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NACA 63-212 AIRFOIL (n63212-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-212 AIRFOIL (n63212-il)
Reynolds number: 200,000
Max Cl/Cd: 65.64 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n63212-il-200000.txt
Download as CSV file: xf-n63212-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.6188   0.07649   0.07291  -0.0428   1.0000   0.0706
  -9.750  -0.6488   0.07203   0.06836  -0.0456   1.0000   0.0708
  -9.500  -0.6830   0.06955   0.06566  -0.0455   1.0000   0.0712
  -9.250  -0.7000   0.06768   0.06347  -0.0448   1.0000   0.0716
  -8.000  -0.6962   0.03595   0.02970  -0.0383   1.0000   0.0386
  -7.750  -0.6850   0.03261   0.02623  -0.0365   1.0000   0.0376
  -7.500  -0.6777   0.03021   0.02362  -0.0338   1.0000   0.0371
  -7.250  -0.6705   0.02846   0.02166  -0.0309   1.0000   0.0370
  -7.000  -0.6616   0.02715   0.02012  -0.0283   1.0000   0.0374
  -6.750  -0.6319   0.02574   0.01839  -0.0292   0.9966   0.0382
  -6.500  -0.5946   0.02372   0.01613  -0.0315   0.9918   0.0383
  -6.250  -0.5586   0.02134   0.01362  -0.0334   0.9872   0.0390
  -6.000  -0.5211   0.01947   0.01177  -0.0357   0.9833   0.0406
  -5.750  -0.4857   0.01831   0.01062  -0.0377   0.9766   0.0430
  -5.500  -0.4458   0.01727   0.00953  -0.0404   0.9721   0.0469
  -5.250  -0.4109   0.01606   0.00837  -0.0425   0.9655   0.0543
  -5.000  -0.3738   0.01490   0.00721  -0.0449   0.9593   0.0712
  -4.750  -0.3419   0.01349   0.00616  -0.0467   0.9515   0.1273
  -4.500  -0.3163   0.01131   0.00541  -0.0484   0.9433   0.4125
  -4.250  -0.2886   0.01102   0.00546  -0.0483   0.9336   0.5200
  -4.000  -0.2564   0.01099   0.00543  -0.0489   0.9268   0.5643
  -3.750  -0.2302   0.01101   0.00543  -0.0482   0.9162   0.5910
  -3.500  -0.2026   0.01105   0.00544  -0.0477   0.9075   0.6126
  -3.250  -0.1763   0.01115   0.00552  -0.0469   0.8986   0.6364
  -3.000  -0.1515   0.01131   0.00568  -0.0457   0.8889   0.6591
  -2.750  -0.1258   0.01143   0.00577  -0.0446   0.8813   0.6770
  -2.500  -0.1008   0.01153   0.00585  -0.0436   0.8711   0.6921
  -2.250  -0.0749   0.01158   0.00585  -0.0428   0.8631   0.7052
  -2.000  -0.0488   0.01159   0.00580  -0.0422   0.8540   0.7161
  -1.750  -0.0229   0.01160   0.00579  -0.0415   0.8456   0.7249
  -1.500   0.0038   0.01158   0.00571  -0.0410   0.8374   0.7351
  -1.250   0.0299   0.01159   0.00571  -0.0404   0.8287   0.7436
  -1.000   0.0565   0.01157   0.00563  -0.0399   0.8211   0.7526
  -0.750   0.0831   0.01158   0.00563  -0.0396   0.8122   0.7618
  -0.500   0.1095   0.01156   0.00557  -0.0390   0.8050   0.7698
   0.000   0.1625   0.01157   0.00555  -0.0380   0.7891   0.7874
   0.250   0.1893   0.01158   0.00558  -0.0378   0.7799   0.7970
   0.500   0.2155   0.01159   0.00556  -0.0371   0.7733   0.8056
   0.750   0.2415   0.01161   0.00562  -0.0367   0.7640   0.8148
   1.000   0.2684   0.01162   0.00560  -0.0362   0.7575   0.8249
   1.250   0.2933   0.01165   0.00570  -0.0355   0.7481   0.8335
   1.500   0.3197   0.01166   0.00569  -0.0350   0.7414   0.8435
   1.750   0.3447   0.01169   0.00578  -0.0343   0.7320   0.8537
   2.000   0.3697   0.01170   0.00581  -0.0333   0.7247   0.8632
   2.250   0.3946   0.01170   0.00587  -0.0326   0.7155   0.8740
   2.500   0.4191   0.01172   0.00592  -0.0317   0.7071   0.8852
   2.750   0.4427   0.01169   0.00594  -0.0304   0.6983   0.8959
   3.000   0.4660   0.01168   0.00599  -0.0292   0.6885   0.9077
   3.250   0.4899   0.01160   0.00592  -0.0280   0.6785   0.9202
   3.500   0.5141   0.01147   0.00581  -0.0268   0.6662   0.9336
   3.750   0.5406   0.01133   0.00572  -0.0262   0.6519   0.9474
   4.000   0.5720   0.01119   0.00559  -0.0265   0.6356   0.9605
   4.250   0.6076   0.01102   0.00546  -0.0279   0.6121   0.9728
   4.500   0.6471   0.01093   0.00536  -0.0302   0.5870   0.9840
   4.750   0.6885   0.01091   0.00535  -0.0330   0.5593   0.9953
   5.000   0.7113   0.01098   0.00542  -0.0325   0.5312   1.0000
   5.250   0.7312   0.01114   0.00553  -0.0314   0.4959   1.0000
   5.500   0.7526   0.01150   0.00568  -0.0305   0.4327   1.0000
   5.750   0.7671   0.01265   0.00611  -0.0290   0.2945   1.0000
   6.000   0.7745   0.01493   0.00731  -0.0273   0.1272   1.0000
   6.250   0.7909   0.01640   0.00845  -0.0261   0.0822   1.0000
   6.500   0.8105   0.01746   0.00944  -0.0253   0.0681   1.0000
   6.750   0.8284   0.01866   0.01060  -0.0242   0.0606   1.0000
   7.000   0.8491   0.01956   0.01151  -0.0234   0.0548   1.0000
   7.250   0.8663   0.02100   0.01290  -0.0222   0.0504   1.0000
   7.500   0.8882   0.02197   0.01395  -0.0215   0.0475   1.0000
   7.750   0.9100   0.02311   0.01511  -0.0208   0.0450   1.0000
   8.000   0.9325   0.02445   0.01642  -0.0203   0.0430   1.0000
   8.250   0.9582   0.02693   0.01890  -0.0202   0.0409   1.0000
   8.500   0.9810   0.02791   0.02008  -0.0196   0.0394   1.0000
   8.750   1.0048   0.02951   0.02185  -0.0191   0.0382   1.0000
   9.000   1.0281   0.03145   0.02399  -0.0186   0.0373   1.0000
   9.250   1.0496   0.03369   0.02648  -0.0180   0.0368   1.0000
   9.500   1.0683   0.03630   0.02941  -0.0170   0.0366   1.0000
   9.750   1.0831   0.03928   0.03274  -0.0157   0.0366   1.0000
  10.000   1.0944   0.04225   0.03604  -0.0143   0.0363   1.0000
  10.250   1.1034   0.04492   0.03899  -0.0128   0.0357   1.0000
  10.500   1.1014   0.04909   0.04360  -0.0104   0.0364   1.0000
  10.750   1.0917   0.05389   0.04883  -0.0078   0.0378   1.0000
  11.000   1.0803   0.05808   0.05327  -0.0054   0.0390   1.0000
  11.250   1.0683   0.06261   0.05796  -0.0036   0.0400   1.0000
  11.500   0.9641   0.05850   0.05435   0.0021   0.0396   1.0000
  11.750   0.9427   0.06425   0.06025   0.0020   0.0402   1.0000
  12.000   0.8525   0.07773   0.07435  -0.0026   0.0462   1.0000
  12.250   0.8097   0.08774   0.08453  -0.0076   0.0479   1.0000
  12.500   0.7834   0.09636   0.09321  -0.0118   0.0495   1.0000
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