Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 64(2)-415 (naca642415-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 64(2)-415 (naca642415-il)
Reynolds number: 200,000
Max Cl/Cd: 75.37 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca642415-il-200000.txt
Download as CSV file: xf-naca642415-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(2)-415                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.4581   0.11273   0.10896  -0.0500   1.0000   0.0712
 -12.250  -0.4325   0.11271   0.10891  -0.0461   1.0000   0.0729
 -12.000  -0.4222   0.11051   0.10671  -0.0457   1.0000   0.0749
 -11.750  -0.4207   0.10689   0.10312  -0.0471   1.0000   0.0774
 -11.500  -0.4758   0.09354   0.08988  -0.0610   1.0000   0.0822
 -11.250  -0.5214   0.08478   0.08110  -0.0686   1.0000   0.0823
 -11.000  -0.4783   0.08430   0.08071  -0.0622   1.0000   0.0848
 -10.750  -0.4629   0.08373   0.08017  -0.0597   1.0000   0.0862
 -10.500  -0.4729   0.07837   0.07485  -0.0624   1.0000   0.0879
 -10.250  -0.5099   0.07062   0.06712  -0.0677   1.0000   0.0887
 -10.000  -0.6809   0.07199   0.06811  -0.0610   0.9954   0.0826
  -9.750  -0.7162   0.04736   0.04232  -0.0660   0.9855   0.0497
  -9.500  -0.6976   0.04222   0.03687  -0.0686   0.9791   0.0484
  -9.250  -0.6756   0.03769   0.03189  -0.0710   0.9727   0.0476
  -9.000  -0.6494   0.03421   0.02797  -0.0731   0.9670   0.0477
  -8.750  -0.6201   0.03178   0.02512  -0.0749   0.9606   0.0490
  -8.500  -0.5841   0.02944   0.02237  -0.0775   0.9572   0.0498
  -8.250  -0.5524   0.02759   0.02021  -0.0790   0.9513   0.0505
  -8.000  -0.5196   0.02506   0.01762  -0.0806   0.9461   0.0520
  -7.750  -0.4830   0.02381   0.01634  -0.0828   0.9418   0.0545
  -7.500  -0.4525   0.02276   0.01519  -0.0835   0.9346   0.0569
  -7.250  -0.4207   0.02172   0.01401  -0.0843   0.9278   0.0588
  -7.000  -0.3906   0.02036   0.01263  -0.0849   0.9217   0.0613
  -6.750  -0.3666   0.01956   0.01188  -0.0845   0.9124   0.0647
  -6.500  -0.3401   0.01889   0.01115  -0.0844   0.9050   0.0684
  -6.250  -0.3187   0.01808   0.01031  -0.0834   0.8954   0.0720
  -6.000  -0.2968   0.01736   0.00963  -0.0826   0.8872   0.0774
  -5.750  -0.2750   0.01675   0.00897  -0.0818   0.8783   0.0843
  -5.500  -0.2532   0.01610   0.00833  -0.0810   0.8703   0.0947
  -5.250  -0.2325   0.01527   0.00761  -0.0803   0.8617   0.1152
  -5.000  -0.2154   0.01373   0.00672  -0.0797   0.8538   0.2292
  -4.750  -0.1986   0.01242   0.00649  -0.0789   0.8452   0.4773
  -4.500  -0.1719   0.01247   0.00656  -0.0783   0.8388   0.5293
  -4.250  -0.1457   0.01260   0.00663  -0.0778   0.8306   0.5582
  -4.000  -0.1181   0.01273   0.00670  -0.0773   0.8248   0.5789
  -3.750  -0.0920   0.01290   0.00684  -0.0767   0.8170   0.5961
  -3.500  -0.0648   0.01305   0.00693  -0.0762   0.8105   0.6121
  -3.250  -0.0382   0.01326   0.00710  -0.0755   0.8041   0.6278
  -3.000  -0.0123   0.01349   0.00732  -0.0747   0.7966   0.6433
  -2.750   0.0142   0.01379   0.00759  -0.0736   0.7912   0.6599
  -2.500   0.0397   0.01404   0.00782  -0.0728   0.7836   0.6733
  -2.250   0.0666   0.01406   0.00782  -0.0723   0.7776   0.6790
  -2.000   0.0948   0.01404   0.00772  -0.0723   0.7723   0.6846
  -1.750   0.1230   0.01399   0.00759  -0.0727   0.7651   0.6912
  -1.500   0.1505   0.01396   0.00753  -0.0725   0.7599   0.6954
  -1.250   0.1781   0.01398   0.00752  -0.0724   0.7541   0.7007
  -1.000   0.2067   0.01395   0.00740  -0.0729   0.7475   0.7074
  -0.750   0.2349   0.01390   0.00731  -0.0728   0.7426   0.7113
  -0.500   0.2621   0.01394   0.00736  -0.0728   0.7369   0.7160
  -0.250   0.2903   0.01395   0.00734  -0.0731   0.7311   0.7222
   0.000   0.3193   0.01393   0.00726  -0.0734   0.7266   0.7271
   0.250   0.3466   0.01399   0.00734  -0.0733   0.7218   0.7317
   0.500   0.3741   0.01405   0.00741  -0.0735   0.7160   0.7378
   0.750   0.4028   0.01405   0.00739  -0.0737   0.7113   0.7438
   1.000   0.4308   0.01412   0.00745  -0.0737   0.7074   0.7490
   1.250   0.4577   0.01424   0.00763  -0.0738   0.7017   0.7558
   1.500   0.4852   0.01431   0.00772  -0.0739   0.6971   0.7615
   1.750   0.5134   0.01436   0.00778  -0.0739   0.6933   0.7675
   2.000   0.5415   0.01451   0.00795  -0.0742   0.6886   0.7752
   2.250   0.5664   0.01463   0.00818  -0.0737   0.6834   0.7809
   2.500   0.5946   0.01469   0.00825  -0.0738   0.6789   0.7889
   2.750   0.6229   0.01476   0.00832  -0.0738   0.6751   0.7956
   3.000   0.6470   0.01494   0.00864  -0.0733   0.6689   0.8032
   3.250   0.6741   0.01503   0.00878  -0.0732   0.6642   0.8109
   3.500   0.7017   0.01510   0.00888  -0.0730   0.6604   0.8185
   3.750   0.7268   0.01528   0.00917  -0.0727   0.6552   0.8270
   4.000   0.7512   0.01537   0.00936  -0.0720   0.6492   0.8356
   4.250   0.7797   0.01526   0.00922  -0.0717   0.6433   0.8442
   4.500   0.8020   0.01526   0.00937  -0.0706   0.6339   0.8542
   4.750   0.8277   0.01502   0.00911  -0.0696   0.6249   0.8629
   5.000   0.8516   0.01484   0.00899  -0.0686   0.6137   0.8734
   5.250   0.8726   0.01471   0.00896  -0.0669   0.6032   0.8838
   5.500   0.8946   0.01446   0.00872  -0.0652   0.5910   0.8949
   5.750   0.9160   0.01421   0.00847  -0.0635   0.5779   0.9076
   6.000   0.9334   0.01405   0.00843  -0.0612   0.5647   0.9222
   6.250   0.9511   0.01389   0.00837  -0.0590   0.5514   0.9389
   6.500   0.9722   0.01373   0.00828  -0.0575   0.5359   0.9590
   6.750   1.0052   0.01362   0.00821  -0.0586   0.5141   0.9812
   7.000   1.0325   0.01370   0.00832  -0.0591   0.4840   1.0000
   7.250   1.0534   0.01398   0.00851  -0.0585   0.4358   1.0000
   7.500   1.0593   0.01503   0.00899  -0.0557   0.3366   1.0000
   7.750   1.0534   0.01686   0.01018  -0.0516   0.2408   1.0000
   8.000   1.0449   0.01868   0.01151  -0.0471   0.1703   1.0000
   8.250   1.0395   0.02055   0.01300  -0.0435   0.1212   1.0000
   8.500   1.0387   0.02230   0.01454  -0.0407   0.0958   1.0000
   8.750   1.0419   0.02391   0.01606  -0.0385   0.0821   1.0000
   9.000   1.0461   0.02553   0.01764  -0.0365   0.0738   1.0000
   9.250   1.0515   0.02714   0.01921  -0.0349   0.0675   1.0000
   9.500   1.0593   0.02867   0.02078  -0.0334   0.0625   1.0000
   9.750   1.0680   0.03017   0.02228  -0.0322   0.0584   1.0000
  10.000   1.0741   0.03200   0.02407  -0.0307   0.0553   1.0000
  10.250   1.0867   0.03332   0.02548  -0.0298   0.0523   1.0000
  10.500   1.0982   0.03476   0.02690  -0.0288   0.0495   1.0000
  10.750   1.1114   0.03637   0.02845  -0.0277   0.0468   1.0000
  11.000   1.1271   0.03764   0.02983  -0.0270   0.0449   1.0000
  11.250   1.1439   0.03894   0.03118  -0.0262   0.0430   1.0000
  11.500   1.1625   0.04024   0.03247  -0.0256   0.0414   1.0000
  11.750   1.1971   0.04169   0.03384  -0.0256   0.0396   1.0000
  12.000   1.2111   0.04323   0.03558  -0.0248   0.0386   1.0000
  12.250   1.2268   0.04488   0.03741  -0.0241   0.0375   1.0000
  12.500   1.2415   0.04659   0.03924  -0.0235   0.0362   1.0000
  12.750   1.2588   0.04841   0.04119  -0.0230   0.0355   1.0000
  13.000   1.2737   0.05044   0.04335  -0.0225   0.0347   1.0000
  13.250   1.2900   0.05268   0.04569  -0.0221   0.0342   1.0000
  13.500   1.3094   0.05557   0.04871  -0.0220   0.0336   1.0000
  13.750   1.3210   0.05940   0.05278  -0.0216   0.0333   1.0000
  14.000   1.3199   0.06324   0.05687  -0.0208   0.0332   1.0000
  14.250   1.3122   0.06685   0.06074  -0.0199   0.0332   1.0000
  14.500   1.3009   0.07075   0.06490  -0.0193   0.0331   1.0000
  14.750   1.2880   0.07498   0.06938  -0.0190   0.0331   1.0000
  15.000   1.2725   0.07956   0.07421  -0.0192   0.0331   1.0000
  15.250   1.2553   0.08455   0.07943  -0.0198   0.0331   1.0000
  15.500   1.2397   0.08999   0.08509  -0.0209   0.0332   1.0000
<< Back to NACA 64(2)-415 (naca642415-il)

Polar data table (+)

Polar graphs


<< Back to NACA 64(2)-415 (naca642415-il)