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NASA/AMES A-03 AIRFOIL (ames03-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NASA/AMES A-03 AIRFOIL (ames03-il)
Reynolds number: 1,000,000
Max Cl/Cd: 83.4 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ames03-il-1000000-n5.txt
Download as CSV file: xf-ames03-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/AMES A-03 AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -1.2558   0.05278   0.05043   0.0035   0.8554   0.0056
 -13.500  -1.3030   0.04239   0.03957   0.0027   0.8496   0.0056
 -13.250  -1.3142   0.03954   0.03652   0.0055   0.8465   0.0057
 -13.000  -1.3134   0.03693   0.03370   0.0072   0.8439   0.0058
 -12.750  -1.3068   0.03468   0.03124   0.0086   0.8415   0.0058
 -12.500  -1.2967   0.03264   0.02898   0.0098   0.8393   0.0059
 -12.250  -1.2833   0.03088   0.02702   0.0109   0.8372   0.0060
 -12.000  -1.2673   0.02930   0.02526   0.0118   0.8350   0.0061
 -11.750  -1.2497   0.02784   0.02364   0.0125   0.8326   0.0062
 -11.500  -1.2306   0.02654   0.02217   0.0132   0.8303   0.0062
 -11.250  -1.2098   0.02544   0.02092   0.0137   0.8282   0.0063
 -11.000  -1.1877   0.02451   0.01986   0.0142   0.8262   0.0064
 -10.750  -1.1677   0.02305   0.01822   0.0148   0.8243   0.0066
 -10.250  -1.1218   0.02107   0.01600   0.0156   0.8207   0.0070
 -10.000  -1.0972   0.02034   0.01519   0.0158   0.8186   0.0071
  -9.750  -1.0722   0.01965   0.01441   0.0159   0.8164   0.0073
  -9.500  -1.0468   0.01897   0.01364   0.0161   0.8144   0.0074
  -9.250  -1.0212   0.01833   0.01291   0.0163   0.8125   0.0076
  -9.000  -0.9954   0.01769   0.01218   0.0164   0.8107   0.0078
  -8.750  -0.9692   0.01709   0.01149   0.0165   0.8090   0.0080
  -8.500  -0.9429   0.01651   0.01081   0.0166   0.8074   0.0082
  -8.250  -0.9160   0.01597   0.01019   0.0166   0.8057   0.0084
  -8.000  -0.8890   0.01544   0.00960   0.0166   0.8039   0.0086
  -7.750  -0.8616   0.01499   0.00907   0.0166   0.8019   0.0088
  -7.500  -0.8343   0.01449   0.00851   0.0165   0.8000   0.0091
  -7.250  -0.8071   0.01391   0.00788   0.0165   0.7982   0.0096
  -7.000  -0.7794   0.01352   0.00745   0.0164   0.7966   0.0100
  -6.750  -0.7515   0.01315   0.00703   0.0163   0.7950   0.0103
  -6.500  -0.7234   0.01280   0.00663   0.0162   0.7935   0.0107
  -6.250  -0.6952   0.01246   0.00625   0.0161   0.7920   0.0111
  -6.000  -0.6667   0.01212   0.00588   0.0159   0.7905   0.0115
  -5.750  -0.6381   0.01183   0.00555   0.0157   0.7888   0.0119
  -5.500  -0.6095   0.01148   0.00517   0.0155   0.7871   0.0124
  -5.250  -0.5808   0.01115   0.00483   0.0153   0.7853   0.0131
  -5.000  -0.5520   0.01089   0.00455   0.0151   0.7835   0.0139
  -4.750  -0.5232   0.01066   0.00430   0.0149   0.7812   0.0148
  -4.500  -0.4943   0.01045   0.00405   0.0147   0.7784   0.0156
  -4.250  -0.4652   0.01019   0.00379   0.0144   0.7757   0.0170
  -4.000  -0.4360   0.00996   0.00357   0.0141   0.7727   0.0185
  -3.750  -0.4067   0.00977   0.00337   0.0138   0.7694   0.0200
  -3.500  -0.3774   0.00958   0.00316   0.0136   0.7670   0.0216
  -3.250  -0.3482   0.00939   0.00298   0.0133   0.7643   0.0248
  -3.000  -0.3188   0.00922   0.00281   0.0130   0.7610   0.0275
  -2.750  -0.2892   0.00903   0.00265   0.0126   0.7571   0.0324
  -2.500  -0.2597   0.00886   0.00250   0.0123   0.7535   0.0387
  -2.250  -0.2302   0.00869   0.00236   0.0119   0.7503   0.0487
  -2.000  -0.2007   0.00851   0.00223   0.0116   0.7468   0.0634
  -1.750  -0.1709   0.00832   0.00212   0.0112   0.7418   0.0829
  -1.500  -0.1413   0.00806   0.00199   0.0107   0.7355   0.1216
  -1.250  -0.1115   0.00778   0.00188   0.0102   0.7290   0.1719
  -1.000  -0.0817   0.00748   0.00175   0.0096   0.7183   0.2341
  -0.750  -0.0516   0.00710   0.00163   0.0089   0.7025   0.3231
  -0.500  -0.0213   0.00643   0.00149   0.0079   0.6791   0.4936
  -0.250   0.0096   0.00613   0.00140   0.0070   0.6416   0.5979
   0.000   0.0479   0.00673   0.00155   0.0037   0.4246   0.6951
   0.250   0.0803   0.00696   0.00165   0.0023   0.3356   0.7527
   0.500   0.1112   0.00711   0.00172   0.0015   0.2905   0.7862
   0.750   0.1407   0.00717   0.00180   0.0011   0.2660   0.8249
   1.000   0.1701   0.00725   0.00187   0.0007   0.2497   0.8502
   1.250   0.1998   0.00733   0.00192   0.0003   0.2372   0.8617
   1.500   0.2296   0.00743   0.00197  -0.0001   0.2274   0.8697
   1.750   0.2591   0.00750   0.00203  -0.0005   0.2213   0.8776
   2.000   0.2887   0.00758   0.00209  -0.0009   0.2153   0.8847
   2.250   0.3181   0.00767   0.00216  -0.0012   0.2095   0.8920
   2.500   0.3476   0.00775   0.00223  -0.0016   0.2048   0.8987
   2.750   0.3767   0.00783   0.00230  -0.0019   0.1995   0.9055
   3.000   0.4062   0.00794   0.00238  -0.0023   0.1945   0.9122
   3.250   0.4348   0.00800   0.00246  -0.0025   0.1908   0.9186
   3.500   0.4638   0.00810   0.00255  -0.0027   0.1860   0.9253
   3.750   0.4924   0.00822   0.00265  -0.0030   0.1803   0.9316
   4.000   0.5208   0.00830   0.00274  -0.0031   0.1768   0.9385
   4.250   0.5492   0.00839   0.00284  -0.0033   0.1718   0.9451
   4.500   0.5772   0.00852   0.00294  -0.0034   0.1657   0.9524
   4.750   0.6053   0.00861   0.00304  -0.0035   0.1611   0.9597
   5.000   0.6333   0.00872   0.00315  -0.0036   0.1558   0.9683
   5.250   0.6624   0.00885   0.00327  -0.0040   0.1499   0.9772
   5.500   0.6931   0.00898   0.00339  -0.0048   0.1446   0.9875
   5.750   0.7241   0.00915   0.00354  -0.0057   0.1382   1.0000
   6.000   0.7538   0.00933   0.00372  -0.0063   0.1322   1.0000
   6.250   0.7833   0.00957   0.00391  -0.0069   0.1234   1.0000
   6.500   0.8126   0.00985   0.00412  -0.0076   0.1109   1.0000
   6.750   0.8417   0.01014   0.00436  -0.0081   0.0997   1.0000
   7.000   0.8705   0.01045   0.00462  -0.0087   0.0886   1.0000
   7.250   0.8991   0.01078   0.00490  -0.0092   0.0789   1.0000
   7.500   0.9275   0.01114   0.00521  -0.0097   0.0690   1.0000
   7.750   0.9556   0.01153   0.00556  -0.0102   0.0592   1.0000
   8.000   0.9833   0.01195   0.00593  -0.0106   0.0506   1.0000
   8.250   1.0110   0.01234   0.00629  -0.0110   0.0435   1.0000
   8.500   1.0383   0.01279   0.00670  -0.0114   0.0359   1.0000
   8.750   1.0652   0.01326   0.00714  -0.0117   0.0293   1.0000
   9.000   1.0920   0.01374   0.00759  -0.0119   0.0244   1.0000
   9.250   1.1185   0.01421   0.00806  -0.0122   0.0209   1.0000
   9.500   1.1449   0.01467   0.00852  -0.0124   0.0183   1.0000
   9.750   1.1709   0.01516   0.00903  -0.0126   0.0161   1.0000
  10.000   1.1967   0.01566   0.00955  -0.0127   0.0144   1.0000
  10.250   1.2224   0.01612   0.01005  -0.0128   0.0135   1.0000
  10.500   1.2475   0.01665   0.01061  -0.0129   0.0125   1.0000
  10.750   1.2720   0.01723   0.01122  -0.0129   0.0116   1.0000
  11.000   1.2962   0.01782   0.01186  -0.0128   0.0109   1.0000
  11.250   1.3203   0.01836   0.01246  -0.0128   0.0105   1.0000
  11.500   1.3438   0.01894   0.01310  -0.0127   0.0100   1.0000
  11.750   1.3666   0.01957   0.01378  -0.0125   0.0095   1.0000
  12.000   1.3886   0.02025   0.01451  -0.0123   0.0091   1.0000
  12.250   1.4096   0.02101   0.01533  -0.0120   0.0087   1.0000
  12.500   1.4290   0.02188   0.01627  -0.0115   0.0082   1.0000
  12.750   1.4475   0.02277   0.01724  -0.0109   0.0080   1.0000
  13.000   1.4660   0.02359   0.01814  -0.0105   0.0078   1.0000
  13.250   1.4825   0.02450   0.01914  -0.0099   0.0076   1.0000
  13.500   1.4949   0.02548   0.02020  -0.0087   0.0075   1.0000
  13.750   1.5058   0.02654   0.02135  -0.0074   0.0073   1.0000
  14.000   1.5168   0.02765   0.02254  -0.0062   0.0071   1.0000
  14.250   1.5272   0.02885   0.02382  -0.0051   0.0068   1.0000
  14.500   1.5363   0.03017   0.02522  -0.0040   0.0066   1.0000
  14.750   1.5440   0.03165   0.02677  -0.0030   0.0064   1.0000
  15.000   1.5496   0.03336   0.02857  -0.0020   0.0062   1.0000
  15.250   1.5524   0.03537   0.03067  -0.0010   0.0060   1.0000
  15.500   1.5518   0.03778   0.03320  -0.0002   0.0058   1.0000
  15.750   1.5493   0.04047   0.03602   0.0004   0.0057   1.0000
  16.000   1.5487   0.04311   0.03877   0.0007   0.0056   1.0000
  16.250   1.5461   0.04608   0.04186   0.0007   0.0056   1.0000
  16.500   1.5401   0.04966   0.04557   0.0003   0.0055   1.0000
  16.750   1.5294   0.05414   0.05019  -0.0009   0.0055   1.0000
  17.000   1.5143   0.05982   0.05604  -0.0032   0.0054   1.0000
  17.250   1.4876   0.06860   0.06502  -0.0081   0.0055   1.0000
  17.500   1.4338   0.08432   0.08105  -0.0176   0.0056   1.0000
  17.750   1.3510   0.10428   0.10128  -0.0279   0.0057   1.0000
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