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(3)-018 (naca633018-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 63(3)-018 (naca633018-il)
Reynolds number: 50,000
Max Cl/Cd: 23.42 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca633018-il-50000.txt
Download as CSV file: xf-naca633018-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63(3)-018                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.8204   0.08389   0.07649  -0.0291   1.0000   0.1820
 -12.750  -0.8748   0.07396   0.06645  -0.0328   1.0000   0.1801
 -12.500  -0.9228   0.06660   0.05891  -0.0344   1.0000   0.1786
 -12.250  -0.9587   0.06129   0.05336  -0.0341   1.0000   0.1783
 -12.000  -0.9838   0.05723   0.04905  -0.0328   1.0000   0.1792
 -11.750  -1.0026   0.05389   0.04543  -0.0306   1.0000   0.1806
 -11.500  -1.0171   0.05095   0.04214  -0.0280   1.0000   0.1825
 -11.250  -0.9778   0.04847   0.03978  -0.0294   1.0000   0.1914
 -11.000  -0.9815   0.04601   0.03703  -0.0274   1.0000   0.1968
 -10.750  -0.9485   0.04384   0.03498  -0.0281   1.0000   0.2081
 -10.500  -0.9214   0.04170   0.03285  -0.0284   1.0000   0.2207
 -10.250  -0.8992   0.03990   0.03114  -0.0280   1.0000   0.2375
 -10.000  -0.8849   0.03814   0.02950  -0.0268   1.0000   0.2580
  -9.750  -0.8632   0.03689   0.02864  -0.0257   1.0000   0.2883
  -9.500  -0.8415   0.03686   0.02917  -0.0235   1.0000   0.3299
  -9.250  -0.7748   0.04244   0.03513  -0.0206   1.0000   0.3889
  -9.000  -0.5503   0.06748   0.05951  -0.0119   1.0000   0.4259
  -8.750  -0.5481   0.06614   0.05813  -0.0107   1.0000   0.4502
  -8.500  -0.4752   0.07051   0.06225  -0.0086   1.0000   0.4753
  -8.250  -0.4743   0.06890   0.06063  -0.0076   1.0000   0.4971
  -8.000  -0.4169   0.07034   0.06189  -0.0072   1.0000   0.5202
  -7.750  -0.3943   0.06965   0.06112  -0.0068   1.0000   0.5413
  -7.500  -0.3849   0.06855   0.06000  -0.0060   1.0000   0.5610
  -7.250  -0.3456   0.06827   0.05962  -0.0063   1.0000   0.5833
  -7.000  -0.3209   0.06764   0.05894  -0.0060   1.0000   0.6039
  -6.750  -0.3104   0.06709   0.05839  -0.0046   1.0000   0.6222
  -6.500  -0.3107   0.06687   0.05819  -0.0016   1.0000   0.6370
  -6.250  -0.3496   0.06672   0.05813   0.0047   1.0000   0.6425
  -6.000  -0.3438   0.06651   0.05789   0.0072   1.0000   0.6568
  -5.750  -0.3418   0.06620   0.05757   0.0099   1.0000   0.6704
  -5.500  -0.3772   0.06563   0.05704   0.0156   1.0000   0.6761
  -5.250  -0.3634   0.06518   0.05654   0.0168   1.0000   0.6902
  -5.000  -0.3564   0.06464   0.05597   0.0185   1.0000   0.7029
  -4.750  -0.3841   0.06386   0.05520   0.0235   1.0000   0.7089
  -4.500  -0.3551   0.06312   0.05438   0.0217   0.9972   0.7233
  -4.250  -0.3094   0.06208   0.05320   0.0165   0.9890   0.7396
  -4.000  -0.2618   0.06099   0.05199   0.0108   0.9811   0.7552
  -3.750  -0.2235   0.05997   0.05087   0.0066   0.9727   0.7687
  -3.500  -0.2060   0.05906   0.04988   0.0045   0.9644   0.7756
  -3.250  -0.1580   0.05807   0.04879  -0.0010   0.9563   0.7891
  -3.000  -0.1534   0.05746   0.04813  -0.0007   0.9477   0.7930
  -2.750  -0.0980   0.05645   0.04704  -0.0073   0.9402   0.8055
  -2.500  -0.0981   0.05606   0.04662  -0.0058   0.9316   0.8085
  -2.250  -0.0463   0.05519   0.04569  -0.0120   0.9245   0.8191
  -2.000  -0.0484   0.05497   0.04545  -0.0097   0.9159   0.8218
  -1.750  -0.0424   0.05473   0.04517  -0.0090   0.9088   0.8263
  -1.500  -0.0227   0.05435   0.04479  -0.0097   0.9009   0.8323
  -1.250  -0.0023   0.05406   0.04447  -0.0109   0.8939   0.8376
  -1.000  -0.0199   0.05412   0.04453  -0.0060   0.8870   0.8410
  -0.750  -0.0124   0.05395   0.04435  -0.0049   0.8802   0.8461
  -0.500   0.0162   0.05383   0.04422  -0.0072   0.8739   0.8522
  -0.250  -0.0126   0.05389   0.04428  -0.0003   0.8681   0.8563
   0.000  -0.0003   0.05383   0.04421   0.0001   0.8622   0.8621
   0.250   0.0123   0.05389   0.04427   0.0003   0.8563   0.8680
   0.500  -0.0160   0.05383   0.04421   0.0071   0.8523   0.8738
   0.750   0.0110   0.05394   0.04434   0.0051   0.8462   0.8801
   1.000   0.0199   0.05411   0.04452   0.0059   0.8410   0.8871
   1.250   0.0023   0.05405   0.04447   0.0109   0.8377   0.8939
   1.500   0.0230   0.05434   0.04477   0.0097   0.8322   0.9009
   1.750   0.0417   0.05470   0.04514   0.0091   0.8262   0.9088
   2.000   0.0489   0.05497   0.04545   0.0096   0.8221   0.9160
   2.250   0.0459   0.05516   0.04566   0.0120   0.8191   0.9245
   2.500   0.0984   0.05604   0.04660   0.0057   0.8086   0.9316
   2.750   0.0980   0.05642   0.04701   0.0073   0.8055   0.9402
   3.000   0.1546   0.05745   0.04812   0.0005   0.7933   0.9477
   3.250   0.1582   0.05803   0.04876   0.0009   0.7890   0.9563
   3.500   0.2068   0.05905   0.04986  -0.0046   0.7758   0.9644
   3.750   0.2243   0.05993   0.05083  -0.0067   0.7686   0.9727
   4.000   0.2620   0.06096   0.05195  -0.0108   0.7554   0.9811
   4.250   0.3099   0.06204   0.05316  -0.0166   0.7396   0.9890
   4.500   0.3561   0.06309   0.05434  -0.0219   0.7232   0.9974
   4.750   0.3841   0.06381   0.05515  -0.0235   0.7089   1.0000
   5.000   0.3565   0.06459   0.05592  -0.0185   0.7030   1.0000
   5.250   0.3635   0.06513   0.05649  -0.0168   0.6902   1.0000
   5.500   0.3772   0.06557   0.05697  -0.0156   0.6761   1.0000
   5.750   0.3421   0.06612   0.05749  -0.0099   0.6701   1.0000
   6.000   0.3438   0.06643   0.05781  -0.0072   0.6567   1.0000
   6.250   0.3485   0.06663   0.05804  -0.0046   0.6423   1.0000
   6.500   0.3107   0.06679   0.05811   0.0016   0.6368   1.0000
   6.750   0.3105   0.06704   0.05834   0.0046   0.6222   1.0000
   7.000   0.3211   0.06761   0.05891   0.0060   0.6040   1.0000
   7.250   0.3490   0.06816   0.05951   0.0061   0.5826   1.0000
   7.500   0.3849   0.06853   0.05997   0.0060   0.5609   1.0000
   7.750   0.3950   0.06963   0.06110   0.0067   0.5414   1.0000
   8.000   0.4178   0.07030   0.06184   0.0071   0.5202   1.0000
   8.250   0.4745   0.06890   0.06062   0.0076   0.4970   1.0000
   8.500   0.4760   0.07045   0.06220   0.0085   0.4752   1.0000
   8.750   0.5500   0.06599   0.05798   0.0106   0.4502   1.0000
   9.250   0.7965   0.04039   0.03308   0.0205   0.3833   1.0000
   9.500   0.8418   0.03686   0.02916   0.0235   0.3299   1.0000
   9.750   0.8637   0.03688   0.02863   0.0256   0.2884   1.0000
  10.000   0.8852   0.03814   0.02950   0.0268   0.2579   1.0000
  10.250   0.8997   0.03989   0.03114   0.0279   0.2375   1.0000
  10.500   0.9219   0.04170   0.03285   0.0283   0.2207   1.0000
  10.750   0.9489   0.04385   0.03499   0.0281   0.2081   1.0000
  11.000   0.9815   0.04600   0.03703   0.0274   0.1967   1.0000
  11.250   0.9783   0.04848   0.03979   0.0294   0.1914   1.0000
  11.500   1.0172   0.05095   0.04214   0.0280   0.1825   1.0000
  11.750   1.0029   0.05389   0.04543   0.0306   0.1806   1.0000
  12.000   0.9841   0.05724   0.04906   0.0327   0.1791   1.0000
  12.250   0.9591   0.06129   0.05337   0.0341   0.1783   1.0000
  12.500   0.9237   0.06658   0.05889   0.0343   0.1786   1.0000
  12.750   0.8745   0.07403   0.06652   0.0327   0.1800   1.0000
  13.000   0.8209   0.08394   0.07654   0.0290   0.1820   1.0000
<< Back to NACA 63(3)-018 (naca633018-il)

Polar data table (+)

Polar graphs


<< Back to NACA 63(3)-018 (naca633018-il)