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NACA 6412 (naca6412-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 6412 (naca6412-il)
Reynolds number: 50,000
Max Cl/Cd: 29.61 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca6412-il-50000-n5.txt
Download as CSV file: xf-naca6412-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 6412                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3155   0.12121   0.11463  -0.0304   1.0001   0.1160
  -8.500  -0.3221   0.11963   0.11313  -0.0288   1.0001   0.1184
  -8.250  -0.3285   0.11792   0.11150  -0.0281   0.9992   0.1206
  -8.000  -0.3281   0.11564   0.10924  -0.0339   0.9915   0.1241
  -7.500  -0.3146   0.10334   0.09684  -0.0436   0.9770   0.0819
  -7.250  -0.2966   0.09906   0.09254  -0.0472   0.9712   0.0792
  -7.000  -0.2865   0.09492   0.08839  -0.0513   0.9620   0.0777
  -6.750  -0.2720   0.09050   0.08394  -0.0568   0.9536   0.0778
  -6.500  -0.2563   0.08594   0.07935  -0.0625   0.9447   0.0781
  -6.250  -0.2424   0.08138   0.07473  -0.0677   0.9354   0.0776
  -6.000  -0.2202   0.07576   0.06900  -0.0753   0.9278   0.0766
  -5.750  -0.2041   0.07067   0.06379  -0.0807   0.9178   0.0760
  -5.500  -0.1743   0.06532   0.05823  -0.0881   0.9113   0.0778
  -5.250  -0.1539   0.06030   0.05297  -0.0931   0.9014   0.0796
  -5.000  -0.1179   0.05339   0.04554  -0.1016   0.8956   0.0811
  -4.750  -0.0901   0.04749   0.03894  -0.1070   0.8872   0.0838
  -4.500  -0.0592   0.04642   0.03787  -0.1084   0.8805   0.0876
  -4.250  -0.0278   0.04324   0.03420  -0.1113   0.8734   0.0914
  -4.000   0.0051   0.04004   0.03029  -0.1141   0.8661   0.0971
  -3.750   0.0429   0.03866   0.02876  -0.1164   0.8614   0.1028
  -3.500   0.0677   0.03693   0.02642  -0.1167   0.8515   0.1099
  -3.250   0.1037   0.03585   0.02530  -0.1184   0.8461   0.1167
  -3.000   0.1306   0.03475   0.02375  -0.1186   0.8371   0.1256
  -2.750   0.1642   0.03391   0.02289  -0.1197   0.8309   0.1337
  -2.500   0.1952   0.03312   0.02184  -0.1204   0.8234   0.1446
  -2.250   0.2254   0.03252   0.02102  -0.1208   0.8155   0.1575
  -2.000   0.2645   0.03170   0.02013  -0.1225   0.8113   0.1721
  -1.750   0.2846   0.03154   0.01993  -0.1213   0.8002   0.1844
  -1.500   0.3241   0.03087   0.01913  -0.1230   0.7955   0.2045
  -1.250   0.3470   0.03076   0.01896  -0.1222   0.7851   0.2218
  -1.000   0.3841   0.03022   0.01832  -0.1235   0.7797   0.2476
  -0.750   0.4087   0.03011   0.01824  -0.1230   0.7702   0.2709
  -0.500   0.4425   0.02964   0.01778  -0.1238   0.7639   0.3038
  -0.250   0.4703   0.02938   0.01761  -0.1238   0.7557   0.3395
   0.000   0.5002   0.02895   0.01738  -0.1241   0.7482   0.3905
   0.250   0.5357   0.02780   0.01695  -0.1250   0.7442   0.5327
   0.500   0.5543   0.02733   0.01715  -0.1229   0.7328   0.9999
   0.750   0.5911   0.02720   0.01667  -0.1240   0.7279   0.9999
   1.000   0.6096   0.02782   0.01710  -0.1227   0.7171   0.9999
   1.250   0.6444   0.02775   0.01680  -0.1234   0.7118   0.9999
   1.500   0.6635   0.02837   0.01729  -0.1222   0.7017   0.9999
   1.750   0.6960   0.02839   0.01714  -0.1227   0.6959   0.9999
   2.000   0.7171   0.02896   0.01761  -0.1218   0.6869   0.9999
   2.250   0.7458   0.02917   0.01769  -0.1218   0.6802   0.9999
   2.500   0.7741   0.02941   0.01783  -0.1217   0.6738   0.9999
   2.750   0.7942   0.03005   0.01842  -0.1207   0.6650   0.9999
   3.000   0.8293   0.02997   0.01824  -0.1215   0.6605   0.9999
   3.250   0.8417   0.03103   0.01929  -0.1196   0.6502   0.9999
   3.500   0.8739   0.03108   0.01928  -0.1200   0.6450   0.9999
   3.750   0.8903   0.03199   0.02020  -0.1186   0.6365   0.9999
   4.000   0.9165   0.03236   0.02054  -0.1183   0.6299   0.9999
   4.250   0.9532   0.03219   0.02033  -0.1192   0.6259   0.9999
   4.500   0.9576   0.03376   0.02196  -0.1165   0.6152   0.9999
   4.750   0.9916   0.03371   0.02191  -0.1170   0.6105   0.9999
   5.000   0.9992   0.03515   0.02341  -0.1147   0.6010   0.9999
   5.250   1.0275   0.03543   0.02370  -0.1146   0.5953   0.9999
   5.500   1.0497   0.03606   0.02439  -0.1139   0.5889   0.9999
   5.750   1.0605   0.03730   0.02570  -0.1119   0.5803   0.9999
   6.000   1.0979   0.03708   0.02551  -0.1128   0.5761   0.9999
   6.250   1.0918   0.03929   0.02781  -0.1090   0.5654   0.9999
   6.500   1.1254   0.03923   0.02783  -0.1095   0.5605   0.9999
   6.750   1.1240   0.04126   0.02996  -0.1063   0.5507   0.9999
   7.000   1.1501   0.04160   0.03038  -0.1059   0.5447   0.9999
   7.500   1.1732   0.04417   0.03317  -0.1025   0.5287   0.9999
   7.750   1.2179   0.04323   0.03233  -0.1036   0.5249   0.9999
   8.000   1.1947   0.04692   0.03613  -0.0990   0.5122   0.9999
   8.250   1.2389   0.04582   0.03517  -0.0998   0.5084   0.9999
   8.500   1.2140   0.04988   0.03935  -0.0957   0.4954   0.9999
   8.750   1.2611   0.04830   0.03791  -0.0963   0.4915   0.9999
   9.000   1.2345   0.05269   0.04240  -0.0924   0.4779   0.9999
   9.250   1.2540   0.05321   0.04306  -0.0912   0.4704   0.9999
   9.500   1.2573   0.05516   0.04513  -0.0893   0.4600   0.9999
  10.000   1.2860   0.05679   0.04707  -0.0863   0.4418   0.9999
  10.250   1.2636   0.06147   0.05185  -0.0840   0.4276   0.9999
  10.500   1.2559   0.06476   0.05526  -0.0823   0.4149   0.9999
  10.750   1.3054   0.06102   0.05172  -0.0809   0.4084   0.9999
  11.000   1.2890   0.06512   0.05594  -0.0791   0.3940   0.9999
  11.250   1.2824   0.06819   0.05912  -0.0777   0.3801   0.9999
  11.500   1.2867   0.06979   0.06085  -0.0762   0.3670   0.9999
  11.750   1.3038   0.06950   0.06070  -0.0744   0.3542   0.9999
  12.000   1.3175   0.06962   0.06096  -0.0728   0.3401   0.9999
  12.250   1.3215   0.07116   0.06261  -0.0714   0.3247   0.9999
  12.500   1.3214   0.07337   0.06493  -0.0702   0.3084   0.9999
  12.750   1.3200   0.07587   0.06752  -0.0693   0.2911   0.9999
  13.000   1.3209   0.07811   0.06983  -0.0683   0.2729   0.9999
  13.250   1.3254   0.07978   0.07152  -0.0672   0.2534   0.9999
  13.500   1.3309   0.08128   0.07295  -0.0660   0.2328   0.9999
  13.750   1.3259   0.08468   0.07635  -0.0656   0.2128   0.9999
  14.000   1.3230   0.08775   0.07932  -0.0651   0.1935   0.9999
  14.250   1.3190   0.09105   0.08248  -0.0647   0.1761   0.9999
  14.500   1.3136   0.09468   0.08599  -0.0645   0.1607   0.9999
  14.750   1.3081   0.09854   0.08977  -0.0646   0.1472   0.9999
  15.000   1.3033   0.10242   0.09362  -0.0648   0.1353   0.9999
  15.250   1.2998   0.10615   0.09732  -0.0650   0.1250   0.9999
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