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NACA 63-212 AIRFOIL (n63212-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-212 AIRFOIL (n63212-il)
Reynolds number: 1,000,000
Max Cl/Cd: 91.94 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n63212-il-1000000.txt
Download as CSV file: xf-n63212-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.4836   0.11475   0.11321  -0.0111   1.0000   0.0189
 -12.500  -0.5837   0.11528   0.11357  -0.0113   1.0000   0.0166
 -12.250  -0.8978   0.04360   0.04075  -0.0519   1.0000   0.0119
 -12.000  -0.9077   0.04058   0.03758  -0.0519   1.0000   0.0118
 -11.750  -0.9159   0.03808   0.03492  -0.0510   1.0000   0.0118
 -11.500  -0.9264   0.03573   0.03241  -0.0489   1.0000   0.0118
 -11.250  -0.9284   0.03403   0.03056  -0.0466   1.0000   0.0117
 -11.000  -0.9308   0.03113   0.02741  -0.0447   1.0000   0.0118
 -10.750  -0.9238   0.02900   0.02507  -0.0433   1.0000   0.0117
 -10.500  -0.9114   0.02735   0.02325  -0.0422   1.0000   0.0117
 -10.250  -0.9005   0.02506   0.02074  -0.0409   1.0000   0.0118
 -10.000  -0.8865   0.02307   0.01856  -0.0398   1.0000   0.0118
  -9.750  -0.8702   0.02140   0.01674  -0.0388   1.0000   0.0119
  -9.500  -0.8529   0.01991   0.01514  -0.0378   1.0000   0.0121
  -9.250  -0.8342   0.01886   0.01403  -0.0369   1.0000   0.0124
  -9.000  -0.8135   0.01798   0.01310  -0.0362   0.9990   0.0126
  -8.750  -0.7809   0.01696   0.01199  -0.0380   0.9886   0.0128
  -8.500  -0.7473   0.01595   0.01090  -0.0399   0.9781   0.0130
  -8.250  -0.7142   0.01511   0.00999  -0.0416   0.9654   0.0134
  -8.000  -0.6861   0.01439   0.00917  -0.0421   0.9485   0.0136
  -7.750  -0.6628   0.01380   0.00848  -0.0415   0.9313   0.0139
  -7.500  -0.6402   0.01324   0.00782  -0.0408   0.9163   0.0140
  -7.250  -0.6167   0.01276   0.00724  -0.0401   0.9031   0.0143
  -7.000  -0.5928   0.01227   0.00666  -0.0396   0.8911   0.0144
  -6.750  -0.5683   0.01185   0.00615  -0.0391   0.8801   0.0147
  -6.500  -0.5430   0.01144   0.00567  -0.0388   0.8694   0.0148
  -6.250  -0.5177   0.01098   0.00512  -0.0385   0.8597   0.0151
  -6.000  -0.4926   0.01048   0.00452  -0.0382   0.8502   0.0158
  -5.750  -0.4660   0.01014   0.00415  -0.0381   0.8409   0.0167
  -5.500  -0.4392   0.00988   0.00384  -0.0380   0.8323   0.0177
  -5.250  -0.4120   0.00964   0.00354  -0.0379   0.8234   0.0187
  -5.000  -0.3849   0.00935   0.00322  -0.0378   0.8152   0.0211
  -4.750  -0.3576   0.00909   0.00295  -0.0378   0.8068   0.0265
  -4.500  -0.3302   0.00882   0.00270  -0.0378   0.7988   0.0382
  -4.250  -0.3028   0.00855   0.00247  -0.0379   0.7908   0.0535
  -4.000  -0.2754   0.00823   0.00226  -0.0380   0.7830   0.0830
  -3.750  -0.2484   0.00780   0.00202  -0.0381   0.7752   0.1363
  -3.500  -0.2217   0.00721   0.00175  -0.0384   0.7677   0.2251
  -3.250  -0.1953   0.00654   0.00149  -0.0386   0.7599   0.3396
  -3.000  -0.1679   0.00613   0.00135  -0.0388   0.7525   0.4232
  -2.750  -0.1397   0.00594   0.00126  -0.0390   0.7449   0.4670
  -2.500  -0.1113   0.00582   0.00121  -0.0392   0.7376   0.5001
  -2.250  -0.0827   0.00574   0.00117  -0.0393   0.7300   0.5266
  -2.000  -0.0541   0.00568   0.00113  -0.0395   0.7229   0.5501
  -1.750  -0.0254   0.00564   0.00110  -0.0396   0.7152   0.5670
  -1.500   0.0032   0.00559   0.00108  -0.0398   0.7080   0.5875
  -1.250   0.0320   0.00556   0.00107  -0.0399   0.7005   0.6040
  -1.000   0.0607   0.00555   0.00106  -0.0401   0.6933   0.6163
  -0.750   0.0896   0.00555   0.00105  -0.0403   0.6855   0.6263
  -0.500   0.1184   0.00555   0.00105  -0.0404   0.6783   0.6363
  -0.250   0.1473   0.00555   0.00105  -0.0406   0.6704   0.6455
   0.000   0.1761   0.00557   0.00105  -0.0407   0.6631   0.6547
   0.250   0.2049   0.00557   0.00107  -0.0409   0.6550   0.6633
   0.500   0.2337   0.00560   0.00108  -0.0411   0.6473   0.6719
   0.750   0.2624   0.00561   0.00110  -0.0412   0.6388   0.6802
   1.000   0.2912   0.00564   0.00113  -0.0414   0.6306   0.6886
   1.250   0.3198   0.00567   0.00116  -0.0415   0.6216   0.6970
   1.500   0.3486   0.00569   0.00120  -0.0417   0.6126   0.7052
   1.750   0.3771   0.00574   0.00125  -0.0418   0.6018   0.7135
   2.250   0.4340   0.00584   0.00134  -0.0420   0.5768   0.7299
   2.500   0.4623   0.00591   0.00140  -0.0421   0.5618   0.7377
   2.750   0.4903   0.00601   0.00147  -0.0421   0.5425   0.7459
   3.000   0.5182   0.00611   0.00154  -0.0421   0.5195   0.7538
   3.250   0.5462   0.00622   0.00163  -0.0422   0.5011   0.7621
   3.500   0.5739   0.00635   0.00173  -0.0422   0.4819   0.7698
   3.750   0.6013   0.00654   0.00185  -0.0421   0.4520   0.7784
   4.000   0.6274   0.00685   0.00202  -0.0420   0.4035   0.7864
   4.250   0.6521   0.00741   0.00228  -0.0417   0.3293   0.7952
   4.500   0.6752   0.00812   0.00265  -0.0412   0.2446   0.8037
   4.750   0.6984   0.00884   0.00304  -0.0408   0.1679   0.8126
   5.000   0.7221   0.00946   0.00342  -0.0403   0.1109   0.8219
   5.250   0.7463   0.00998   0.00378  -0.0399   0.0724   0.8311
   5.500   0.7713   0.01042   0.00412  -0.0396   0.0497   0.8411
   5.750   0.7964   0.01075   0.00444  -0.0392   0.0392   0.8513
   6.000   0.8212   0.01111   0.00481  -0.0388   0.0324   0.8620
   6.250   0.8465   0.01139   0.00512  -0.0384   0.0290   0.8733
   6.500   0.8704   0.01178   0.00555  -0.0378   0.0253   0.8857
   6.750   0.8946   0.01203   0.00587  -0.0371   0.0233   0.8989
   7.000   0.9172   0.01241   0.00628  -0.0363   0.0213   0.9139
   7.250   0.9379   0.01285   0.00680  -0.0350   0.0199   0.9319
   7.500   0.9585   0.01308   0.00713  -0.0336   0.0192   0.9603
   7.750   0.9868   0.01346   0.00756  -0.0341   0.0182   1.0000
   8.000   1.0117   0.01391   0.00801  -0.0339   0.0174   1.0000
   8.250   1.0347   0.01451   0.00863  -0.0334   0.0166   1.0000
   8.500   1.0538   0.01547   0.00966  -0.0324   0.0158   1.0000
   8.750   1.0777   0.01589   0.01012  -0.0320   0.0154   1.0000
   9.000   1.1003   0.01640   0.01067  -0.0314   0.0150   1.0000
   9.250   1.1218   0.01699   0.01131  -0.0307   0.0146   1.0000
   9.500   1.1428   0.01759   0.01195  -0.0300   0.0142   1.0000
   9.750   1.1628   0.01823   0.01264  -0.0291   0.0138   1.0000
  10.000   1.1819   0.01891   0.01336  -0.0281   0.0134   1.0000
  10.250   1.1997   0.01965   0.01414  -0.0269   0.0132   1.0000
  10.500   1.2143   0.02059   0.01512  -0.0254   0.0128   1.0000
  10.750   1.2217   0.02189   0.01651  -0.0228   0.0125   1.0000
  11.000   1.2238   0.02375   0.01850  -0.0197   0.0122   1.0000
  11.250   1.2360   0.02459   0.01941  -0.0180   0.0121   1.0000
  11.500   1.2483   0.02541   0.02031  -0.0164   0.0120   1.0000
  11.750   1.2589   0.02646   0.02145  -0.0148   0.0118   1.0000
  12.000   1.2705   0.02736   0.02243  -0.0135   0.0116   1.0000
  12.250   1.2800   0.02857   0.02372  -0.0121   0.0114   1.0000
  12.500   1.2877   0.03002   0.02527  -0.0107   0.0112   1.0000
  12.750   1.2945   0.03160   0.02695  -0.0095   0.0111   1.0000
  13.000   1.3022   0.03304   0.02848  -0.0085   0.0108   1.0000
  13.250   1.3073   0.03484   0.03038  -0.0075   0.0107   1.0000
  13.500   1.3127   0.03662   0.03226  -0.0067   0.0105   1.0000
  13.750   1.3153   0.03882   0.03457  -0.0060   0.0104   1.0000
  14.000   1.3184   0.04097   0.03682  -0.0056   0.0103   1.0000
  14.250   1.3195   0.04343   0.03939  -0.0054   0.0102   1.0000
  14.500   1.3202   0.04601   0.04207  -0.0053   0.0101   1.0000
  14.750   1.3204   0.04874   0.04489  -0.0056   0.0100   1.0000
  15.000   1.3186   0.05180   0.04803  -0.0060   0.0098   1.0000
  15.250   1.3126   0.05560   0.05198  -0.0068   0.0098   1.0000
  15.500   1.3047   0.05981   0.05630  -0.0080   0.0097   1.0000
  15.750   1.2967   0.06427   0.06091  -0.0095   0.0097   1.0000
  16.000   1.2819   0.07002   0.06682  -0.0118   0.0096   1.0000
  16.250   1.2666   0.07620   0.07317  -0.0146   0.0095   1.0000
  16.500   1.2475   0.08346   0.08060  -0.0184   0.0095   1.0000
  16.750   1.2293   0.09101   0.08832  -0.0226   0.0095   1.0000
  17.000   1.2123   0.09881   0.09628  -0.0272   0.0095   1.0000
  17.250   1.1888   0.10842   0.10607  -0.0331   0.0094   1.0000
  17.500   1.1690   0.11781   0.11560  -0.0391   0.0095   1.0000
  17.750   1.1481   0.12805   0.12601  -0.0457   0.0096   1.0000
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