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NACA 63-210 AIRFOIL (n63210-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 63-210 AIRFOIL (n63210-il)
Reynolds number: 200,000
Max Cl/Cd: 48.69 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n63210-il-200000-n5.txt
Download as CSV file: xf-n63210-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.6022   0.08750   0.08397  -0.0195   1.0000   0.0142
 -10.250  -0.6864   0.05894   0.05523  -0.0398   1.0000   0.0127
 -10.000  -0.7079   0.05365   0.04979  -0.0429   1.0000   0.0128
  -9.750  -0.7270   0.04971   0.04568  -0.0430   1.0000   0.0128
  -9.500  -0.7361   0.04603   0.04177  -0.0428   1.0000   0.0129
  -9.250  -0.7344   0.04340   0.03897  -0.0424   1.0000   0.0132
  -9.000  -0.7295   0.04075   0.03610  -0.0419   1.0000   0.0136
  -8.750  -0.7210   0.03824   0.03336  -0.0413   1.0000   0.0141
  -8.500  -0.7108   0.03562   0.03045  -0.0405   1.0000   0.0149
  -8.250  -0.6988   0.03291   0.02736  -0.0396   1.0000   0.0164
  -8.000  -0.6839   0.03061   0.02455  -0.0385   1.0000   0.0181
  -7.750  -0.6710   0.02757   0.02114  -0.0375   1.0000   0.0197
  -7.500  -0.6527   0.02619   0.01961  -0.0367   1.0000   0.0210
  -7.250  -0.6337   0.02487   0.01809  -0.0357   1.0000   0.0224
  -7.000  -0.6141   0.02380   0.01681  -0.0347   1.0000   0.0241
  -6.750  -0.5938   0.02312   0.01590  -0.0336   1.0000   0.0260
  -6.500  -0.5754   0.02167   0.01429  -0.0325   1.0000   0.0276
  -6.250  -0.5490   0.02063   0.01320  -0.0329   0.9968   0.0291
  -6.000  -0.5153   0.01943   0.01182  -0.0345   0.9906   0.0294
  -5.750  -0.4807   0.01826   0.01052  -0.0362   0.9852   0.0294
  -5.500  -0.4478   0.01727   0.00944  -0.0375   0.9780   0.0293
  -5.250  -0.4148   0.01639   0.00849  -0.0389   0.9707   0.0294
  -5.000  -0.3817   0.01562   0.00763  -0.0404   0.9632   0.0295
  -4.750  -0.3508   0.01495   0.00690  -0.0413   0.9533   0.0296
  -4.500  -0.3202   0.01437   0.00626  -0.0422   0.9430   0.0299
  -4.250  -0.2901   0.01387   0.00567  -0.0429   0.9320   0.0303
  -4.000  -0.2605   0.01344   0.00514  -0.0433   0.9202   0.0308
  -3.750  -0.2317   0.01308   0.00469  -0.0436   0.9076   0.0316
  -3.500  -0.2030   0.01275   0.00427  -0.0438   0.8958   0.0327
  -3.250  -0.1745   0.01247   0.00390  -0.0439   0.8850   0.0345
  -3.000  -0.1466   0.01219   0.00356  -0.0438   0.8750   0.0393
  -2.750  -0.1194   0.01183   0.00325  -0.0437   0.8655   0.0643
  -2.500  -0.0962   0.01039   0.00281  -0.0440   0.8553   0.3047
  -2.250  -0.0730   0.00951   0.00282  -0.0436   0.8456   0.5222
  -2.000  -0.0463   0.00945   0.00280  -0.0432   0.8366   0.5856
  -1.750  -0.0194   0.00937   0.00274  -0.0428   0.8267   0.6104
  -1.500   0.0065   0.00927   0.00277  -0.0422   0.8173   0.6426
  -1.250   0.0318   0.00926   0.00287  -0.0413   0.8084   0.6873
  -1.000   0.0580   0.00926   0.00293  -0.0407   0.7987   0.7135
  -0.750   0.0854   0.00926   0.00289  -0.0405   0.7896   0.7233
  -0.500   0.1128   0.00926   0.00285  -0.0403   0.7810   0.7335
  -0.250   0.1401   0.00925   0.00285  -0.0400   0.7714   0.7435
   0.000   0.1673   0.00926   0.00284  -0.0398   0.7629   0.7535
   0.250   0.1945   0.00927   0.00285  -0.0395   0.7538   0.7642
   0.500   0.2217   0.00929   0.00288  -0.0393   0.7447   0.7752
   0.750   0.2485   0.00931   0.00291  -0.0388   0.7363   0.7859
   1.000   0.2754   0.00933   0.00297  -0.0385   0.7266   0.7971
   1.250   0.3020   0.00936   0.00303  -0.0381   0.7160   0.8087
   1.500   0.3274   0.00938   0.00299  -0.0373   0.6936   0.8207
   1.750   0.3522   0.00940   0.00297  -0.0363   0.6665   0.8323
   2.000   0.3776   0.00945   0.00304  -0.0356   0.6498   0.8441
   2.250   0.4031   0.00950   0.00311  -0.0349   0.6348   0.8561
   2.500   0.4282   0.00955   0.00320  -0.0342   0.6167   0.8685
   2.750   0.4523   0.00965   0.00324  -0.0331   0.5864   0.8816
   3.000   0.4749   0.00984   0.00328  -0.0318   0.5337   0.8956
   3.250   0.4961   0.01019   0.00334  -0.0304   0.4560   0.9113
   3.500   0.5131   0.01117   0.00358  -0.0288   0.2977   0.9308
   3.750   0.5320   0.01259   0.00416  -0.0281   0.1219   0.9537
   4.000   0.5614   0.01346   0.00470  -0.0291   0.0494   0.9803
   4.250   0.5895   0.01394   0.00513  -0.0296   0.0369   1.0000
   4.500   0.6156   0.01437   0.00557  -0.0295   0.0325   1.0000
   4.750   0.6412   0.01487   0.00607  -0.0294   0.0298   1.0000
   5.000   0.6666   0.01539   0.00667  -0.0293   0.0287   1.0000
   5.250   0.6918   0.01591   0.00728  -0.0291   0.0281   1.0000
   5.500   0.7163   0.01651   0.00795  -0.0288   0.0275   1.0000
   5.750   0.7402   0.01717   0.00868  -0.0284   0.0270   1.0000
   6.000   0.7635   0.01791   0.00949  -0.0279   0.0265   1.0000
   6.250   0.7865   0.01871   0.01038  -0.0274   0.0261   1.0000
   6.500   0.8091   0.01960   0.01133  -0.0268   0.0257   1.0000
   6.750   0.8317   0.02055   0.01235  -0.0262   0.0254   1.0000
   7.000   0.8544   0.02159   0.01347  -0.0256   0.0252   1.0000
   7.250   0.8774   0.02272   0.01469  -0.0251   0.0250   1.0000
   7.500   0.9008   0.02397   0.01604  -0.0246   0.0248   1.0000
   7.750   0.9242   0.02534   0.01758  -0.0241   0.0247   1.0000
   8.000   0.9476   0.02688   0.01928  -0.0236   0.0246   1.0000
   8.250   0.9702   0.02850   0.02111  -0.0231   0.0244   1.0000
   8.500   0.9914   0.02976   0.02253  -0.0225   0.0234   1.0000
   8.750   1.0113   0.03094   0.02378  -0.0221   0.0221   1.0000
   9.000   1.0274   0.03391   0.02698  -0.0214   0.0209   1.0000
   9.250   1.0438   0.03554   0.02895  -0.0203   0.0203   1.0000
   9.500   1.0589   0.03709   0.03085  -0.0191   0.0192   1.0000
   9.750   1.0708   0.03915   0.03326  -0.0178   0.0179   1.0000
  10.000   1.0789   0.04166   0.03609  -0.0162   0.0170   1.0000
  10.250   1.0845   0.04403   0.03872  -0.0147   0.0162   1.0000
  10.500   1.0862   0.04644   0.04137  -0.0129   0.0156   1.0000
  10.750   1.0828   0.04864   0.04376  -0.0107   0.0152   1.0000
  11.000   1.0770   0.05089   0.04615  -0.0088   0.0148   1.0000
  11.250   1.0668   0.05389   0.04933  -0.0074   0.0145   1.0000
  11.500   1.0526   0.05763   0.05324  -0.0070   0.0142   1.0000
  11.750   1.0327   0.06250   0.05833  -0.0076   0.0140   1.0000
  12.000   1.0107   0.06820   0.06424  -0.0096   0.0139   1.0000
  12.250   0.9913   0.07423   0.07048  -0.0127   0.0140   1.0000
  12.500   0.9716   0.08115   0.07760  -0.0171   0.0141   1.0000
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