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NACA 6412 (naca6412-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 6412 (naca6412-il)
Reynolds number: 200,000
Max Cl/Cd: 79.99 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca6412-il-200000.txt
Download as CSV file: xf-naca6412-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.1668   0.08960   0.08612  -0.0733   0.9635   0.0672
  -7.750  -0.1641   0.08548   0.08200  -0.0833   0.9536   0.0713
  -7.500  -0.1520   0.07897   0.07549  -0.0933   0.9452   0.0728
  -7.250  -0.1249   0.07680   0.07330  -0.0911   0.9442   0.0743
  -7.000  -0.0951   0.07338   0.06986  -0.0957   0.9424   0.0770
  -6.750  -0.0779   0.06385   0.06012  -0.1193   0.9279   0.0837
  -6.500  -0.0530   0.06111   0.05743  -0.1181   0.9269   0.0848
  -6.250  -0.0552   0.04110   0.03671  -0.1339   0.9129   0.0632
  -6.000  -0.0258   0.03333   0.02830  -0.1398   0.9103   0.0604
  -5.750  -0.0160   0.02910   0.02351  -0.1388   0.8995   0.0602
  -5.500   0.0168   0.02553   0.01914  -0.1410   0.8965   0.0619
  -5.250   0.0521   0.02358   0.01704  -0.1430   0.8944   0.0648
  -5.000   0.0715   0.02283   0.01618  -0.1414   0.8850   0.0671
  -4.750   0.1053   0.02132   0.01430  -0.1425   0.8812   0.0705
  -4.500   0.1409   0.01993   0.01274  -0.1439   0.8784   0.0749
  -4.250   0.1636   0.01949   0.01224  -0.1427   0.8697   0.0791
  -4.000   0.1960   0.01850   0.01100  -0.1433   0.8650   0.0842
  -3.750   0.2309   0.01774   0.01026  -0.1444   0.8615   0.0910
  -3.500   0.2541   0.01727   0.00965  -0.1432   0.8519   0.0969
  -3.250   0.2864   0.01660   0.00900  -0.1438   0.8467   0.1050
  -3.000   0.3136   0.01607   0.00840  -0.1434   0.8390   0.1133
  -2.750   0.3429   0.01568   0.00797  -0.1433   0.8316   0.1229
  -2.500   0.3724   0.01517   0.00747  -0.1434   0.8246   0.1335
  -2.250   0.3994   0.01476   0.00703  -0.1429   0.8155   0.1450
  -2.000   0.4287   0.01447   0.00668  -0.1428   0.8078   0.1587
  -1.750   0.4557   0.01419   0.00641  -0.1425   0.7984   0.1744
  -1.500   0.4834   0.01393   0.00616  -0.1422   0.7896   0.1921
  -1.250   0.5114   0.01366   0.00589  -0.1419   0.7802   0.2116
  -1.000   0.5373   0.01345   0.00574  -0.1414   0.7697   0.2328
  -0.750   0.5667   0.01321   0.00551  -0.1414   0.7611   0.2584
  -0.500   0.5912   0.01309   0.00545  -0.1406   0.7495   0.2858
  -0.250   0.6182   0.01291   0.00533  -0.1403   0.7397   0.3198
   0.000   0.6441   0.01267   0.00521  -0.1398   0.7293   0.3641
   0.250   0.6667   0.01228   0.00521  -0.1387   0.7183   0.4649
   0.500   0.7208   0.01120   0.00511  -0.1439   0.7093   0.9999
   0.750   0.7460   0.01134   0.00512  -0.1432   0.6978   0.9999
   1.000   0.7725   0.01149   0.00512  -0.1428   0.6877   0.9999
   1.250   0.7997   0.01164   0.00511  -0.1425   0.6781   0.9999
   1.500   0.8250   0.01182   0.00522  -0.1420   0.6680   0.9999
   1.750   0.8532   0.01200   0.00522  -0.1419   0.6597   0.9999
   2.000   0.8775   0.01220   0.00538  -0.1412   0.6496   0.9999
   2.250   0.9054   0.01240   0.00545  -0.1411   0.6420   0.9999
   2.500   0.9299   0.01261   0.00564  -0.1405   0.6328   0.9999
   2.750   0.9581   0.01284   0.00572  -0.1405   0.6256   0.9999
   3.000   0.9820   0.01306   0.00596  -0.1397   0.6170   0.9999
   3.250   1.0096   0.01329   0.00609  -0.1396   0.6101   0.9999
   3.500   1.0342   0.01354   0.00635  -0.1391   0.6024   0.9999
   3.750   1.0606   0.01377   0.00654  -0.1388   0.5954   0.9999
   4.000   1.0869   0.01405   0.00677  -0.1385   0.5888   0.9999
   4.250   1.1117   0.01430   0.00703  -0.1380   0.5816   0.9999
   4.500   1.1397   0.01457   0.00723  -0.1380   0.5756   0.9999
   4.750   1.1630   0.01485   0.00757  -0.1373   0.5684   0.9999
   5.000   1.1890   0.01511   0.00781  -0.1370   0.5619   0.9999
   5.250   1.2155   0.01542   0.00810  -0.1368   0.5560   0.9999
   5.500   1.2388   0.01570   0.00844  -0.1360   0.5488   0.9999
   5.750   1.2659   0.01597   0.00867  -0.1359   0.5427   0.9999
   6.000   1.2893   0.01630   0.00908  -0.1352   0.5361   0.9999
   6.250   1.3138   0.01658   0.00940  -0.1346   0.5294   0.9999
   6.500   1.3403   0.01690   0.00968  -0.1345   0.5230   0.9999
   6.750   1.3613   0.01718   0.01006  -0.1333   0.5149   0.9999
   7.000   1.3882   0.01746   0.01029  -0.1331   0.5078   0.9999
   7.250   1.4068   0.01771   0.01067  -0.1315   0.4985   0.9999
   7.500   1.4296   0.01792   0.01083  -0.1305   0.4885   0.9999
   7.750   1.4476   0.01810   0.01109  -0.1287   0.4774   0.9999
   8.000   1.4661   0.01835   0.01139  -0.1270   0.4667   0.9999
   8.250   1.4878   0.01860   0.01159  -0.1259   0.4569   0.9999
   8.500   1.5025   0.01888   0.01201  -0.1236   0.4463   0.9999
   8.750   1.5206   0.01917   0.01235  -0.1219   0.4363   0.9999
   9.000   1.5355   0.01946   0.01268  -0.1196   0.4250   0.9999
   9.250   1.5477   0.01979   0.01312  -0.1169   0.4128   0.9999
   9.500   1.5582   0.02015   0.01353  -0.1139   0.4005   0.9999
   9.750   1.5674   0.02059   0.01401  -0.1108   0.3871   0.9999
  10.000   1.5754   0.02114   0.01459  -0.1076   0.3724   0.9999
  10.250   1.5820   0.02180   0.01529  -0.1043   0.3557   0.9999
  10.500   1.5874   0.02262   0.01613  -0.1011   0.3364   0.9999
  10.750   1.5895   0.02370   0.01717  -0.0976   0.3141   0.9999
  11.000   1.5894   0.02506   0.01846  -0.0941   0.2887   0.9999
  11.250   1.5853   0.02680   0.02008  -0.0905   0.2606   0.9999
  11.500   1.5779   0.02895   0.02209  -0.0868   0.2304   0.9999
  11.750   1.5676   0.03153   0.02451  -0.0833   0.1991   0.9999
  12.000   1.5549   0.03453   0.02734  -0.0801   0.1694   0.9999
  12.250   1.5413   0.03785   0.03052  -0.0772   0.1446   0.9999
  12.500   1.5291   0.04126   0.03382  -0.0748   0.1235   0.9999
  12.750   1.5173   0.04486   0.03735  -0.0728   0.1084   0.9999
  13.000   1.5075   0.04844   0.04092  -0.0712   0.0967   0.9999
  13.250   1.4987   0.05208   0.04457  -0.0699   0.0877   0.9999
  13.500   1.4876   0.05611   0.04856  -0.0689   0.0813   0.9999
  13.750   1.4838   0.05943   0.05197  -0.0681   0.0747   0.9999
  14.000   1.4729   0.06361   0.05612  -0.0673   0.0704   0.9999
  14.250   1.4713   0.06682   0.05945  -0.0668   0.0656   0.9999
  14.500   1.4653   0.07058   0.06321  -0.0663   0.0621   0.9999
  14.750   1.4606   0.07412   0.06680  -0.0658   0.0589   0.9999
  15.000   1.4597   0.07732   0.07009  -0.0655   0.0557   0.9999
  15.250   1.4571   0.08070   0.07348  -0.0652   0.0531   0.9999
  15.500   1.4559   0.08371   0.07651  -0.0645   0.0507   0.9999
  15.750   1.4575   0.08666   0.07958  -0.0643   0.0483   0.9999
  16.000   1.4584   0.08961   0.08257  -0.0642   0.0461   0.9999
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