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NACA 64(1)-212 (n64212-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 64(1)-212 (n64212-il)
Reynolds number: 100,000
Max Cl/Cd: 45.88 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64212-il-100000-n5.txt
Download as CSV file: xf-n64212-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(1)-212                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.6049   0.09003   0.08476  -0.0334   1.0000   0.0319
 -11.250  -0.6173   0.08310   0.07781  -0.0379   1.0000   0.0316
 -11.000  -0.6340   0.07639   0.07108  -0.0424   1.0000   0.0314
 -10.750  -0.6527   0.07050   0.06511  -0.0462   1.0000   0.0311
 -10.500  -0.6732   0.06536   0.05984  -0.0489   1.0000   0.0310
 -10.250  -0.6916   0.06125   0.05560  -0.0498   1.0000   0.0310
 -10.000  -0.7099   0.05775   0.05194  -0.0491   1.0000   0.0309
  -9.750  -0.7219   0.05429   0.04825  -0.0479   1.0000   0.0309
  -9.500  -0.7286   0.05080   0.04448  -0.0467   1.0000   0.0310
  -9.250  -0.7315   0.04738   0.04071  -0.0452   1.0000   0.0311
  -9.000  -0.7298   0.04419   0.03715  -0.0437   1.0000   0.0313
  -8.750  -0.7246   0.04126   0.03380  -0.0420   1.0000   0.0316
  -8.500  -0.7167   0.03861   0.03078  -0.0403   1.0000   0.0322
  -8.250  -0.7052   0.03642   0.02849  -0.0390   1.0000   0.0332
  -8.000  -0.6925   0.03490   0.02686  -0.0375   1.0000   0.0344
  -7.750  -0.6797   0.03330   0.02509  -0.0358   1.0000   0.0355
  -7.500  -0.6670   0.03160   0.02317  -0.0339   1.0000   0.0363
  -7.250  -0.6541   0.03000   0.02133  -0.0318   1.0000   0.0371
  -7.000  -0.6408   0.02858   0.01970  -0.0297   1.0000   0.0380
  -6.750  -0.6112   0.02691   0.01779  -0.0305   0.9946   0.0394
  -6.500  -0.5773   0.02543   0.01610  -0.0321   0.9875   0.0416
  -6.250  -0.5447   0.02407   0.01476  -0.0339   0.9803   0.0446
  -6.000  -0.5097   0.02286   0.01349  -0.0358   0.9741   0.0476
  -5.750  -0.4772   0.02184   0.01236  -0.0371   0.9662   0.0508
  -5.500  -0.4451   0.02078   0.01133  -0.0388   0.9587   0.0559
  -5.250  -0.4129   0.01994   0.01040  -0.0401   0.9507   0.0617
  -5.000  -0.3833   0.01910   0.00954  -0.0411   0.9416   0.0696
  -4.750  -0.3513   0.01828   0.00873  -0.0424   0.9341   0.0830
  -4.500  -0.3250   0.01743   0.00799  -0.0427   0.9237   0.1108
  -4.250  -0.3009   0.01596   0.00719  -0.0433   0.9145   0.2333
  -4.000  -0.2810   0.01465   0.00700  -0.0426   0.9048   0.4680
  -3.750  -0.2556   0.01454   0.00704  -0.0418   0.8952   0.5458
  -3.250  -0.2044   0.01483   0.00740  -0.0397   0.8775   0.6459
  -3.000  -0.1797   0.01513   0.00773  -0.0380   0.8694   0.6794
  -2.750  -0.1537   0.01524   0.00775  -0.0370   0.8606   0.6960
  -2.500  -0.1265   0.01519   0.00758  -0.0368   0.8522   0.7053
  -2.250  -0.0990   0.01514   0.00744  -0.0365   0.8442   0.7134
  -2.000  -0.0721   0.01509   0.00727  -0.0363   0.8356   0.7227
  -1.750  -0.0446   0.01503   0.00714  -0.0360   0.8283   0.7290
  -1.500  -0.0178   0.01499   0.00702  -0.0358   0.8198   0.7369
  -1.250   0.0096   0.01494   0.00689  -0.0356   0.8127   0.7435
  -1.000   0.0362   0.01491   0.00682  -0.0354   0.8043   0.7508
  -0.750   0.0635   0.01487   0.00672  -0.0351   0.7973   0.7580
  -0.500   0.0898   0.01487   0.00670  -0.0348   0.7896   0.7656
  -0.250   0.1169   0.01485   0.00665  -0.0346   0.7827   0.7732
   0.000   0.1433   0.01487   0.00665  -0.0343   0.7753   0.7806
   0.250   0.1699   0.01487   0.00664  -0.0340   0.7681   0.7887
   0.500   0.1964   0.01489   0.00667  -0.0337   0.7615   0.7971
   0.750   0.2226   0.01493   0.00673  -0.0333   0.7545   0.8053
   1.000   0.2497   0.01494   0.00673  -0.0331   0.7489   0.8141
   1.250   0.2749   0.01502   0.00688  -0.0326   0.7409   0.8225
   1.500   0.3018   0.01504   0.00691  -0.0323   0.7353   0.8325
   1.750   0.3269   0.01514   0.00709  -0.0318   0.7283   0.8415
   2.000   0.3530   0.01519   0.00720  -0.0313   0.7221   0.8511
   2.250   0.3789   0.01527   0.00733  -0.0309   0.7159   0.8621
   2.500   0.4040   0.01535   0.00752  -0.0303   0.7088   0.8721
   2.750   0.4307   0.01537   0.00761  -0.0298   0.7028   0.8828
   3.000   0.4555   0.01546   0.00782  -0.0292   0.6940   0.8949
   3.250   0.4828   0.01548   0.00790  -0.0289   0.6876   0.9074
   3.500   0.5094   0.01557   0.00816  -0.0287   0.6787   0.9203
   3.750   0.5390   0.01556   0.00826  -0.0288   0.6693   0.9333
   4.000   0.5697   0.01541   0.00819  -0.0290   0.6523   0.9466
   4.250   0.6021   0.01509   0.00791  -0.0293   0.6254   0.9600
   4.500   0.6350   0.01484   0.00764  -0.0298   0.5848   0.9755
   4.750   0.6679   0.01478   0.00752  -0.0308   0.5353   0.9984
   5.000   0.6864   0.01496   0.00761  -0.0292   0.4863   1.0000
   5.250   0.7013   0.01551   0.00769  -0.0270   0.3756   1.0000
   5.500   0.7078   0.01715   0.00837  -0.0245   0.2260   1.0000
   5.750   0.7191   0.01872   0.00934  -0.0228   0.1315   1.0000
   6.000   0.7345   0.01995   0.01026  -0.0215   0.0913   1.0000
   6.250   0.7523   0.02096   0.01120  -0.0204   0.0744   1.0000
   6.500   0.7698   0.02197   0.01218  -0.0193   0.0646   1.0000
   6.750   0.7878   0.02292   0.01314  -0.0182   0.0575   1.0000
   7.000   0.8050   0.02397   0.01423  -0.0170   0.0530   1.0000
   7.250   0.8232   0.02494   0.01524  -0.0160   0.0483   1.0000
   7.500   0.8388   0.02625   0.01649  -0.0148   0.0450   1.0000
   7.750   0.8586   0.02739   0.01777  -0.0138   0.0429   1.0000
   8.000   0.8792   0.02864   0.01911  -0.0131   0.0405   1.0000
   8.250   0.8995   0.02985   0.02037  -0.0124   0.0380   1.0000
   8.500   0.9197   0.03135   0.02182  -0.0119   0.0359   1.0000
   8.750   0.9434   0.03315   0.02377  -0.0116   0.0346   1.0000
   9.000   0.9670   0.03499   0.02584  -0.0112   0.0335   1.0000
   9.250   0.9889   0.03705   0.02815  -0.0107   0.0326   1.0000
   9.500   1.0083   0.03931   0.03070  -0.0100   0.0318   1.0000
   9.750   1.0245   0.04168   0.03336  -0.0091   0.0311   1.0000
  10.000   1.0373   0.04391   0.03587  -0.0080   0.0302   1.0000
  10.250   1.0476   0.04601   0.03819  -0.0067   0.0293   1.0000
  10.500   1.0556   0.04814   0.04050  -0.0054   0.0285   1.0000
  10.750   1.0609   0.05052   0.04301  -0.0041   0.0277   1.0000
  11.000   1.0610   0.05347   0.04618  -0.0023   0.0274   1.0000
  11.250   1.0545   0.05668   0.04964  -0.0003   0.0272   1.0000
  11.500   1.0434   0.05985   0.05311   0.0015   0.0271   1.0000
  11.750   1.0304   0.06336   0.05689   0.0026   0.0271   1.0000
  12.000   1.0147   0.06733   0.06112   0.0030   0.0271   1.0000
  12.250   0.9973   0.07177   0.06580   0.0026   0.0271   1.0000
  12.500   0.9786   0.07677   0.07102   0.0013   0.0271   1.0000
  12.750   0.9591   0.08233   0.07677  -0.0009   0.0271   1.0000
  13.000   0.9382   0.08866   0.08328  -0.0041   0.0272   1.0000
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