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NACA 65(1)-212 a=0.6 (naca651212a06-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 65(1)-212 a=0.6 (naca651212a06-il)
Reynolds number: 200,000
Max Cl/Cd: 56.65 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca651212a06-il-200000-n5.txt
Download as CSV file: xf-naca651212a06-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(1)-212 a=0.6                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5422   0.08996   0.08643  -0.0349   1.0000   0.0188
 -10.750  -0.5552   0.08122   0.07774  -0.0408   1.0000   0.0187
 -10.500  -0.5776   0.07089   0.06738  -0.0491   1.0000   0.0184
 -10.250  -0.6001   0.06419   0.06058  -0.0537   1.0000   0.0181
 -10.000  -0.6225   0.05902   0.05530  -0.0559   1.0000   0.0179
  -9.750  -0.6448   0.05482   0.05095  -0.0553   1.0000   0.0179
  -9.500  -0.6558   0.05028   0.04616  -0.0554   0.9729   0.0179
  -9.250  -0.6555   0.04506   0.04050  -0.0566   0.9520   0.0181
  -9.000  -0.6539   0.04075   0.03575  -0.0557   0.9363   0.0184
  -8.750  -0.6504   0.03711   0.03163  -0.0539   0.9228   0.0188
  -8.500  -0.6429   0.03410   0.02809  -0.0518   0.9115   0.0197
  -8.250  -0.6320   0.03165   0.02516  -0.0500   0.9024   0.0205
  -8.000  -0.6160   0.02966   0.02296  -0.0489   0.8940   0.0210
  -7.750  -0.5980   0.02806   0.02113  -0.0479   0.8869   0.0215
  -7.500  -0.5784   0.02661   0.01944  -0.0469   0.8794   0.0221
  -7.250  -0.5579   0.02524   0.01783  -0.0459   0.8736   0.0226
  -7.000  -0.5354   0.02397   0.01636  -0.0453   0.8669   0.0234
  -6.750  -0.5128   0.02297   0.01516  -0.0445   0.8611   0.0246
  -6.500  -0.4892   0.02199   0.01397  -0.0439   0.8555   0.0258
  -6.250  -0.4650   0.02096   0.01275  -0.0433   0.8496   0.0264
  -6.000  -0.4410   0.02009   0.01173  -0.0426   0.8448   0.0269
  -5.750  -0.4184   0.01871   0.01031  -0.0420   0.8396   0.0280
  -5.500  -0.3955   0.01788   0.00945  -0.0414   0.8339   0.0290
  -5.250  -0.3724   0.01727   0.00877  -0.0407   0.8293   0.0307
  -5.000  -0.3486   0.01673   0.00818  -0.0402   0.8245   0.0328
  -4.750  -0.3249   0.01617   0.00755  -0.0396   0.8193   0.0344
  -4.500  -0.3013   0.01566   0.00694  -0.0389   0.8149   0.0357
  -4.250  -0.2787   0.01502   0.00623  -0.0382   0.8105   0.0380
  -4.000  -0.2543   0.01458   0.00576  -0.0378   0.8053   0.0415
  -3.750  -0.2292   0.01425   0.00535  -0.0374   0.8010   0.0464
  -3.500  -0.2046   0.01384   0.00491  -0.0369   0.7975   0.0540
  -3.250  -0.1797   0.01343   0.00456  -0.0366   0.7929   0.0740
  -3.000  -0.1599   0.01237   0.00413  -0.0359   0.7881   0.2173
  -2.750  -0.1447   0.01100   0.00381  -0.0343   0.7840   0.4687
  -2.500  -0.1225   0.01069   0.00386  -0.0332   0.7805   0.5863
  -2.250  -0.0992   0.01060   0.00401  -0.0320   0.7760   0.6571
  -2.000  -0.0750   0.01063   0.00413  -0.0310   0.7719   0.7003
  -1.750  -0.0495   0.01068   0.00418  -0.0302   0.7683   0.7237
  -1.500  -0.0227   0.01069   0.00414  -0.0299   0.7649   0.7361
  -1.250   0.0051   0.01070   0.00408  -0.0300   0.7606   0.7436
  -1.000   0.0327   0.01068   0.00403  -0.0300   0.7568   0.7497
  -0.750   0.0605   0.01067   0.00395  -0.0300   0.7533   0.7569
  -0.500   0.0883   0.01065   0.00387  -0.0301   0.7502   0.7634
  -0.250   0.1159   0.01066   0.00386  -0.0302   0.7458   0.7710
   0.000   0.1435   0.01064   0.00383  -0.0303   0.7419   0.7777
   0.250   0.1713   0.01062   0.00378  -0.0303   0.7384   0.7855
   0.500   0.1991   0.01057   0.00373  -0.0303   0.7355   0.7921
   0.750   0.2266   0.01056   0.00377  -0.0304   0.7311   0.8000
   1.000   0.2539   0.01053   0.00382  -0.0304   0.7270   0.8072
   1.250   0.2813   0.01052   0.00386  -0.0302   0.7234   0.8148
   1.500   0.3086   0.01054   0.00395  -0.0300   0.7205   0.8229
   1.750   0.3349   0.01063   0.00419  -0.0295   0.7161   0.8312
   2.000   0.3616   0.01075   0.00442  -0.0291   0.7119   0.8400
   2.250   0.3893   0.01085   0.00462  -0.0287   0.7082   0.8499
   2.750   0.4360   0.01116   0.00497  -0.0273   0.7000   0.9066
   3.000   0.4620   0.01119   0.00507  -0.0269   0.6948   0.9160
   3.250   0.4895   0.01115   0.00506  -0.0267   0.6897   0.9241
   3.500   0.5158   0.01110   0.00511  -0.0263   0.6787   0.9325
   3.750   0.5451   0.01086   0.00486  -0.0261   0.6583   0.9396
   4.000   0.5730   0.01066   0.00463  -0.0258   0.6189   0.9475
   4.250   0.6029   0.01066   0.00451  -0.0261   0.5652   0.9543
   4.500   0.6283   0.01109   0.00451  -0.0258   0.4635   0.9617
   4.750   0.6429   0.01280   0.00522  -0.0248   0.2712   0.9717
   5.000   0.6608   0.01458   0.00618  -0.0248   0.1127   0.9817
   5.250   0.6852   0.01565   0.00693  -0.0253   0.0570   0.9913
   5.500   0.7104   0.01635   0.00759  -0.0255   0.0441   1.0000
   5.750   0.7238   0.01691   0.00815  -0.0232   0.0387   1.0000
   6.000   0.7385   0.01742   0.00872  -0.0211   0.0357   1.0000
   6.250   0.7526   0.01803   0.00936  -0.0190   0.0331   1.0000
   6.500   0.7638   0.01886   0.01024  -0.0166   0.0307   1.0000
   6.750   0.7787   0.01950   0.01093  -0.0147   0.0292   1.0000
   7.000   0.7940   0.02014   0.01163  -0.0130   0.0273   1.0000
   7.250   0.8076   0.02089   0.01242  -0.0110   0.0261   1.0000
   7.500   0.8205   0.02168   0.01326  -0.0090   0.0252   1.0000
   7.750   0.8339   0.02255   0.01417  -0.0071   0.0243   1.0000
   8.000   0.8482   0.02357   0.01520  -0.0054   0.0235   1.0000
   8.250   0.8650   0.02491   0.01656  -0.0042   0.0228   1.0000
   8.500   0.8858   0.02611   0.01784  -0.0034   0.0222   1.0000
   8.750   0.9082   0.02729   0.01913  -0.0029   0.0218   1.0000
   9.000   0.9302   0.02847   0.02047  -0.0023   0.0212   1.0000
   9.250   0.9509   0.02970   0.02185  -0.0017   0.0203   1.0000
   9.500   0.9704   0.03098   0.02328  -0.0009   0.0196   1.0000
   9.750   0.9887   0.03240   0.02486   0.0000   0.0189   1.0000
  10.000   1.0064   0.03405   0.02669   0.0009   0.0186   1.0000
  10.250   1.0211   0.03574   0.02857   0.0021   0.0182   1.0000
  10.500   1.0328   0.03745   0.03048   0.0035   0.0179   1.0000
  10.750   1.0424   0.03934   0.03255   0.0051   0.0176   1.0000
  11.000   1.0495   0.04137   0.03475   0.0067   0.0173   1.0000
  11.250   1.0534   0.04373   0.03734   0.0085   0.0172   1.0000
  11.500   1.0534   0.04659   0.04040   0.0103   0.0169   1.0000
  11.750   1.0478   0.04952   0.04358   0.0123   0.0168   1.0000
  12.000   1.0382   0.05227   0.04663   0.0143   0.0166   1.0000
  12.250   1.0254   0.05556   0.05023   0.0159   0.0164   1.0000
  12.500   1.0099   0.05930   0.05427   0.0169   0.0161   1.0000
  12.750   0.9938   0.06353   0.05873   0.0173   0.0161   1.0000
  13.000   0.9736   0.06844   0.06390   0.0168   0.0159   1.0000
  13.250   0.9531   0.07381   0.06950   0.0155   0.0159   1.0000
  13.500   0.9315   0.07985   0.07573   0.0132   0.0159   1.0000
  13.750   0.9063   0.08718   0.08325   0.0096   0.0160   1.0000
  14.000   0.8807   0.09572   0.09195   0.0046   0.0161   1.0000
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