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RUTAN WING AIRFOIL (amsoil2-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: RUTAN WING AIRFOIL (amsoil2-il)
Reynolds number: 100,000
Max Cl/Cd: 38.67 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-amsoil2-il-100000.txt
Download as CSV file: xf-amsoil2-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RUTAN WING AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5387   0.10505   0.09958  -0.0129   1.0000   0.1495
  -9.500  -0.5431   0.10123   0.09581  -0.0156   1.0000   0.1564
  -9.250  -0.6339   0.09307   0.08774  -0.0319   1.0000   0.1596
  -9.000  -0.5435   0.09273   0.08738  -0.0187   1.0000   0.1653
  -8.750  -0.5439   0.08900   0.08369  -0.0205   1.0000   0.1718
  -8.500  -0.6481   0.08170   0.07625  -0.0341   1.0000   0.1768
  -8.250  -0.5702   0.07847   0.07330  -0.0276   1.0000   0.1820
  -8.000  -0.5736   0.07491   0.06975  -0.0286   1.0000   0.1880
  -7.750  -0.6095   0.06947   0.06424  -0.0318   1.0000   0.1970
  -7.500  -0.6762   0.05138   0.04469  -0.0332   1.0000   0.1119
  -7.250  -0.6724   0.04809   0.04132  -0.0308   1.0000   0.1097
  -7.000  -0.6714   0.04489   0.03786  -0.0280   1.0000   0.1080
  -6.750  -0.6681   0.04170   0.03430  -0.0254   1.0000   0.1065
  -6.500  -0.6609   0.03859   0.03078  -0.0230   1.0000   0.1051
  -6.250  -0.6497   0.03588   0.02768  -0.0209   1.0000   0.1045
  -6.000  -0.6352   0.03411   0.02567  -0.0193   1.0000   0.1062
  -5.750  -0.6192   0.03244   0.02372  -0.0177   1.0000   0.1084
  -5.500  -0.6014   0.03075   0.02170  -0.0163   1.0000   0.1102
  -5.250  -0.5820   0.02930   0.01988  -0.0151   1.0000   0.1122
  -5.000  -0.5619   0.02775   0.01816  -0.0142   1.0000   0.1154
  -4.750  -0.5411   0.02674   0.01715  -0.0134   1.0000   0.1192
  -4.500  -0.5191   0.02578   0.01606  -0.0126   1.0000   0.1230
  -4.250  -0.4965   0.02512   0.01511  -0.0118   1.0000   0.1278
  -4.000  -0.4734   0.02395   0.01410  -0.0115   1.0000   0.1336
  -3.750  -0.4505   0.02331   0.01339  -0.0108   1.0000   0.1402
  -3.500  -0.4275   0.02251   0.01264  -0.0103   1.0000   0.1478
  -3.250  -0.4048   0.02202   0.01214  -0.0098   1.0000   0.1575
  -3.000  -0.3819   0.02133   0.01161  -0.0093   1.0000   0.1684
  -2.750  -0.3590   0.02078   0.01117  -0.0089   1.0000   0.1824
  -2.500  -0.3240   0.02019   0.01078  -0.0108   0.9966   0.2061
  -2.250  -0.2866   0.01946   0.01039  -0.0132   0.9932   0.2497
  -2.000  -0.2643   0.01724   0.01067  -0.0119   0.9910   0.6940
  -1.750  -0.2457   0.01785   0.01150  -0.0078   0.9857   0.8081
  -1.500  -0.2251   0.01840   0.01205  -0.0047   0.9803   0.8586
  -1.250  -0.2054   0.01885   0.01248  -0.0015   0.9744   0.8974
  -1.000  -0.1710   0.01938   0.01295  -0.0012   0.9708   0.9353
  -0.750  -0.1056   0.02007   0.01352  -0.0075   0.9696   0.9673
  -0.500   0.0031   0.02079   0.01410  -0.0227   0.9724   0.9912
  -0.250   0.0679   0.02099   0.01423  -0.0309   0.9703   1.0000
   0.000   0.0902   0.02105   0.01426  -0.0314   0.9618   1.0000
   0.250   0.1259   0.02118   0.01436  -0.0342   0.9561   1.0000
   0.500   0.1443   0.02130   0.01447  -0.0338   0.9468   1.0000
   0.750   0.1820   0.02151   0.01467  -0.0368   0.9415   1.0000
   1.000   0.1912   0.02169   0.01485  -0.0346   0.9312   1.0000
   1.250   0.2302   0.02181   0.01499  -0.0373   0.9213   1.0000
   1.500   0.3448   0.02086   0.01413  -0.0512   0.9018   1.0000
   1.750   0.4066   0.01997   0.01332  -0.0558   0.8840   1.0000
   2.000   0.4442   0.01922   0.01262  -0.0559   0.8654   1.0000
   2.250   0.4708   0.01850   0.01195  -0.0539   0.8458   1.0000
   2.500   0.4924   0.01774   0.01121  -0.0508   0.8252   1.0000
   2.750   0.5114   0.01699   0.01049  -0.0474   0.8043   1.0000
   3.000   0.5286   0.01631   0.00982  -0.0437   0.7813   1.0000
   3.250   0.5439   0.01567   0.00922  -0.0399   0.7517   1.0000
   3.500   0.5584   0.01495   0.00848  -0.0356   0.7044   1.0000
   3.750   0.5646   0.01460   0.00724  -0.0287   0.4842   1.0000
   4.000   0.5579   0.01695   0.00790  -0.0232   0.2571   1.0000
   4.250   0.5691   0.01807   0.00863  -0.0206   0.2172   1.0000
   4.500   0.5852   0.01906   0.00933  -0.0187   0.1951   1.0000
   4.750   0.6055   0.01997   0.01005  -0.0174   0.1785   1.0000
   5.000   0.6284   0.02088   0.01084  -0.0166   0.1653   1.0000
   5.250   0.6530   0.02195   0.01179  -0.0161   0.1551   1.0000
   5.500   0.6783   0.02294   0.01265  -0.0157   0.1458   1.0000
   5.750   0.7049   0.02411   0.01382  -0.0154   0.1384   1.0000
   6.000   0.7311   0.02517   0.01486  -0.0151   0.1317   1.0000
   6.250   0.7580   0.02665   0.01631  -0.0150   0.1259   1.0000
   6.500   0.7842   0.02787   0.01769  -0.0146   0.1211   1.0000
   6.750   0.8100   0.02918   0.01900  -0.0144   0.1164   1.0000
   7.000   0.8351   0.03107   0.02098  -0.0142   0.1125   1.0000
   7.250   0.8586   0.03273   0.02299  -0.0133   0.1095   1.0000
   7.500   0.8815   0.03445   0.02494  -0.0126   0.1063   1.0000
   7.750   0.9057   0.03606   0.02654  -0.0124   0.1029   1.0000
   8.000   0.9274   0.03912   0.02966  -0.0121   0.1008   1.0000
   8.250   0.9434   0.04144   0.03250  -0.0105   0.0995   1.0000
   8.500   0.9567   0.04421   0.03578  -0.0088   0.0980   1.0000
   8.750   0.9677   0.04745   0.03944  -0.0071   0.0970   1.0000
   9.000   0.9752   0.05132   0.04371  -0.0053   0.0975   1.0000
   9.250   0.9793   0.05544   0.04820  -0.0035   0.0982   1.0000
   9.500   0.9807   0.05971   0.05278  -0.0018   0.0988   1.0000
   9.750   0.9818   0.06414   0.05744  -0.0004   0.0996   1.0000
  10.000   0.7344   0.10328   0.09796  -0.0191   0.1875   1.0000
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