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NACA 65(1)-212 (naca651212-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 65(1)-212 (naca651212-il)
Reynolds number: 1,000,000
Max Cl/Cd: 87.81 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca651212-il-1000000.txt
Download as CSV file: xf-naca651212-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(1)-212                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.7915   0.05582   0.05375  -0.0559   1.0000   0.0098
 -12.500  -0.8174   0.04967   0.04741  -0.0586   1.0000   0.0098
 -12.250  -0.8490   0.04389   0.04140  -0.0597   1.0000   0.0099
 -12.000  -0.8733   0.03953   0.03681  -0.0588   1.0000   0.0099
 -11.750  -0.8968   0.03575   0.03279  -0.0564   1.0000   0.0099
 -11.500  -0.8853   0.03580   0.03288  -0.0552   1.0000   0.0102
 -11.250  -0.9006   0.03331   0.03019  -0.0511   1.0000   0.0102
 -11.000  -0.8984   0.03170   0.02844  -0.0488   1.0000   0.0103
 -10.750  -0.8949   0.02988   0.02645  -0.0465   1.0000   0.0104
 -10.500  -0.8782   0.02990   0.02647  -0.0454   1.0000   0.0107
 -10.250  -0.8701   0.02881   0.02528  -0.0431   1.0000   0.0109
 -10.000  -0.8468   0.02728   0.02359  -0.0441   0.9916   0.0112
  -9.750  -0.8198   0.02532   0.02140  -0.0458   0.9853   0.0118
  -9.500  -0.7923   0.02332   0.01914  -0.0473   0.9776   0.0123
  -9.250  -0.7622   0.02202   0.01763  -0.0489   0.9698   0.0126
  -9.000  -0.7351   0.02123   0.01666  -0.0495   0.9585   0.0129
  -8.750  -0.7200   0.01790   0.01298  -0.0484   0.9453   0.0135
  -8.500  -0.6986   0.01717   0.01218  -0.0476   0.9337   0.0138
  -8.250  -0.6762   0.01677   0.01171  -0.0470   0.9234   0.0143
  -8.000  -0.6540   0.01619   0.01103  -0.0462   0.9138   0.0147
  -7.750  -0.6306   0.01574   0.01050  -0.0457   0.9047   0.0153
  -7.500  -0.6074   0.01520   0.00987  -0.0451   0.8963   0.0158
  -7.250  -0.5836   0.01465   0.00924  -0.0446   0.8875   0.0163
  -7.000  -0.5598   0.01411   0.00860  -0.0440   0.8795   0.0166
  -6.750  -0.5351   0.01374   0.00815  -0.0436   0.8716   0.0169
  -6.500  -0.5158   0.01240   0.00670  -0.0424   0.8638   0.0177
  -6.250  -0.4926   0.01183   0.00608  -0.0419   0.8560   0.0184
  -6.000  -0.4675   0.01151   0.00573  -0.0416   0.8488   0.0192
  -5.750  -0.4421   0.01121   0.00538  -0.0413   0.8414   0.0201
  -5.500  -0.4168   0.01087   0.00498  -0.0410   0.8346   0.0209
  -5.250  -0.3912   0.01055   0.00461  -0.0408   0.8276   0.0215
  -5.000  -0.3650   0.01032   0.00433  -0.0406   0.8214   0.0221
  -4.750  -0.3409   0.00969   0.00362  -0.0402   0.8145   0.0237
  -4.250  -0.2878   0.00921   0.00307  -0.0400   0.8017   0.0273
  -4.000  -0.2607   0.00905   0.00287  -0.0400   0.7954   0.0288
  -3.750  -0.2342   0.00873   0.00250  -0.0399   0.7897   0.0328
  -3.500  -0.2069   0.00853   0.00229  -0.0399   0.7835   0.0368
  -3.250  -0.1800   0.00832   0.00208  -0.0399   0.7778   0.0474
  -3.000  -0.1553   0.00759   0.00178  -0.0398   0.7718   0.1581
  -2.750  -0.1333   0.00642   0.00139  -0.0397   0.7660   0.3770
  -2.500  -0.1088   0.00570   0.00121  -0.0396   0.7607   0.5377
  -2.250  -0.0811   0.00555   0.00117  -0.0397   0.7551   0.5827
  -2.000  -0.0531   0.00549   0.00114  -0.0398   0.7497   0.6096
  -1.750  -0.0246   0.00545   0.00113  -0.0400   0.7446   0.6322
  -1.500   0.0035   0.00541   0.00114  -0.0401   0.7393   0.6549
  -1.250   0.0317   0.00543   0.00115  -0.0402   0.7342   0.6728
  -1.000   0.0602   0.00542   0.00117  -0.0404   0.7293   0.6868
  -0.750   0.0888   0.00543   0.00118  -0.0406   0.7242   0.6958
  -0.500   0.1173   0.00545   0.00117  -0.0408   0.7194   0.7007
  -0.250   0.1463   0.00546   0.00117  -0.0411   0.7147   0.7056
   0.000   0.1750   0.00545   0.00117  -0.0413   0.7099   0.7103
   0.250   0.2035   0.00547   0.00118  -0.0415   0.7052   0.7153
   0.500   0.2324   0.00549   0.00119  -0.0418   0.7008   0.7203
   0.750   0.2611   0.00549   0.00121  -0.0420   0.6961   0.7252
   1.000   0.2896   0.00551   0.00125  -0.0422   0.6915   0.7303
   1.250   0.3183   0.00554   0.00128  -0.0425   0.6859   0.7357
   1.500   0.3466   0.00554   0.00129  -0.0426   0.6778   0.7408
   1.750   0.3747   0.00555   0.00132  -0.0427   0.6669   0.7462
   2.000   0.4029   0.00560   0.00134  -0.0428   0.6541   0.7518
   2.250   0.4303   0.00563   0.00136  -0.0428   0.6352   0.7572
   2.500   0.4579   0.00569   0.00140  -0.0428   0.6183   0.7631
   2.750   0.4853   0.00579   0.00146  -0.0428   0.5958   0.7688
   3.000   0.5122   0.00591   0.00153  -0.0427   0.5697   0.7744
   3.250   0.5383   0.00613   0.00163  -0.0424   0.5275   0.7808
   3.500   0.5587   0.00686   0.00191  -0.0414   0.4079   0.7870
   3.750   0.5746   0.00812   0.00245  -0.0398   0.2379   0.7940
   4.000   0.5927   0.00915   0.00293  -0.0386   0.1086   0.8005
   4.250   0.6139   0.00984   0.00333  -0.0377   0.0440   0.8075
   4.500   0.6387   0.01019   0.00365  -0.0373   0.0327   0.8144
   4.750   0.6643   0.01041   0.00392  -0.0370   0.0298   0.8215
   5.000   0.6882   0.01083   0.00436  -0.0364   0.0252   0.8289
   5.250   0.7135   0.01104   0.00462  -0.0361   0.0238   0.8361
   5.500   0.7384   0.01132   0.00494  -0.0357   0.0223   0.8437
   5.750   0.7623   0.01163   0.00529  -0.0351   0.0208   0.8515
   6.000   0.7827   0.01229   0.00602  -0.0340   0.0192   0.8601
   6.250   0.8056   0.01265   0.00646  -0.0332   0.0186   0.8690
   6.500   0.8283   0.01301   0.00688  -0.0324   0.0181   0.8778
   7.000   0.8713   0.01383   0.00784  -0.0304   0.0169   0.8974
   7.250   0.8926   0.01418   0.00823  -0.0294   0.0162   0.9081
   7.500   0.9126   0.01457   0.00867  -0.0282   0.0156   0.9200
   7.750   0.9287   0.01518   0.00935  -0.0263   0.0150   0.9345
   8.000   0.9368   0.01648   0.01079  -0.0230   0.0144   0.9571
   8.250   0.9635   0.01720   0.01161  -0.0234   0.0142   1.0000
   8.500   0.9857   0.01781   0.01227  -0.0229   0.0140   1.0000
   8.750   1.0069   0.01856   0.01308  -0.0221   0.0137   1.0000
   9.000   1.0275   0.01940   0.01398  -0.0214   0.0134   1.0000
   9.250   1.0479   0.02022   0.01487  -0.0206   0.0131   1.0000
   9.500   1.0679   0.02108   0.01580  -0.0197   0.0128   1.0000
   9.750   1.0866   0.02170   0.01647  -0.0187   0.0124   1.0000
  10.000   1.1032   0.02229   0.01712  -0.0173   0.0120   1.0000
  10.250   1.1192   0.02311   0.01801  -0.0159   0.0118   1.0000
  10.500   1.1341   0.02394   0.01889  -0.0144   0.0116   1.0000
  10.750   1.1482   0.02500   0.02001  -0.0128   0.0113   1.0000
  11.000   1.1607   0.02712   0.02227  -0.0115   0.0110   1.0000
  11.250   1.1655   0.03087   0.02638  -0.0094   0.0107   1.0000
  11.500   1.1721   0.03200   0.02765  -0.0071   0.0106   1.0000
  11.750   1.1779   0.03323   0.02902  -0.0050   0.0105   1.0000
  12.000   1.1813   0.03482   0.03078  -0.0028   0.0103   1.0000
  12.250   1.1811   0.03692   0.03307  -0.0007   0.0102   1.0000
  12.500   1.1786   0.03922   0.03555   0.0014   0.0100   1.0000
  12.750   1.1715   0.04209   0.03864   0.0033   0.0099   1.0000
  13.000   1.1710   0.04408   0.04075   0.0045   0.0096   1.0000
  13.250   1.1632   0.04708   0.04393   0.0056   0.0095   1.0000
  13.500   1.1362   0.05269   0.04983   0.0066   0.0095   1.0000
  13.750   1.1143   0.05790   0.05527   0.0064   0.0095   1.0000
  14.000   1.0954   0.06306   0.06060   0.0054   0.0094   1.0000
  14.250   1.0588   0.07148   0.06928   0.0025   0.0094   1.0000
  14.500   1.0198   0.08152   0.07955  -0.0025   0.0095   1.0000
  14.750   0.9678   0.09670   0.09497  -0.0122   0.0098   1.0000
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