   1.0000
   8.000   0.8220   0.02286   0.01456   0.0091   0.0249   1.0000
   8.250   0.8400   0.02378   0.01557   0.0105   0.0238   1.0000
   8.500   0.8580   0.02467   0.01654   0.0119   0.0226   1.0000
   8.750   0.8757   0.02553   0.01745   0.0132   0.0215   1.0000
   9.000   0.8924   0.02649   0.01843   0.0145   0.0206   1.0000
   9.250   0.9077   0.02789   0.01987   0.0161   0.0198   1.0000
   9.500   0.9244   0.02911   0.02127   0.0176   0.0193   1.0000
   9.750   0.9402   0.03051   0.02283   0.0191   0.0187   1.0000
  10.000   0.9549   0.03201   0.02452   0.0207   0.0182   1.0000
  10.250   0.9683   0.03362   0.02631   0.0224   0.0177   1.0000
  10.500   0.9796   0.03530   0.02820   0.0242   0.0173   1.0000
  10.750   0.9890   0.03694   0.03002   0.0262   0.0168   1.0000
  11.000   0.9967   0.03846   0.03168   0.0282   0.0164   1.0000
  11.250   1.0004   0.03995   0.03330   0.0308   0.0161   1.0000
  11.500   1.0013   0.04142   0.03484   0.0335   0.0158   1.0000
  11.750   1.0006   0.04337   0.03689   0.0359   0.0155   1.0000
  12.000   0.9945   0.04587   0.03961   0.0382   0.0152   1.0000
  12.250   0.9851   0.04873   0.04276   0.0401   0.0150   1.0000
  12.500   0.9732   0.05217   0.04649   0.0412   0.0148   1.0000
  12.750   0.9595   0.05614   0.05071   0.0415   0.0147   1.0000
  13.000   0.9437   0.06072   0.05554   0.0408   0.0147   1.0000
  13.250   0.9260   0.06599   0.06104   0.0390   0.0146   1.0000
  13.500   0.9054   0.07221   0.06748   0.0361   0.0146   1.0000
  13.750   0.8835   0.07922   0.07469   0.0323   0.0147   1.0000
  14.000   0.8593   0.08733   0.08299   0.0274   0.0147   1.0000
  14.250   0.8328   0.09672   0.09254   0.0216   0.0148   1.0000
  14.500   0.8029   0.10804   0.10400   0.0147   0.0150   1.0000
  14.750   0.7659   0.12269   0.11874   0.0065   0.0152   1.0000
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