Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 63-015A AIRFOIL (n63015a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 63-015A AIRFOIL (n63015a-il)
Reynolds number: 1,000,000
Max Cl/Cd: 66.87 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n63015a-il-1000000-n5.txt
Download as CSV file: xf-n63015a-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-015A 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
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.1886   0.11333   0.11008  -0.0016   1.0000   0.0091
 -19.500  -1.2064   0.10639   0.10301  -0.0050   1.0000   0.0092
 -19.250  -1.2241   0.09963   0.09614  -0.0081   1.0000   0.0092
 -19.000  -1.2404   0.09331   0.08970  -0.0110   1.0000   0.0093
 -18.750  -1.2547   0.08737   0.08365  -0.0136   1.0000   0.0093
 -18.500  -1.2681   0.08173   0.07790  -0.0160   1.0000   0.0094
 -18.250  -1.2798   0.07652   0.07258  -0.0181   1.0000   0.0094
 -18.000  -1.2895   0.07168   0.06763  -0.0199   1.0000   0.0095
 -17.750  -1.2975   0.06720   0.06305  -0.0215   1.0000   0.0096
 -17.500  -1.3042   0.06304   0.05879  -0.0229   1.0000   0.0096
 -17.250  -1.3092   0.05921   0.05487  -0.0240   1.0000   0.0097
 -17.000  -1.3127   0.05564   0.05121  -0.0250   1.0000   0.0097
 -16.750  -1.3148   0.05237   0.04785  -0.0257   1.0000   0.0098
 -16.500  -1.3157   0.04936   0.04475  -0.0263   1.0000   0.0099
 -16.250  -1.3156   0.04653   0.04184  -0.0267   1.0000   0.0099
 -16.000  -1.3143   0.04392   0.03915  -0.0269   1.0000   0.0100
 -15.750  -1.3119   0.04151   0.03666  -0.0270   1.0000   0.0101
 -15.500  -1.3081   0.03927   0.03434  -0.0270   1.0000   0.0102
 -15.250  -1.3034   0.03717   0.03217  -0.0269   1.0000   0.0102
 -15.000  -1.2977   0.03523   0.03015  -0.0267   1.0000   0.0103
 -14.750  -1.2910   0.03340   0.02825  -0.0264   1.0000   0.0104
 -14.500  -1.2834   0.03169   0.02647  -0.0260   1.0000   0.0105
 -14.250  -1.2750   0.03011   0.02482  -0.0256   1.0000   0.0106
 -14.000  -1.2654   0.02864   0.02328  -0.0251   1.0000   0.0107
 -13.750  -1.2550   0.02730   0.02188  -0.0245   1.0000   0.0109
 -13.500  -1.2438   0.02605   0.02057  -0.0238   1.0000   0.0110
 -13.250  -1.2320   0.02489   0.01934  -0.0231   1.0000   0.0111
 -13.000  -1.2199   0.02380   0.01820  -0.0223   1.0000   0.0113
 -12.750  -1.2072   0.02278   0.01712  -0.0214   1.0000   0.0114
 -12.500  -1.1940   0.02185   0.01613  -0.0204   1.0000   0.0114
 -12.250  -1.1801   0.02100   0.01523  -0.0193   1.0000   0.0115
 -12.000  -1.1657   0.02023   0.01440  -0.0182   1.0000   0.0116
 -11.750  -1.1516   0.01947   0.01359  -0.0169   1.0000   0.0117
 -11.500  -1.1384   0.01870   0.01278  -0.0153   1.0000   0.0120
 -11.250  -1.1241   0.01804   0.01208  -0.0137   1.0000   0.0122
 -11.000  -1.1091   0.01746   0.01148  -0.0121   1.0000   0.0125
 -10.750  -1.0938   0.01695   0.01094  -0.0104   1.0000   0.0127
 -10.500  -1.0767   0.01648   0.01043  -0.0089   1.0000   0.0130
 -10.250  -1.0586   0.01603   0.00996  -0.0076   1.0000   0.0133
 -10.000  -1.0380   0.01559   0.00951  -0.0067   0.9977   0.0136
  -9.750  -1.0086   0.01513   0.00902  -0.0077   0.9861   0.0141
  -9.500  -0.9784   0.01470   0.00855  -0.0088   0.9723   0.0145
  -9.250  -0.9513   0.01424   0.00806  -0.0092   0.9523   0.0154
  -9.000  -0.9282   0.01388   0.00765  -0.0086   0.9281   0.0162
  -8.750  -0.9065   0.01358   0.00727  -0.0076   0.9033   0.0171
  -8.500  -0.8841   0.01332   0.00691  -0.0068   0.8813   0.0180
  -8.250  -0.8614   0.01302   0.00655  -0.0060   0.8620   0.0195
  -8.000  -0.8379   0.01275   0.00622  -0.0055   0.8450   0.0213
  -7.500  -0.7895   0.01222   0.00559  -0.0045   0.8162   0.0258
  -7.250  -0.7647   0.01197   0.00530  -0.0042   0.8043   0.0284
  -7.000  -0.7398   0.01172   0.00502  -0.0038   0.7935   0.0319
  -6.750  -0.7148   0.01146   0.00475  -0.0035   0.7830   0.0363
  -6.500  -0.6895   0.01121   0.00449  -0.0032   0.7741   0.0419
  -6.250  -0.6642   0.01096   0.00424  -0.0029   0.7648   0.0491
  -6.000  -0.6387   0.01070   0.00399  -0.0027   0.7566   0.0580
  -5.750  -0.6132   0.01045   0.00376  -0.0024   0.7483   0.0685
  -5.500  -0.5876   0.01018   0.00353  -0.0022   0.7408   0.0816
  -5.250  -0.5624   0.00989   0.00329  -0.0019   0.7327   0.1002
  -5.000  -0.5376   0.00953   0.00305  -0.0016   0.7257   0.1275
  -4.500  -0.4888   0.00875   0.00255  -0.0008   0.7110   0.2040
  -4.250  -0.4639   0.00838   0.00233  -0.0005   0.7036   0.2425
  -4.000  -0.4398   0.00797   0.00210   0.0000   0.6967   0.2930
  -3.750  -0.4162   0.00748   0.00187   0.0005   0.6897   0.3587
  -3.500  -0.3909   0.00720   0.00172   0.0008   0.6823   0.4010
  -3.250  -0.3638   0.00705   0.00163   0.0009   0.6759   0.4254
  -3.000  -0.3365   0.00693   0.00154   0.0009   0.6686   0.4444
  -2.750  -0.3089   0.00684   0.00147   0.0009   0.6619   0.4608
  -2.500  -0.2815   0.00673   0.00141   0.0009   0.6548   0.4818
  -2.250  -0.2541   0.00665   0.00136   0.0009   0.6481   0.5012
  -2.000  -0.2261   0.00658   0.00131   0.0009   0.6412   0.5145
  -1.750  -0.1982   0.00653   0.00127   0.0008   0.6341   0.5276
  -1.500  -0.1700   0.00649   0.00124   0.0007   0.6276   0.5393
  -1.250  -0.1418   0.00646   0.00121   0.0006   0.6204   0.5505
  -1.000  -0.1138   0.00643   0.00119   0.0006   0.6139   0.5593
  -0.750  -0.0851   0.00642   0.00117   0.0004   0.6070   0.5664
  -0.250  -0.0284   0.00640   0.00115   0.0001   0.5935   0.5801
   0.000   0.0000   0.00640   0.00115   0.0000   0.5865   0.5865
   0.250   0.0284   0.00640   0.00115  -0.0001   0.5801   0.5935
   0.750   0.0852   0.00642   0.00117  -0.0004   0.5664   0.6070
   1.000   0.1138   0.00643   0.00119  -0.0006   0.5593   0.6139
   1.250   0.1419   0.00646   0.00121  -0.0006   0.5505   0.6204
   1.500   0.1701   0.00649   0.00124  -0.0007   0.5393   0.6276
   1.750   0.1982   0.00653   0.00127  -0.0008   0.5275   0.6341
   2.000   0.2261   0.00658   0.00131  -0.0009   0.5146   0.6411
   2.250   0.2541   0.00665   0.00136  -0.0009   0.5011   0.6480
   2.500   0.2815   0.00673   0.00141  -0.0009   0.4817   0.6548
   2.750   0.3089   0.00684   0.00147  -0.0009   0.4610   0.6620
   3.000   0.3365   0.00693   0.00154  -0.0009   0.4442   0.6687
   3.250   0.3638   0.00705   0.00163  -0.0009   0.4254   0.6759
   3.500   0.3908   0.00721   0.00173  -0.0008   0.4001   0.6824
   3.750   0.4162   0.00748   0.00187  -0.0005   0.3587   0.6897
   4.000   0.4398   0.00797   0.00210   0.0000   0.2931   0.6967
   4.250   0.4639   0.00838   0.00233   0.0005   0.2428   0.7036
   4.500   0.4888   0.00874   0.00255   0.0008   0.2043   0.7110
   4.750   0.5129   0.00916   0.00280   0.0013   0.1615   0.7181
   5.000   0.5375   0.00954   0.00305   0.0016   0.1272   0.7257
   5.250   0.5624   0.00989   0.00329   0.0019   0.1001   0.7328
   5.500   0.5876   0.01018   0.00353   0.0022   0.0815   0.7409
   5.750   0.6131   0.01045   0.00376   0.0025   0.0683   0.7484
   6.000   0.6386   0.01070   0.00399   0.0027   0.0580   0.7566
   6.250   0.6641   0.01096   0.00424   0.0030   0.0491   0.7648
   6.500   0.6895   0.01121   0.00449   0.0032   0.0419   0.7740
   6.750   0.7148   0.01146   0.00475   0.0035   0.0363   0.7831
   7.000   0.7398   0.01172   0.00502   0.0038   0.0319   0.7936
   7.250   0.7646   0.01197   0.00530   0.0042   0.0285   0.8044
   7.500   0.7894   0.01222   0.00559   0.0045   0.0258   0.8163
   8.000   0.8378   0.01275   0.00622   0.0055   0.0213   0.8450
   8.250   0.8613   0.01302   0.00655   0.0061   0.0195   0.8621
   8.500   0.8840   0.01331   0.00691   0.0068   0.0180   0.8814
   8.750   0.9065   0.01358   0.00727   0.0076   0.0171   0.9034
   9.000   0.9282   0.01388   0.00765   0.0086   0.0162   0.9282
   9.250   0.9513   0.01424   0.00806   0.0092   0.0153   0.9523
   9.500   0.9785   0.01470   0.00855   0.0088   0.0146   0.9724
   9.750   1.0087   0.01513   0.00901   0.0077   0.0141   0.9862
  10.000   1.0381   0.01559   0.00951   0.0067   0.0136   0.9978
  10.250   1.0587   0.01603   0.00996   0.0076   0.0133   1.0000
  10.500   1.0769   0.01648   0.01043   0.0089   0.0130   1.0000
  10.750   1.0940   0.01695   0.01094   0.0103   0.0127   1.0000
  11.000   1.1094   0.01746   0.01147   0.0120   0.0125   1.0000
  11.250   1.1244   0.01804   0.01208   0.0136   0.0122   1.0000
  11.500   1.1389   0.01869   0.01277   0.0152   0.0120   1.0000
  11.750   1.1522   0.01946   0.01359   0.0168   0.0117   1.0000
  12.000   1.1663   0.02023   0.01440   0.0181   0.0116   1.0000
  12.250   1.1808   0.02100   0.01522   0.0192   0.0115   1.0000
  12.500   1.1947   0.02185   0.01613   0.0203   0.0115   1.0000
  12.750   1.2080   0.02277   0.01711   0.0212   0.0114   1.0000
  13.000   1.2207   0.02378   0.01818   0.0222   0.0113   1.0000
  13.250   1.2329   0.02487   0.01933   0.0230   0.0111   1.0000
  13.500   1.2448   0.02603   0.02054   0.0237   0.0110   1.0000
  13.750   1.2560   0.02727   0.02186   0.0243   0.0109   1.0000
  14.000   1.2666   0.02861   0.02326   0.0249   0.0107   1.0000
  14.250   1.2762   0.03007   0.02478   0.0254   0.0106   1.0000
  14.500   1.2846   0.03166   0.02644   0.0258   0.0105   1.0000
  14.750   1.2923   0.03336   0.02821   0.0262   0.0104   1.0000
  15.000   1.2992   0.03518   0.03009   0.0265   0.0103   1.0000
  15.250   1.3050   0.03713   0.03212   0.0267   0.0102   1.0000
  15.500   1.3099   0.03921   0.03427   0.0268   0.0102   1.0000
  15.750   1.3138   0.04144   0.03658   0.0268   0.0101   1.0000
  16.000   1.3162   0.04386   0.03908   0.0267   0.0100   1.0000
  16.250   1.3175   0.04645   0.04176   0.0264   0.0099   1.0000
  16.500   1.3178   0.04927   0.04466   0.0260   0.0099   1.0000
  16.750   1.3169   0.05229   0.04777   0.0255   0.0098   1.0000
  17.000   1.3149   0.05554   0.05111   0.0247   0.0097   1.0000
  17.250   1.3114   0.05911   0.05477   0.0238   0.0097   1.0000
  17.500   1.3065   0.06294   0.05869   0.0226   0.0096   1.0000
  17.750   1.3000   0.06708   0.06293   0.0213   0.0095   1.0000
  18.000   1.2918   0.07158   0.06754   0.0197   0.0095   1.0000
  18.250   1.2821   0.07644   0.07249   0.0178   0.0094   1.0000
  18.500   1.2705   0.08163   0.07780   0.0157   0.0094   1.0000
  18.750   1.2569   0.08731   0.08359   0.0133   0.0093   1.0000
  19.000   1.2424   0.09328   0.08967   0.0107   0.0093   1.0000
  19.250   1.2262   0.09962   0.09612   0.0078   0.0092   1.0000
<< Back to NACA 63-015A AIRFOIL (n63015a-il)

Polar data table (+)

Polar graphs


<< Back to NACA 63-015A AIRFOIL (n63015a-il)