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NACA 65(1)-412 (naca651412-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 65(1)-412 (naca651412-il)
Reynolds number: 100,000
Max Cl/Cd: 51.57 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca651412-il-100000-n5.txt
Download as CSV file: xf-naca651412-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(1)-412                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4401   0.09480   0.08962  -0.0522   1.0000   0.0326
 -10.250  -0.4461   0.08945   0.08432  -0.0549   1.0000   0.0326
 -10.000  -0.4523   0.08428   0.07922  -0.0574   1.0000   0.0324
  -9.750  -0.4621   0.07882   0.07381  -0.0604   1.0000   0.0322
  -9.500  -0.4763   0.07421   0.06924  -0.0623   1.0000   0.0318
  -9.250  -0.4962   0.07052   0.06559  -0.0626   1.0000   0.0316
  -9.000  -0.5208   0.06821   0.06334  -0.0602   1.0000   0.0311
  -8.750  -0.5495   0.06663   0.06180  -0.0560   1.0000   0.0310
  -8.500  -0.5626   0.06283   0.05786  -0.0562   0.9956   0.0310
  -8.250  -0.5557   0.05701   0.05169  -0.0608   0.9860   0.0313
  -8.000  -0.5459   0.05175   0.04598  -0.0639   0.9768   0.0318
  -7.750  -0.5319   0.04727   0.04108  -0.0658   0.9685   0.0318
  -7.500  -0.5120   0.04292   0.03621  -0.0678   0.9625   0.0319
  -7.250  -0.4930   0.03941   0.03220  -0.0686   0.9547   0.0322
  -7.000  -0.4648   0.03651   0.02858  -0.0703   0.9502   0.0333
  -6.750  -0.4442   0.03359   0.02543  -0.0708   0.9430   0.0347
  -6.500  -0.4152   0.03141   0.02298  -0.0721   0.9383   0.0360
  -6.250  -0.3829   0.02928   0.02051  -0.0736   0.9349   0.0369
  -6.000  -0.3588   0.02769   0.01864  -0.0733   0.9276   0.0379
  -5.750  -0.3277   0.02626   0.01697  -0.0742   0.9231   0.0401
  -5.500  -0.2938   0.02495   0.01540  -0.0754   0.9199   0.0425
  -5.250  -0.2697   0.02391   0.01418  -0.0748   0.9123   0.0436
  -5.000  -0.2400   0.02252   0.01276  -0.0753   0.9079   0.0451
  -4.750  -0.2109   0.02151   0.01178  -0.0759   0.9035   0.0478
  -4.500  -0.1875   0.02087   0.01111  -0.0754   0.8962   0.0517
  -4.250  -0.1581   0.02015   0.01027  -0.0758   0.8917   0.0551
  -4.000  -0.1343   0.01943   0.00952  -0.0755   0.8853   0.0588
  -3.750  -0.1079   0.01891   0.00892  -0.0755   0.8794   0.0657
  -3.500  -0.0782   0.01826   0.00826  -0.0761   0.8754   0.0792
  -3.250  -0.0567   0.01758   0.00779  -0.0754   0.8680   0.1169
  -3.000  -0.0416   0.01540   0.00759  -0.0744   0.8625   0.5413
  -2.750  -0.0194   0.01551   0.00794  -0.0724   0.8571   0.6546
  -2.500  -0.0017   0.01596   0.00851  -0.0690   0.8506   0.7180
  -2.250   0.0179   0.01645   0.00901  -0.0655   0.8463   0.7619
  -2.000   0.0385   0.01664   0.00913  -0.0635   0.8400   0.7781
  -1.750   0.0648   0.01662   0.00899  -0.0631   0.8346   0.7849
  -1.500   0.0955   0.01652   0.00873  -0.0638   0.8309   0.7921
  -1.250   0.1188   0.01656   0.00870  -0.0630   0.8248   0.7978
  -1.000   0.1461   0.01653   0.00857  -0.0631   0.8196   0.8049
  -0.750   0.1754   0.01646   0.00842  -0.0633   0.8158   0.8104
  -0.500   0.1991   0.01652   0.00844  -0.0628   0.8099   0.8170
  -0.250   0.2256   0.01653   0.00839  -0.0627   0.8047   0.8237
   0.000   0.2542   0.01649   0.00831  -0.0628   0.8010   0.8295
   0.250   0.2789   0.01657   0.00836  -0.0625   0.7953   0.8372
   0.500   0.3031   0.01662   0.00842  -0.0619   0.7900   0.8432
   0.750   0.3323   0.01660   0.00837  -0.0622   0.7863   0.8506
   1.000   0.3558   0.01669   0.00849  -0.0615   0.7808   0.8572
   1.250   0.3804   0.01679   0.00860  -0.0611   0.7754   0.8654
   1.500   0.4082   0.01678   0.00862  -0.0611   0.7716   0.8721
   1.750   0.4327   0.01689   0.00876  -0.0607   0.7664   0.8808
   2.000   0.4555   0.01701   0.00896  -0.0598   0.7607   0.8890
   2.250   0.4837   0.01702   0.00901  -0.0599   0.7567   0.8978
   2.500   0.5082   0.01712   0.00920  -0.0594   0.7517   0.9071
   2.750   0.5317   0.01726   0.00944  -0.0588   0.7457   0.9174
   3.000   0.5611   0.01726   0.00952  -0.0592   0.7417   0.9276
   3.250   0.5872   0.01739   0.00977  -0.0591   0.7358   0.9395
   3.500   0.6174   0.01746   0.00996  -0.0598   0.7295   0.9506
   3.750   0.6554   0.01734   0.00998  -0.0617   0.7251   0.9601
   4.000   0.6870   0.01753   0.01034  -0.0630   0.7161   0.9748
   4.250   0.7260   0.01732   0.01028  -0.0650   0.7076   0.9901
   4.500   0.7528   0.01702   0.01007  -0.0644   0.6916   1.0000
   4.750   0.7757   0.01632   0.00935  -0.0624   0.6584   1.0000
   5.000   0.7960   0.01577   0.00866  -0.0599   0.6059   1.0000
   5.250   0.8143   0.01579   0.00860  -0.0579   0.5480   1.0000
   5.500   0.8294   0.01621   0.00849  -0.0553   0.4332   1.0000
   5.750   0.8266   0.01803   0.00922  -0.0509   0.2688   1.0000
   6.000   0.8256   0.02011   0.01040  -0.0473   0.1315   1.0000
   6.250   0.8344   0.02161   0.01147  -0.0450   0.0791   1.0000
   6.500   0.8483   0.02269   0.01247  -0.0433   0.0630   1.0000
   6.750   0.8611   0.02374   0.01350  -0.0414   0.0548   1.0000
   7.000   0.8755   0.02471   0.01457  -0.0397   0.0502   1.0000
   7.250   0.8885   0.02581   0.01570  -0.0380   0.0464   1.0000
   7.500   0.9009   0.02701   0.01695  -0.0362   0.0432   1.0000
   7.750   0.9158   0.02813   0.01817  -0.0348   0.0405   1.0000
   8.000   0.9311   0.02939   0.01951  -0.0334   0.0386   1.0000
   8.250   0.9484   0.03073   0.02088  -0.0324   0.0370   1.0000
   8.500   0.9691   0.03233   0.02246  -0.0318   0.0353   1.0000
   8.750   0.9954   0.03399   0.02420  -0.0319   0.0336   1.0000
   9.000   1.0206   0.03547   0.02590  -0.0317   0.0319   1.0000
   9.250   1.0490   0.03736   0.02798  -0.0321   0.0307   1.0000
   9.500   1.0765   0.03951   0.03035  -0.0324   0.0298   1.0000
   9.750   1.1003   0.04184   0.03293  -0.0323   0.0290   1.0000
  10.000   1.1195   0.04430   0.03567  -0.0317   0.0285   1.0000
  10.250   1.1338   0.04688   0.03857  -0.0306   0.0281   1.0000
  10.500   1.1431   0.04939   0.04134  -0.0290   0.0276   1.0000
  10.750   1.1491   0.05187   0.04403  -0.0273   0.0270   1.0000
  11.000   1.1527   0.05479   0.04714  -0.0257   0.0264   1.0000
  11.250   1.1494   0.05832   0.05091  -0.0236   0.0259   1.0000
  11.500   1.1388   0.06101   0.05396  -0.0209   0.0257   1.0000
  11.750   1.1270   0.06419   0.05746  -0.0187   0.0255   1.0000
  12.000   1.1139   0.06782   0.06138  -0.0171   0.0254   1.0000
  12.250   1.0988   0.07183   0.06567  -0.0161   0.0254   1.0000
  12.500   1.0817   0.07627   0.07036  -0.0158   0.0254   1.0000
  12.750   1.0633   0.08113   0.07546  -0.0162   0.0254   1.0000
  13.000   1.0438   0.08649   0.08103  -0.0174   0.0254   1.0000
  13.250   1.0231   0.09246   0.08720  -0.0195   0.0255   1.0000
  13.500   1.0023   0.09902   0.09394  -0.0226   0.0256   1.0000
  13.750   0.9811   0.10631   0.10137  -0.0265   0.0257   1.0000
  14.000   0.9607   0.11439   0.10958  -0.0314   0.0259   1.0000
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