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NACA 63-212 AIRFOIL (n63212-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 63-212 AIRFOIL (n63212-il)
Reynolds number: 200,000
Max Cl/Cd: 57.37 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n63212-il-200000-n5.txt
Download as CSV file: xf-n63212-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-212 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.6759   0.08043   0.07660  -0.0301   1.0000   0.0178
 -11.750  -0.7050   0.07039   0.06643  -0.0379   1.0000   0.0176
 -11.500  -0.7286   0.06322   0.05912  -0.0431   1.0000   0.0174
 -11.250  -0.7516   0.05726   0.05296  -0.0466   1.0000   0.0174
 -11.000  -0.7724   0.05240   0.04789  -0.0485   1.0000   0.0173
 -10.750  -0.7879   0.04868   0.04397  -0.0487   1.0000   0.0173
 -10.500  -0.8040   0.04537   0.04043  -0.0474   1.0000   0.0173
 -10.250  -0.8118   0.04222   0.03700  -0.0459   1.0000   0.0173
 -10.000  -0.8128   0.03913   0.03358  -0.0446   1.0000   0.0174
  -9.750  -0.8085   0.03627   0.03038  -0.0433   1.0000   0.0176
  -9.500  -0.7992   0.03379   0.02757  -0.0422   1.0000   0.0177
  -9.250  -0.7868   0.03154   0.02499  -0.0411   1.0000   0.0179
  -9.000  -0.7718   0.02971   0.02283  -0.0400   1.0000   0.0183
  -8.750  -0.7552   0.02803   0.02097  -0.0391   1.0000   0.0186
  -8.500  -0.7376   0.02677   0.01966  -0.0382   1.0000   0.0191
  -8.250  -0.7198   0.02559   0.01839  -0.0372   1.0000   0.0195
  -8.000  -0.7030   0.02442   0.01711  -0.0358   1.0000   0.0198
  -7.750  -0.6795   0.02318   0.01576  -0.0358   0.9950   0.0201
  -7.500  -0.6474   0.02190   0.01436  -0.0374   0.9849   0.0205
  -7.000  -0.5837   0.01968   0.01193  -0.0403   0.9647   0.0217
  -6.750  -0.5528   0.01873   0.01089  -0.0415   0.9540   0.0224
  -6.500  -0.5228   0.01791   0.00996  -0.0424   0.9433   0.0231
  -6.250  -0.4942   0.01703   0.00904  -0.0432   0.9325   0.0241
  -6.000  -0.4669   0.01640   0.00834  -0.0436   0.9210   0.0257
  -5.750  -0.4404   0.01587   0.00774  -0.0436   0.9098   0.0281
  -5.500  -0.4148   0.01528   0.00707  -0.0434   0.8992   0.0313
  -5.250  -0.3896   0.01475   0.00647  -0.0432   0.8889   0.0362
  -5.000  -0.3648   0.01424   0.00593  -0.0428   0.8783   0.0443
  -4.750  -0.3397   0.01379   0.00548  -0.0424   0.8688   0.0579
  -4.500  -0.3150   0.01328   0.00506  -0.0421   0.8594   0.0867
  -4.250  -0.2906   0.01266   0.00464  -0.0419   0.8498   0.1395
  -4.000  -0.2670   0.01188   0.00421  -0.0417   0.8415   0.2284
  -3.750  -0.2443   0.01095   0.00388  -0.0415   0.8320   0.3686
  -3.500  -0.2194   0.01054   0.00377  -0.0411   0.8239   0.4577
  -3.250  -0.1934   0.01036   0.00374  -0.0407   0.8151   0.5177
  -3.000  -0.1672   0.01027   0.00373  -0.0403   0.8073   0.5623
  -2.750  -0.1405   0.01022   0.00372  -0.0398   0.7989   0.5912
  -2.500  -0.1133   0.01021   0.00367  -0.0395   0.7911   0.6127
  -2.250  -0.0859   0.01020   0.00362  -0.0393   0.7829   0.6286
  -2.000  -0.0584   0.01018   0.00356  -0.0391   0.7754   0.6393
  -1.750  -0.0306   0.01016   0.00349  -0.0389   0.7673   0.6495
  -1.500  -0.0026   0.01015   0.00342  -0.0389   0.7598   0.6596
  -1.250   0.0250   0.01013   0.00338  -0.0387   0.7519   0.6678
  -1.000   0.0531   0.01013   0.00332  -0.0387   0.7444   0.6769
  -0.750   0.0808   0.01012   0.00331  -0.0385   0.7366   0.6848
  -0.500   0.1089   0.01013   0.00327  -0.0385   0.7293   0.6934
  -0.250   0.1366   0.01013   0.00327  -0.0384   0.7213   0.7014
   0.000   0.1646   0.01015   0.00326  -0.0383   0.7142   0.7098
   0.250   0.1924   0.01016   0.00329  -0.0382   0.7062   0.7180
   0.500   0.2202   0.01019   0.00330  -0.0381   0.6991   0.7263
   0.750   0.2480   0.01021   0.00335  -0.0381   0.6911   0.7348
   1.000   0.2757   0.01024   0.00338  -0.0379   0.6840   0.7429
   1.250   0.3035   0.01028   0.00345  -0.0379   0.6758   0.7518
   1.500   0.3309   0.01032   0.00351  -0.0377   0.6685   0.7598
   1.750   0.3586   0.01037   0.00359  -0.0376   0.6600   0.7691
   2.000   0.3857   0.01041   0.00369  -0.0373   0.6522   0.7770
   2.250   0.4133   0.01047   0.00377  -0.0372   0.6433   0.7864
   2.500   0.4401   0.01052   0.00389  -0.0369   0.6342   0.7947
   2.750   0.4671   0.01058   0.00398  -0.0366   0.6251   0.8038
   3.000   0.4938   0.01064   0.00410  -0.0362   0.6137   0.8132
   3.250   0.5199   0.01069   0.00420  -0.0357   0.5994   0.8223
   3.500   0.5460   0.01076   0.00429  -0.0352   0.5823   0.8325
   3.750   0.5709   0.01083   0.00437  -0.0344   0.5633   0.8420
   4.000   0.5955   0.01092   0.00447  -0.0336   0.5372   0.8522
   4.250   0.6192   0.01108   0.00454  -0.0327   0.5018   0.8632
   4.500   0.6419   0.01128   0.00468  -0.0316   0.4613   0.8744
   4.750   0.6638   0.01157   0.00486  -0.0304   0.4148   0.8864
   5.000   0.6833   0.01209   0.00511  -0.0290   0.3443   0.8998
   5.250   0.6999   0.01295   0.00557  -0.0274   0.2544   0.9158
   5.500   0.7174   0.01388   0.00612  -0.0262   0.1754   0.9351
   5.750   0.7399   0.01481   0.00673  -0.0260   0.1122   0.9587
   6.000   0.7669   0.01566   0.00737  -0.0267   0.0743   1.0000
   6.250   0.7899   0.01636   0.00800  -0.0265   0.0570   1.0000
   6.500   0.8129   0.01704   0.00865  -0.0262   0.0478   1.0000
   7.000   0.8576   0.01843   0.01008  -0.0253   0.0374   1.0000
   7.250   0.8789   0.01917   0.01085  -0.0247   0.0343   1.0000
   7.500   0.8980   0.02010   0.01180  -0.0238   0.0318   1.0000
   7.750   0.9187   0.02084   0.01262  -0.0231   0.0297   1.0000
   8.000   0.9385   0.02163   0.01348  -0.0224   0.0277   1.0000
   8.250   0.9568   0.02255   0.01442  -0.0214   0.0263   1.0000
   8.500   0.9722   0.02374   0.01563  -0.0202   0.0253   1.0000
   8.750   0.9894   0.02481   0.01678  -0.0191   0.0244   1.0000
   9.000   1.0068   0.02589   0.01796  -0.0180   0.0237   1.0000
   9.250   1.0238   0.02703   0.01921  -0.0169   0.0229   1.0000
   9.500   1.0401   0.02822   0.02049  -0.0157   0.0223   1.0000
   9.750   1.0561   0.02945   0.02182  -0.0146   0.0216   1.0000
  10.000   1.0715   0.03067   0.02312  -0.0134   0.0210   1.0000
  10.250   1.0856   0.03188   0.02439  -0.0123   0.0204   1.0000
  10.500   1.0991   0.03327   0.02584  -0.0112   0.0199   1.0000
  10.750   1.1124   0.03512   0.02780  -0.0102   0.0193   1.0000
  11.000   1.1242   0.03677   0.02966  -0.0090   0.0190   1.0000
  11.250   1.1340   0.03866   0.03177  -0.0077   0.0186   1.0000
  11.500   1.1411   0.04077   0.03413  -0.0064   0.0183   1.0000
  11.750   1.1454   0.04311   0.03671  -0.0052   0.0181   1.0000
  12.000   1.1469   0.04566   0.03951  -0.0041   0.0178   1.0000
  12.250   1.1450   0.04854   0.04265  -0.0031   0.0176   1.0000
  12.500   1.1403   0.05170   0.04606  -0.0024   0.0175   1.0000
  12.750   1.1328   0.05522   0.04982  -0.0022   0.0173   1.0000
  13.000   1.1233   0.05907   0.05391  -0.0024   0.0171   1.0000
  13.250   1.1102   0.06362   0.05871  -0.0033   0.0170   1.0000
  13.500   1.0960   0.06849   0.06380  -0.0049   0.0169   1.0000
  13.750   1.0791   0.07413   0.06966  -0.0072   0.0168   1.0000
  14.000   1.0592   0.08066   0.07641  -0.0106   0.0167   1.0000
  14.250   1.0292   0.08973   0.08574  -0.0158   0.0169   1.0000
  14.500   0.9968   0.10052   0.09677  -0.0229   0.0171   1.0000
  14.750   0.9379   0.12061   0.11716  -0.0364   0.0177   1.0000
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