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NACA 63-210 AIRFOIL (n63210-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 63-210 AIRFOIL (n63210-il)
Reynolds number: 500,000
Max Cl/Cd: 55.8 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n63210-il-500000-n5.txt
Download as CSV file: xf-n63210-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-210 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.9148   0.04026   0.03732  -0.0458   1.0000   0.0052
 -11.250  -0.9486   0.03396   0.03050  -0.0435   1.0000   0.0053
 -11.000  -0.9533   0.02981   0.02590  -0.0421   1.0000   0.0054
 -10.750  -0.9461   0.02697   0.02270  -0.0410   1.0000   0.0056
 -10.500  -0.9347   0.02454   0.01992  -0.0400   1.0000   0.0058
 -10.250  -0.9190   0.02272   0.01784  -0.0392   1.0000   0.0060
 -10.000  -0.8998   0.02151   0.01646  -0.0386   1.0000   0.0063
  -9.750  -0.8770   0.02101   0.01592  -0.0382   1.0000   0.0067
  -9.500  -0.8525   0.02089   0.01582  -0.0380   1.0000   0.0071
  -9.250  -0.8264   0.02121   0.01620  -0.0380   1.0000   0.0075
  -9.000  -0.8024   0.02106   0.01603  -0.0377   1.0000   0.0080
  -8.750  -0.7800   0.02047   0.01535  -0.0373   1.0000   0.0086
  -8.500  -0.7591   0.01927   0.01392  -0.0364   1.0000   0.0112
  -8.250  -0.7356   0.01898   0.01347  -0.0358   1.0000   0.0123
  -8.000  -0.7148   0.01822   0.01261  -0.0350   1.0000   0.0130
  -7.750  -0.6864   0.01773   0.01211  -0.0358   0.9962   0.0139
  -7.500  -0.6540   0.01735   0.01166  -0.0373   0.9901   0.0149
  -7.250  -0.6209   0.01691   0.01114  -0.0389   0.9845   0.0159
  -7.000  -0.5888   0.01650   0.01066  -0.0402   0.9776   0.0170
  -6.750  -0.5569   0.01614   0.01021  -0.0414   0.9699   0.0178
  -6.500  -0.5253   0.01588   0.00987  -0.0424   0.9614   0.0183
  -6.250  -0.4979   0.01492   0.00879  -0.0427   0.9501   0.0189
  -6.000  -0.4729   0.01396   0.00773  -0.0425   0.9353   0.0197
  -5.750  -0.4481   0.01334   0.00704  -0.0421   0.9151   0.0204
  -5.250  -0.3989   0.01239   0.00587  -0.0409   0.8781   0.0204
  -4.750  -0.3477   0.01163   0.00488  -0.0402   0.8558   0.0202
  -4.500  -0.3213   0.01129   0.00447  -0.0400   0.8467   0.0201
  -4.250  -0.2947   0.01099   0.00408  -0.0399   0.8380   0.0200
  -4.000  -0.2675   0.01069   0.00372  -0.0398   0.8292   0.0200
  -3.750  -0.2404   0.01043   0.00340  -0.0398   0.8209   0.0200
  -3.500  -0.2130   0.01019   0.00310  -0.0398   0.8118   0.0199
  -3.250  -0.1854   0.00997   0.00283  -0.0398   0.8031   0.0200
  -3.000  -0.1578   0.00979   0.00257  -0.0397   0.7943   0.0200
  -2.750  -0.1300   0.00961   0.00234  -0.0398   0.7851   0.0202
  -2.500  -0.1022   0.00947   0.00214  -0.0398   0.7765   0.0204
  -2.250  -0.0743   0.00934   0.00196  -0.0398   0.7676   0.0207
  -2.000  -0.0463   0.00923   0.00179  -0.0398   0.7588   0.0213
  -1.750  -0.0184   0.00914   0.00166  -0.0398   0.7505   0.0224
  -1.500   0.0098   0.00904   0.00155  -0.0399   0.7416   0.0246
  -1.250   0.0358   0.00762   0.00120  -0.0407   0.7333   0.3342
  -1.000   0.0630   0.00707   0.00112  -0.0410   0.7246   0.4763
  -0.750   0.0908   0.00686   0.00116  -0.0411   0.7162   0.5509
  -0.500   0.1190   0.00686   0.00116  -0.0412   0.7078   0.5840
  -0.250   0.1473   0.00682   0.00115  -0.0413   0.6989   0.6044
   0.000   0.1755   0.00679   0.00115  -0.0413   0.6906   0.6162
   0.250   0.2026   0.00671   0.00116  -0.0411   0.6692   0.6450
   0.500   0.2292   0.00674   0.00119  -0.0408   0.6381   0.6787
   0.750   0.2570   0.00680   0.00122  -0.0408   0.6194   0.6934
   1.000   0.2849   0.00687   0.00125  -0.0408   0.5993   0.7041
   1.250   0.3125   0.00695   0.00130  -0.0407   0.5778   0.7146
   1.500   0.3399   0.00707   0.00135  -0.0406   0.5494   0.7249
   1.750   0.3669   0.00725   0.00142  -0.0405   0.5112   0.7355
   2.000   0.3914   0.00779   0.00157  -0.0401   0.4102   0.7466
   2.250   0.4134   0.00883   0.00194  -0.0396   0.2405   0.7577
   2.500   0.4345   0.01012   0.00245  -0.0391   0.0504   0.7687
   2.750   0.4609   0.01044   0.00268  -0.0389   0.0244   0.7799
   3.250   0.5149   0.01078   0.00310  -0.0386   0.0207   0.8020
   3.500   0.5416   0.01095   0.00334  -0.0385   0.0203   0.8128
   3.750   0.5682   0.01115   0.00360  -0.0382   0.0200   0.8235
   4.000   0.5945   0.01137   0.00390  -0.0380   0.0196   0.8356
   4.250   0.6203   0.01161   0.00422  -0.0376   0.0192   0.8482
   4.500   0.6455   0.01188   0.00456  -0.0371   0.0189   0.8600
   4.750   0.6702   0.01218   0.00494  -0.0365   0.0185   0.8729
   5.000   0.6941   0.01250   0.00537  -0.0357   0.0182   0.8875
   5.250   0.7172   0.01286   0.00581  -0.0348   0.0179   0.9038
   5.500   0.7394   0.01325   0.00629  -0.0338   0.0177   0.9221
   5.750   0.7610   0.01366   0.00678  -0.0326   0.0175   0.9423
   6.000   0.7859   0.01415   0.00735  -0.0322   0.0173   0.9673
   6.250   0.8130   0.01475   0.00803  -0.0324   0.0172   1.0000
   6.500   0.8372   0.01541   0.00874  -0.0320   0.0171   1.0000
   6.750   0.8611   0.01611   0.00950  -0.0316   0.0171   1.0000
   7.000   0.8845   0.01689   0.01035  -0.0311   0.0170   1.0000
   7.250   0.9078   0.01770   0.01123  -0.0306   0.0170   1.0000
   7.500   0.9314   0.01844   0.01206  -0.0302   0.0167   1.0000
   7.750   0.9550   0.01906   0.01272  -0.0299   0.0159   1.0000
   8.000   0.9778   0.01981   0.01350  -0.0295   0.0152   1.0000
   8.250   0.9990   0.02095   0.01471  -0.0289   0.0146   1.0000
   8.500   1.0197   0.02240   0.01628  -0.0282   0.0142   1.0000
   8.750   1.0389   0.02444   0.01851  -0.0274   0.0138   1.0000
   9.000   1.0620   0.02463   0.01881  -0.0270   0.0135   1.0000
   9.250   1.0844   0.02499   0.01927  -0.0265   0.0131   1.0000
   9.500   1.1061   0.02546   0.01984  -0.0260   0.0125   1.0000
   9.750   1.1267   0.02610   0.02059  -0.0253   0.0119   1.0000
  10.000   1.1462   0.02687   0.02147  -0.0246   0.0113   1.0000
  10.250   1.1652   0.02753   0.02222  -0.0238   0.0107   1.0000
  10.500   1.1837   0.02805   0.02282  -0.0230   0.0102   1.0000
  10.750   1.2017   0.02849   0.02332  -0.0221   0.0098   1.0000
  11.000   1.2188   0.02885   0.02369  -0.0211   0.0094   1.0000
  11.250   1.2315   0.02974   0.02467  -0.0196   0.0091   1.0000
  11.500   1.2378   0.03220   0.02755  -0.0174   0.0078   1.0000
  11.750   1.2437   0.03381   0.02936  -0.0154   0.0068   1.0000
  12.000   1.2548   0.03448   0.03010  -0.0140   0.0063   1.0000
  12.250   1.2618   0.03572   0.03144  -0.0125   0.0061   1.0000
  12.500   1.2709   0.03676   0.03257  -0.0114   0.0058   1.0000
  12.750   1.2822   0.03756   0.03340  -0.0106   0.0056   1.0000
  13.000   1.2930   0.03849   0.03437  -0.0100   0.0054   1.0000
  13.250   1.3047   0.03940   0.03532  -0.0095   0.0051   1.0000
  13.500   1.3092   0.04125   0.03725  -0.0090   0.0050   1.0000
  13.750   1.3177   0.04268   0.03870  -0.0088   0.0048   1.0000
  14.000   1.3198   0.04500   0.04113  -0.0087   0.0046   1.0000
  14.250   1.3184   0.04786   0.04410  -0.0089   0.0044   1.0000
  14.500   1.3125   0.05148   0.04788  -0.0096   0.0044   1.0000
  14.750   1.3049   0.05556   0.05213  -0.0108   0.0043   1.0000
  15.000   1.2940   0.06038   0.05711  -0.0126   0.0042   1.0000
  15.250   1.2787   0.06626   0.06315  -0.0154   0.0041   1.0000
  15.500   1.2592   0.07333   0.07044  -0.0192   0.0042   1.0000
  15.750   1.2352   0.08196   0.07929  -0.0243   0.0042   1.0000
  16.000   1.1886   0.09665   0.09431  -0.0336   0.0044   1.0000
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