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NACA 63A010 AIRFOIL (n63010a-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 63A010 AIRFOIL (n63010a-il)
Reynolds number: 200,000
Max Cl/Cd: 39.2 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n63010a-il-200000-n5.txt
Download as CSV file: xf-n63010a-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63A010 AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7834   0.07830   0.07478  -0.0101   1.0000   0.0137
 -11.000  -0.8266   0.06531   0.06151  -0.0198   1.0000   0.0133
 -10.750  -0.8488   0.05928   0.05526  -0.0229   1.0000   0.0133
 -10.500  -0.8675   0.05474   0.05049  -0.0234   1.0000   0.0133
 -10.250  -0.8832   0.05097   0.04649  -0.0221   1.0000   0.0133
 -10.000  -0.8920   0.04742   0.04269  -0.0205   1.0000   0.0135
  -9.750  -0.8929   0.04433   0.03934  -0.0190   1.0000   0.0137
  -9.500  -0.8860   0.04221   0.03701  -0.0179   1.0000   0.0141
  -9.250  -0.8754   0.04043   0.03505  -0.0169   1.0000   0.0147
  -9.000  -0.8641   0.03836   0.03276  -0.0158   1.0000   0.0154
  -8.750  -0.8532   0.03565   0.02969  -0.0144   1.0000   0.0161
  -8.500  -0.8408   0.03272   0.02634  -0.0128   1.0000   0.0166
  -8.250  -0.8252   0.03015   0.02339  -0.0115   1.0000   0.0170
  -8.000  -0.8070   0.02800   0.02088  -0.0103   1.0000   0.0175
  -7.750  -0.7869   0.02623   0.01882  -0.0093   1.0000   0.0181
  -7.500  -0.7659   0.02483   0.01716  -0.0084   1.0000   0.0189
  -7.250  -0.7458   0.02306   0.01528  -0.0075   1.0000   0.0200
  -7.000  -0.7243   0.02185   0.01398  -0.0067   1.0000   0.0208
  -6.750  -0.7026   0.02072   0.01275  -0.0058   1.0000   0.0215
  -6.500  -0.6811   0.01968   0.01163  -0.0049   1.0000   0.0224
  -6.250  -0.6599   0.01873   0.01060  -0.0038   1.0000   0.0234
  -6.000  -0.6390   0.01786   0.00963  -0.0027   1.0000   0.0245
  -5.750  -0.6178   0.01717   0.00886  -0.0016   1.0000   0.0259
  -5.500  -0.5984   0.01632   0.00797  -0.0003   1.0000   0.0280
  -5.250  -0.5786   0.01561   0.00724   0.0009   1.0000   0.0304
  -5.000  -0.5581   0.01502   0.00660   0.0021   1.0000   0.0332
  -4.750  -0.5371   0.01453   0.00600   0.0033   1.0000   0.0367
  -4.500  -0.5171   0.01394   0.00544   0.0045   1.0000   0.0441
  -4.250  -0.4951   0.01346   0.00498   0.0053   0.9993   0.0570
  -4.000  -0.4614   0.01271   0.00447   0.0034   0.9923   0.1025
  -3.750  -0.4306   0.01145   0.00389   0.0016   0.9847   0.2447
  -3.500  -0.4027   0.01027   0.00354   0.0006   0.9753   0.4257
  -3.250  -0.3723   0.00982   0.00339  -0.0002   0.9652   0.5137
  -3.000  -0.3417   0.00953   0.00332  -0.0008   0.9549   0.5777
  -2.750  -0.3109   0.00934   0.00326  -0.0013   0.9447   0.6310
  -2.500  -0.2799   0.00922   0.00325  -0.0018   0.9346   0.6730
  -2.250  -0.2502   0.00914   0.00320  -0.0019   0.9227   0.6984
  -2.000  -0.2207   0.00908   0.00310  -0.0021   0.9106   0.7174
  -1.750  -0.1916   0.00902   0.00302  -0.0021   0.8985   0.7320
  -1.500  -0.1630   0.00896   0.00294  -0.0021   0.8862   0.7438
  -1.250  -0.1350   0.00891   0.00287  -0.0019   0.8741   0.7554
  -1.000  -0.1074   0.00888   0.00279  -0.0016   0.8619   0.7669
  -0.750  -0.0804   0.00885   0.00274  -0.0013   0.8496   0.7786
  -0.500  -0.0536   0.00883   0.00271  -0.0009   0.8372   0.7906
  -0.250  -0.0268   0.00882   0.00269  -0.0004   0.8252   0.8021
   0.000   0.0000   0.00881   0.00269   0.0000   0.8135   0.8135
   0.250   0.0268   0.00882   0.00269   0.0004   0.8021   0.8252
   0.500   0.0536   0.00883   0.00271   0.0009   0.7906   0.8372
   0.750   0.0804   0.00885   0.00274   0.0013   0.7786   0.8496
   1.000   0.1075   0.00888   0.00279   0.0016   0.7669   0.8619
   1.250   0.1350   0.00891   0.00287   0.0019   0.7554   0.8741
   1.500   0.1630   0.00896   0.00294   0.0021   0.7438   0.8862
   1.750   0.1916   0.00902   0.00302   0.0021   0.7319   0.8985
   2.000   0.2207   0.00908   0.00310   0.0021   0.7174   0.9106
   2.250   0.2502   0.00914   0.00320   0.0019   0.6984   0.9227
   2.500   0.2798   0.00922   0.00325   0.0018   0.6730   0.9346
   2.750   0.3108   0.00934   0.00326   0.0013   0.6310   0.9447
   3.000   0.3417   0.00953   0.00332   0.0008   0.5777   0.9549
   3.250   0.3723   0.00981   0.00339   0.0002   0.5138   0.9652
   3.500   0.4026   0.01027   0.00353  -0.0005   0.4258   0.9753
   3.750   0.4306   0.01144   0.00389  -0.0016   0.2451   0.9847
   4.000   0.4613   0.01271   0.00447  -0.0034   0.1026   0.9923
   4.250   0.4951   0.01346   0.00498  -0.0053   0.0569   0.9993
   4.500   0.5170   0.01394   0.00544  -0.0045   0.0441   1.0000
   4.750   0.5370   0.01453   0.00600  -0.0033   0.0367   1.0000
   5.000   0.5580   0.01502   0.00660  -0.0021   0.0332   1.0000
   5.250   0.5785   0.01560   0.00724  -0.0009   0.0304   1.0000
   5.500   0.5983   0.01632   0.00797   0.0003   0.0280   1.0000
   5.750   0.6178   0.01717   0.00886   0.0016   0.0259   1.0000
   6.000   0.6390   0.01786   0.00963   0.0027   0.0245   1.0000
   6.250   0.6599   0.01873   0.01060   0.0038   0.0234   1.0000
   6.500   0.6811   0.01968   0.01163   0.0049   0.0224   1.0000
   6.750   0.7026   0.02072   0.01275   0.0058   0.0215   1.0000
   7.000   0.7243   0.02185   0.01398   0.0067   0.0208   1.0000
   7.250   0.7459   0.02306   0.01528   0.0075   0.0200   1.0000
   7.500   0.7659   0.02483   0.01715   0.0084   0.0189   1.0000
   7.750   0.7870   0.02623   0.01882   0.0093   0.0181   1.0000
   8.000   0.8071   0.02800   0.02089   0.0103   0.0175   1.0000
   8.250   0.8253   0.03016   0.02339   0.0115   0.0170   1.0000
   8.500   0.8409   0.03272   0.02635   0.0128   0.0166   1.0000
   8.750   0.8533   0.03565   0.02969   0.0143   0.0161   1.0000
   9.000   0.8642   0.03838   0.03278   0.0158   0.0154   1.0000
   9.250   0.8754   0.04046   0.03509   0.0169   0.0147   1.0000
   9.500   0.8861   0.04223   0.03704   0.0179   0.0141   1.0000
   9.750   0.8930   0.04435   0.03937   0.0190   0.0137   1.0000
  10.000   0.8922   0.04745   0.04272   0.0204   0.0135   1.0000
  10.250   0.8835   0.05099   0.04652   0.0220   0.0133   1.0000
  10.500   0.8678   0.05477   0.05053   0.0233   0.0133   1.0000
  10.750   0.8491   0.05934   0.05532   0.0227   0.0133   1.0000
  11.000   0.8270   0.06537   0.06158   0.0196   0.0133   1.0000
  11.250   0.7814   0.07918   0.07568   0.0093   0.0138   1.0000
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