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NACA 63A010 AIRFOIL (n63010a-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 63A010 AIRFOIL (n63010a-il)
Reynolds number: 500,000
Max Cl/Cd: 51 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n63010a-il-500000-n5.txt
Download as CSV file: xf-n63010a-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.9715   0.06212   0.05959  -0.0152   1.0000   0.0066
 -12.500  -1.0090   0.05253   0.04968  -0.0210   1.0000   0.0065
 -12.250  -1.0246   0.04761   0.04456  -0.0229   1.0000   0.0066
 -12.000  -1.0348   0.04398   0.04073  -0.0233   1.0000   0.0066
 -11.750  -1.0411   0.04115   0.03773  -0.0226   1.0000   0.0067
 -11.500  -1.0423   0.03908   0.03550  -0.0211   1.0000   0.0068
 -11.250  -1.0406   0.03727   0.03353  -0.0193   1.0000   0.0070
 -11.000  -1.0347   0.03539   0.03144  -0.0178   1.0000   0.0072
 -10.750  -1.0266   0.03343   0.02925  -0.0164   1.0000   0.0075
 -10.500  -1.0168   0.03141   0.02699  -0.0150   1.0000   0.0079
 -10.250  -1.0051   0.02939   0.02470  -0.0137   1.0000   0.0082
 -10.000  -0.9911   0.02752   0.02256  -0.0124   1.0000   0.0085
  -9.750  -0.9747   0.02593   0.02073  -0.0113   1.0000   0.0088
  -9.500  -0.9563   0.02465   0.01924  -0.0104   1.0000   0.0090
  -9.250  -0.9409   0.02260   0.01695  -0.0091   1.0000   0.0094
  -9.000  -0.9218   0.02136   0.01558  -0.0083   1.0000   0.0097
  -8.750  -0.9007   0.02052   0.01464  -0.0076   1.0000   0.0101
  -8.500  -0.8785   0.01987   0.01392  -0.0070   1.0000   0.0105
  -8.250  -0.8562   0.01920   0.01317  -0.0064   1.0000   0.0110
  -8.000  -0.8340   0.01844   0.01232  -0.0057   1.0000   0.0116
  -7.750  -0.8121   0.01762   0.01140  -0.0049   1.0000   0.0120
  -7.500  -0.7903   0.01683   0.01050  -0.0041   1.0000   0.0123
  -7.250  -0.7683   0.01612   0.00969  -0.0033   1.0000   0.0127
  -7.000  -0.7461   0.01549   0.00898  -0.0024   1.0000   0.0129
  -6.750  -0.7260   0.01462   0.00804  -0.0012   1.0000   0.0136
  -6.500  -0.7052   0.01395   0.00734  -0.0002   1.0000   0.0144
  -6.250  -0.6836   0.01344   0.00680   0.0008   1.0000   0.0150
  -6.000  -0.6620   0.01298   0.00630   0.0019   1.0000   0.0157
  -5.750  -0.6353   0.01252   0.00578   0.0018   0.9976   0.0164
  -5.500  -0.6026   0.01207   0.00527   0.0005   0.9922   0.0173
  -5.250  -0.5699   0.01167   0.00481  -0.0009   0.9859   0.0182
  -5.000  -0.5382   0.01123   0.00433  -0.0019   0.9779   0.0200
  -4.750  -0.5064   0.01085   0.00395  -0.0030   0.9689   0.0238
  -4.500  -0.4745   0.01053   0.00361  -0.0041   0.9587   0.0290
  -4.250  -0.4435   0.01022   0.00331  -0.0049   0.9467   0.0374
  -4.000  -0.4143   0.00991   0.00302  -0.0053   0.9327   0.0513
  -3.750  -0.3870   0.00959   0.00276  -0.0053   0.9170   0.0738
  -3.500  -0.3614   0.00920   0.00250  -0.0050   0.9008   0.1153
  -3.250  -0.3378   0.00860   0.00220  -0.0045   0.8845   0.2000
  -3.000  -0.3162   0.00775   0.00188  -0.0037   0.8689   0.3394
  -2.750  -0.2928   0.00723   0.00168  -0.0031   0.8542   0.4370
  -2.500  -0.2675   0.00699   0.00156  -0.0026   0.8407   0.4896
  -2.250  -0.2424   0.00676   0.00148  -0.0021   0.8277   0.5461
  -2.000  -0.2171   0.00657   0.00142  -0.0016   0.8156   0.5958
  -1.750  -0.1909   0.00648   0.00138  -0.0012   0.8038   0.6280
  -1.500  -0.1642   0.00642   0.00134  -0.0009   0.7924   0.6507
  -1.250  -0.1372   0.00638   0.00131  -0.0006   0.7813   0.6696
  -1.000  -0.1100   0.00635   0.00127  -0.0005   0.7708   0.6846
  -0.750  -0.0826   0.00635   0.00125  -0.0003   0.7602   0.6960
  -0.500  -0.0550   0.00634   0.00123  -0.0002   0.7493   0.7067
   0.000   0.0000   0.00633   0.00121   0.0000   0.7282   0.7283
   0.500   0.0551   0.00634   0.00123   0.0002   0.7067   0.7493
   0.750   0.0826   0.00635   0.00125   0.0003   0.6959   0.7601
   1.000   0.1100   0.00635   0.00127   0.0005   0.6846   0.7708
   1.250   0.1372   0.00638   0.00131   0.0006   0.6695   0.7813
   1.500   0.1642   0.00642   0.00134   0.0009   0.6507   0.7924
   1.750   0.1910   0.00648   0.00138   0.0012   0.6280   0.8039
   2.000   0.2171   0.00657   0.00142   0.0016   0.5958   0.8156
   2.250   0.2424   0.00676   0.00148   0.0021   0.5453   0.8277
   2.500   0.2676   0.00699   0.00156   0.0026   0.4893   0.8407
   2.750   0.2929   0.00723   0.00168   0.0031   0.4369   0.8541
   3.000   0.3163   0.00774   0.00188   0.0037   0.3402   0.8687
   3.250   0.3380   0.00859   0.00220   0.0044   0.2011   0.8843
   3.500   0.3615   0.00920   0.00250   0.0050   0.1151   0.9007
   3.750   0.3871   0.00959   0.00276   0.0053   0.0738   0.9169
   4.000   0.4143   0.00991   0.00302   0.0053   0.0513   0.9328
   4.250   0.4435   0.01022   0.00331   0.0049   0.0373   0.9467
   4.500   0.4745   0.01053   0.00361   0.0040   0.0290   0.9586
   4.750   0.5064   0.01085   0.00395   0.0030   0.0238   0.9688
   5.000   0.5382   0.01123   0.00433   0.0019   0.0200   0.9779
   5.250   0.5699   0.01167   0.00481   0.0009   0.0182   0.9859
   5.500   0.6026   0.01207   0.00527  -0.0005   0.0173   0.9923
   5.750   0.6353   0.01252   0.00578  -0.0018   0.0164   0.9977
   6.000   0.6620   0.01298   0.00630  -0.0019   0.0156   1.0000
   6.250   0.6836   0.01344   0.00680  -0.0008   0.0150   1.0000
   6.500   0.7052   0.01395   0.00733   0.0002   0.0144   1.0000
   6.750   0.7260   0.01462   0.00804   0.0012   0.0136   1.0000
   7.000   0.7461   0.01549   0.00898   0.0024   0.0129   1.0000
   7.250   0.7683   0.01612   0.00969   0.0033   0.0127   1.0000
   7.500   0.7903   0.01683   0.01051   0.0041   0.0123   1.0000
   7.750   0.8122   0.01762   0.01140   0.0049   0.0120   1.0000
   8.000   0.8341   0.01845   0.01233   0.0057   0.0116   1.0000
   8.250   0.8563   0.01920   0.01318   0.0064   0.0111   1.0000
   8.500   0.8788   0.01987   0.01392   0.0070   0.0105   1.0000
   8.750   0.9009   0.02053   0.01465   0.0075   0.0101   1.0000
   9.000   0.9222   0.02137   0.01560   0.0082   0.0097   1.0000
   9.250   0.9414   0.02260   0.01695   0.0090   0.0094   1.0000
   9.500   0.9567   0.02467   0.01926   0.0103   0.0090   1.0000
   9.750   0.9752   0.02595   0.02075   0.0112   0.0088   1.0000
  10.000   0.9916   0.02754   0.02258   0.0123   0.0085   1.0000
  10.250   1.0056   0.02941   0.02472   0.0136   0.0082   1.0000
  10.500   1.0174   0.03142   0.02699   0.0149   0.0079   1.0000
  10.750   1.0273   0.03344   0.02926   0.0163   0.0075   1.0000
  11.000   1.0354   0.03542   0.03147   0.0176   0.0072   1.0000
  11.250   1.0419   0.03723   0.03349   0.0190   0.0070   1.0000
  11.500   1.0441   0.03901   0.03542   0.0209   0.0068   1.0000
  11.750   1.0421   0.04119   0.03776   0.0223   0.0067   1.0000
  12.000   1.0363   0.04396   0.04071   0.0230   0.0066   1.0000
  12.250   1.0266   0.04755   0.04449   0.0227   0.0066   1.0000
  12.500   1.0114   0.05241   0.04955   0.0208   0.0065   1.0000
  12.750   0.9725   0.06225   0.05972   0.0148   0.0066   1.0000
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