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ULTIMATE (ultimate-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: ULTIMATE (ultimate-il)
Reynolds number: 1,000,000
Max Cl/Cd: 63.41 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ultimate-il-1000000.txt
Download as CSV file: xf-ultimate-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -1.1597   0.08977   0.08701   0.0020   1.0000   0.0081
 -16.500  -1.1798   0.08236   0.07945  -0.0019   1.0000   0.0082
 -16.250  -1.2017   0.07495   0.07186  -0.0055   1.0000   0.0082
 -16.000  -1.2168   0.06889   0.06566  -0.0084   1.0000   0.0082
 -15.750  -1.2353   0.06262   0.05921  -0.0110   1.0000   0.0083
 -15.500  -1.2505   0.05713   0.05357  -0.0130   1.0000   0.0083
 -15.250  -1.2613   0.05247   0.04876  -0.0145   1.0000   0.0084
 -15.000  -1.2697   0.04831   0.04447  -0.0155   1.0000   0.0085
 -14.750  -1.2742   0.04483   0.04087  -0.0161   1.0000   0.0086
 -14.500  -1.2749   0.04193   0.03787  -0.0164   1.0000   0.0087
 -14.250  -1.2741   0.03932   0.03516  -0.0164   1.0000   0.0088
 -14.000  -1.2721   0.03697   0.03271  -0.0160   1.0000   0.0089
 -13.750  -1.2676   0.03499   0.03063  -0.0155   1.0000   0.0091
 -13.500  -1.2636   0.03306   0.02860  -0.0146   1.0000   0.0092
 -13.250  -1.2577   0.03140   0.02685  -0.0135   1.0000   0.0094
 -13.000  -1.2503   0.02996   0.02531  -0.0122   1.0000   0.0096
 -12.750  -1.2418   0.02868   0.02394  -0.0108   1.0000   0.0097
 -12.500  -1.2330   0.02747   0.02264  -0.0092   1.0000   0.0100
 -12.250  -1.2234   0.02635   0.02144  -0.0073   1.0000   0.0102
 -12.000  -1.2130   0.02533   0.02032  -0.0054   1.0000   0.0104
 -11.750  -1.2017   0.02437   0.01927  -0.0034   1.0000   0.0105
 -11.500  -1.1896   0.02348   0.01829  -0.0013   1.0000   0.0107
 -11.250  -1.1759   0.02273   0.01746   0.0006   1.0000   0.0108
 -11.000  -1.1711   0.02134   0.01595   0.0040   1.0000   0.0111
 -10.750  -1.1625   0.02004   0.01454   0.0067   1.0000   0.0114
 -10.500  -1.1464   0.01922   0.01367   0.0083   1.0000   0.0118
 -10.250  -1.1273   0.01858   0.01299   0.0095   1.0000   0.0122
 -10.000  -1.1071   0.01800   0.01237   0.0105   1.0000   0.0126
  -9.750  -1.0863   0.01744   0.01176   0.0114   1.0000   0.0130
  -9.500  -1.0649   0.01690   0.01117   0.0123   1.0000   0.0135
  -9.250  -1.0430   0.01639   0.01061   0.0131   1.0000   0.0139
  -9.000  -1.0187   0.01608   0.01027   0.0135   1.0000   0.0143
  -8.750  -1.0029   0.01505   0.00915   0.0154   1.0000   0.0153
  -8.500  -0.9810   0.01456   0.00863   0.0162   1.0000   0.0161
  -8.250  -0.9586   0.01416   0.00822   0.0170   1.0000   0.0170
  -8.000  -0.9370   0.01380   0.00783   0.0181   1.0000   0.0178
  -7.750  -0.9115   0.01349   0.00749   0.0182   0.9986   0.0186
  -7.500  -0.8816   0.01282   0.00675   0.0174   0.9957   0.0204
  -7.250  -0.8504   0.01243   0.00636   0.0163   0.9921   0.0221
  -7.000  -0.8219   0.01217   0.00608   0.0160   0.9856   0.0237
  -6.750  -0.8018   0.01188   0.00575   0.0177   0.9751   0.0254
  -6.500  -0.7845   0.01157   0.00544   0.0200   0.9639   0.0282
  -6.250  -0.7645   0.01133   0.00517   0.0217   0.9541   0.0304
  -6.000  -0.7452   0.01102   0.00483   0.0236   0.9448   0.0345
  -5.750  -0.7227   0.01073   0.00454   0.0247   0.9352   0.0395
  -5.500  -0.7019   0.01033   0.00419   0.0262   0.9264   0.0539
  -5.250  -0.6832   0.00975   0.00379   0.0280   0.9175   0.0930
  -5.000  -0.6629   0.00914   0.00343   0.0294   0.9090   0.1478
  -4.750  -0.6419   0.00868   0.00314   0.0307   0.9014   0.1945
  -4.500  -0.6186   0.00824   0.00289   0.0315   0.8940   0.2423
  -4.250  -0.5957   0.00788   0.00268   0.0325   0.8870   0.2879
  -4.000  -0.5705   0.00758   0.00252   0.0329   0.8802   0.3276
  -3.750  -0.5449   0.00739   0.00239   0.0334   0.8735   0.3549
  -3.500  -0.5180   0.00724   0.00228   0.0335   0.8670   0.3763
  -3.250  -0.4916   0.00707   0.00217   0.0338   0.8599   0.3994
  -3.000  -0.4653   0.00689   0.00206   0.0341   0.8532   0.4279
  -2.750  -0.4390   0.00668   0.00195   0.0344   0.8458   0.4584
  -2.500  -0.4123   0.00652   0.00185   0.0346   0.8383   0.4846
  -2.250  -0.3853   0.00636   0.00175   0.0348   0.8298   0.5068
  -2.000  -0.3584   0.00620   0.00167   0.0350   0.8211   0.5335
  -1.750  -0.3318   0.00604   0.00158   0.0353   0.8111   0.5634
  -1.500  -0.3049   0.00589   0.00151   0.0355   0.7992   0.5939
  -1.250  -0.2778   0.00578   0.00145   0.0356   0.7861   0.6221
  -1.000  -0.2509   0.00568   0.00139   0.0359   0.7706   0.6478
  -0.750  -0.2237   0.00562   0.00134   0.0361   0.7529   0.6707
  -0.500  -0.1965   0.00558   0.00131   0.0362   0.7343   0.6917
  -0.250  -0.1689   0.00557   0.00128   0.0363   0.7149   0.7104
   0.000  -0.1412   0.00557   0.00126   0.0364   0.6960   0.7265
   0.250  -0.1134   0.00558   0.00125   0.0364   0.6785   0.7410
   0.500  -0.0856   0.00559   0.00125   0.0364   0.6621   0.7548
   0.750  -0.0577   0.00560   0.00126   0.0363   0.6465   0.7684
   1.000  -0.0298   0.00561   0.00127   0.0363   0.6311   0.7823
   1.250  -0.0020   0.00563   0.00128   0.0363   0.6139   0.7963
   1.500   0.0256   0.00566   0.00131   0.0364   0.5947   0.8113
   1.750   0.0532   0.00568   0.00133   0.0364   0.5771   0.8270
   2.000   0.0810   0.00570   0.00137   0.0364   0.5622   0.8426
   2.250   0.1089   0.00573   0.00141   0.0364   0.5482   0.8587
   2.500   0.1372   0.00576   0.00145   0.0363   0.5344   0.8744
   2.750   0.1666   0.00577   0.00150   0.0359   0.5214   0.8897
   3.000   0.1985   0.00580   0.00154   0.0349   0.5062   0.9051
   3.250   0.2377   0.00587   0.00160   0.0322   0.4828   0.9194
   3.500   0.2867   0.00602   0.00171   0.0271   0.4562   0.9297
   3.750   0.3405   0.00622   0.00185   0.0208   0.4245   0.9354
   4.000   0.3890   0.00654   0.00204   0.0158   0.3807   0.9410
   4.250   0.4335   0.00697   0.00227   0.0116   0.3244   0.9462
   4.500   0.4739   0.00766   0.00262   0.0083   0.2410   0.9514
   4.750   0.5113   0.00845   0.00305   0.0055   0.1590   0.9582
   5.000   0.5407   0.00946   0.00359   0.0045   0.0645   0.9748
   5.250   0.5680   0.01005   0.00407   0.0043   0.0414   0.9911
   5.500   0.6037   0.01052   0.00450   0.0023   0.0329   0.9947
   5.750   0.6408   0.01079   0.00477   0.0000   0.0297   0.9963
   6.000   0.6759   0.01123   0.00521  -0.0019   0.0257   0.9978
   6.250   0.7116   0.01147   0.00546  -0.0039   0.0240   0.9991
   6.500   0.7443   0.01176   0.00575  -0.0052   0.0222   1.0000
   6.750   0.7666   0.01229   0.00631  -0.0044   0.0201   1.0000
   7.000   0.7905   0.01257   0.00661  -0.0038   0.0194   1.0000
   7.250   0.8145   0.01288   0.00695  -0.0033   0.0185   1.0000
   7.500   0.8383   0.01322   0.00730  -0.0027   0.0175   1.0000
   7.750   0.8616   0.01362   0.00771  -0.0021   0.0166   1.0000
   8.000   0.8806   0.01461   0.00877  -0.0008   0.0153   1.0000
   8.250   0.9046   0.01489   0.00907  -0.0003   0.0150   1.0000
   8.500   0.9276   0.01527   0.00950   0.0004   0.0144   1.0000
   8.750   0.9498   0.01576   0.01003   0.0012   0.0139   1.0000
   9.000   0.9718   0.01625   0.01055   0.0020   0.0134   1.0000
   9.250   0.9936   0.01674   0.01106   0.0028   0.0129   1.0000
   9.500   1.0141   0.01735   0.01170   0.0038   0.0125   1.0000
   9.750   1.0304   0.01839   0.01282   0.0054   0.0120   1.0000
  10.000   1.0431   0.01984   0.01438   0.0075   0.0116   1.0000
  10.250   1.0623   0.02048   0.01509   0.0086   0.0114   1.0000
  10.500   1.0807   0.02117   0.01585   0.0099   0.0112   1.0000
  10.750   1.0972   0.02202   0.01677   0.0114   0.0110   1.0000
  11.000   1.1131   0.02285   0.01769   0.0129   0.0108   1.0000
  11.250   1.1274   0.02379   0.01871   0.0147   0.0106   1.0000
  11.500   1.1416   0.02465   0.01965   0.0164   0.0103   1.0000
  11.750   1.1552   0.02545   0.02051   0.0182   0.0101   1.0000
  12.000   1.1644   0.02627   0.02140   0.0207   0.0099   1.0000
  12.250   1.1682   0.02709   0.02228   0.0240   0.0097   1.0000
  12.500   1.1726   0.02810   0.02336   0.0267   0.0095   1.0000
  12.750   1.1775   0.02927   0.02460   0.0290   0.0094   1.0000
  13.000   1.1814   0.03070   0.02611   0.0310   0.0093   1.0000
  13.250   1.1832   0.03246   0.02796   0.0329   0.0091   1.0000
  13.500   1.1796   0.03490   0.03054   0.0346   0.0090   1.0000
  13.750   1.1693   0.03827   0.03409   0.0362   0.0088   1.0000
  14.000   1.1483   0.04311   0.03920   0.0374   0.0087   1.0000
  14.250   1.1462   0.04597   0.04221   0.0373   0.0086   1.0000
  14.500   1.1420   0.04929   0.04566   0.0367   0.0086   1.0000
  14.750   1.1359   0.05306   0.04958   0.0357   0.0086   1.0000
  15.000   1.1284   0.05722   0.05388   0.0343   0.0085   1.0000
  15.250   1.1165   0.06221   0.05903   0.0323   0.0085   1.0000
  15.500   1.1017   0.06789   0.06486   0.0297   0.0085   1.0000
  15.750   1.0847   0.07424   0.07137   0.0266   0.0085   1.0000
  16.000   1.0649   0.08148   0.07876   0.0228   0.0085   1.0000
  16.250   1.0391   0.09016   0.08762   0.0181   0.0085   1.0000
  16.500   1.0078   0.10055   0.09818   0.0124   0.0085   1.0000
  16.750   0.9696   0.11312   0.11092   0.0054   0.0086   1.0000
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