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NACA 65(2)-415 a=0.5 (naca652415a05-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 65(2)-415 a=0.5 (naca652415a05-il)
Reynolds number: 200,000
Max Cl/Cd: 74.74 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca652415a05-il-200000.txt
Download as CSV file: xf-naca652415a05-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(2)-415 a=0.5                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.2422   0.09909   0.09567  -0.0631   0.8880   0.0658
 -11.250  -0.2729   0.09215   0.08876  -0.0700   0.8852   0.0683
 -11.000  -0.3033   0.08358   0.08020  -0.0777   0.8814   0.0686
 -10.750  -0.2755   0.08199   0.07859  -0.0722   0.8751   0.0703
 -10.500  -0.2578   0.08123   0.07777  -0.0694   0.8698   0.0725
 -10.250  -0.2546   0.07776   0.07431  -0.0705   0.8644   0.0757
 -10.000  -0.2663   0.07204   0.06859  -0.0737   0.8600   0.0780
  -9.750  -0.3002   0.06301   0.05955  -0.0808   0.8566   0.0793
  -9.500  -0.4164   0.06289   0.05910  -0.0906   0.8653   0.0717
  -9.250  -0.4206   0.06072   0.05688  -0.0891   0.8583   0.0731
  -9.000  -0.4277   0.05824   0.05427  -0.0877   0.8523   0.0746
  -8.750  -0.4342   0.05560   0.05147  -0.0867   0.8453   0.0771
  -8.500  -0.4643   0.05757   0.05257  -0.0814   0.8385   0.0817
  -8.250  -0.4448   0.04971   0.04509  -0.0836   0.8342   0.0851
  -8.000  -0.4309   0.04778   0.04311  -0.0829   0.8289   0.0888
  -7.750  -0.4370   0.04565   0.04043  -0.0803   0.8240   0.0975
  -7.500  -0.4315   0.03513   0.02871  -0.0762   0.8200   0.0552
  -7.250  -0.4150   0.03187   0.02510  -0.0751   0.8151   0.0527
  -7.000  -0.3957   0.02978   0.02267  -0.0739   0.8112   0.0529
  -6.750  -0.3744   0.02784   0.02040  -0.0728   0.8080   0.0530
  -6.500  -0.3509   0.02609   0.01836  -0.0721   0.8047   0.0529
  -6.250  -0.3257   0.02472   0.01679  -0.0719   0.8001   0.0535
  -6.000  -0.3005   0.02377   0.01564  -0.0714   0.7962   0.0553
  -5.750  -0.2750   0.02294   0.01461  -0.0708   0.7930   0.0566
  -5.500  -0.2491   0.02183   0.01336  -0.0703   0.7905   0.0576
  -5.250  -0.2234   0.02058   0.01217  -0.0704   0.7866   0.0595
  -5.000  -0.1988   0.01996   0.01159  -0.0701   0.7828   0.0625
  -4.750  -0.1743   0.01943   0.01103  -0.0697   0.7796   0.0658
  -4.500  -0.1500   0.01892   0.01043  -0.0690   0.7769   0.0684
  -4.250  -0.1290   0.01810   0.00964  -0.0679   0.7746   0.0723
  -4.000  -0.1061   0.01779   0.00937  -0.0676   0.7703   0.0785
  -3.750  -0.0841   0.01734   0.00895  -0.0669   0.7667   0.0876
  -3.500  -0.0618   0.01683   0.00850  -0.0662   0.7637   0.1086
  -3.250  -0.0593   0.01449   0.00796  -0.0630   0.7610   0.4883
  -3.000  -0.0406   0.01425   0.00819  -0.0607   0.7590   0.6378
  -2.750  -0.0176   0.01450   0.00851  -0.0597   0.7554   0.6813
  -2.500   0.0060   0.01475   0.00880  -0.0588   0.7516   0.7115
  -2.250   0.0307   0.01495   0.00898  -0.0580   0.7487   0.7354
  -2.000   0.0536   0.01524   0.00930  -0.0564   0.7464   0.7660
  -1.750   0.0739   0.01569   0.00980  -0.0535   0.7444   0.7997
  -1.500   0.0966   0.01600   0.01012  -0.0514   0.7427   0.8190
  -1.250   0.1175   0.01640   0.01055  -0.0504   0.7383   0.8308
  -1.000   0.1413   0.01662   0.01075  -0.0499   0.7349   0.8381
  -0.750   0.1664   0.01673   0.01081  -0.0497   0.7324   0.8472
  -0.500   0.1925   0.01679   0.01083  -0.0493   0.7302   0.8542
  -0.250   0.2190   0.01681   0.01079  -0.0490   0.7284   0.8629
   0.000   0.2461   0.01684   0.01077  -0.0487   0.7268   0.8702
   0.250   0.2615   0.01749   0.01149  -0.0475   0.7216   0.8814
   0.500   0.2838   0.01779   0.01181  -0.0468   0.7182   0.8890
   0.750   0.3083   0.01788   0.01187  -0.0463   0.7157   0.8990
   1.000   0.3362   0.01790   0.01188  -0.0461   0.7139   0.9072
   1.250   0.3640   0.01795   0.01190  -0.0461   0.7122   0.9162
   1.500   0.3939   0.01801   0.01194  -0.0465   0.7109   0.9250
   1.750   0.4070   0.01911   0.01317  -0.0456   0.7035   0.9377
   2.000   0.4390   0.01934   0.01342  -0.0469   0.7009   0.9465
   2.250   0.4782   0.01939   0.01346  -0.0493   0.6991   0.9530
   2.500   0.5184   0.01936   0.01343  -0.0517   0.6976   0.9594
   2.750   0.5632   0.01936   0.01344  -0.0552   0.6963   0.9634
   3.000   0.6056   0.01939   0.01348  -0.0582   0.6949   0.9686
   3.250   0.6374   0.02074   0.01498  -0.0618   0.6869   0.9768
   3.500   0.6790   0.02071   0.01500  -0.0648   0.6844   0.9827
   3.750   0.7252   0.02049   0.01481  -0.0684   0.6827   0.9864
   4.000   0.7705   0.02020   0.01456  -0.0717   0.6810   0.9907
   4.250   0.8085   0.02074   0.01522  -0.0751   0.6757   0.9978
   4.500   0.8251   0.02107   0.01561  -0.0741   0.6699   1.0000
   4.750   0.8488   0.02057   0.01514  -0.0730   0.6670   1.0000
   5.000   0.8792   0.01984   0.01440  -0.0727   0.6645   1.0000
   5.250   0.8621   0.02087   0.01551  -0.0661   0.6550   1.0000
   5.500   0.8958   0.02006   0.01473  -0.0663   0.6516   1.0000
   5.750   0.9245   0.01912   0.01382  -0.0654   0.6440   1.0000
   6.000   0.9673   0.01660   0.01120  -0.0655   0.6268   1.0000
   6.250   0.9949   0.01562   0.01019  -0.0645   0.6140   1.0000
   6.500   1.0206   0.01504   0.00959  -0.0635   0.6025   1.0000
   6.750   1.0382   0.01480   0.00943  -0.0615   0.5883   1.0000
   7.000   1.0576   0.01454   0.00921  -0.0598   0.5713   1.0000
   7.250   1.0712   0.01452   0.00930  -0.0572   0.5477   1.0000
   7.500   1.0837   0.01450   0.00923  -0.0544   0.5094   1.0000
   7.750   1.0818   0.01498   0.00926  -0.0492   0.4273   1.0000
   8.000   1.0600   0.01632   0.01012  -0.0415   0.3586   1.0000
   8.250   1.0369   0.01828   0.01166  -0.0350   0.2948   1.0000
   8.500   1.0142   0.02077   0.01370  -0.0296   0.2274   1.0000
   8.750   0.9941   0.02352   0.01599  -0.0252   0.1570   1.0000
   9.000   0.9777   0.02634   0.01834  -0.0215   0.0998   1.0000
   9.250   0.9715   0.02866   0.02044  -0.0189   0.0752   1.0000
   9.500   0.9727   0.03054   0.02227  -0.0170   0.0647   1.0000
   9.750   0.9745   0.03242   0.02415  -0.0152   0.0587   1.0000
  10.000   0.9811   0.03400   0.02576  -0.0138   0.0539   1.0000
  10.250   0.9824   0.03601   0.02772  -0.0121   0.0507   1.0000
  10.500   0.9920   0.03742   0.02920  -0.0109   0.0483   1.0000
  10.750   1.0027   0.03878   0.03060  -0.0098   0.0461   1.0000
  11.000   1.0136   0.04016   0.03197  -0.0087   0.0438   1.0000
  11.250   1.0292   0.04137   0.03308  -0.0074   0.0417   1.0000
  11.500   1.0453   0.04246   0.03428  -0.0066   0.0402   1.0000
  11.750   1.0655   0.04340   0.03529  -0.0059   0.0390   1.0000
  12.000   1.0875   0.04439   0.03633  -0.0052   0.0377   1.0000
  12.250   1.1118   0.04540   0.03740  -0.0046   0.0367   1.0000
  12.500   1.1387   0.04652   0.03855  -0.0043   0.0356   1.0000
  12.750   1.1908   0.04831   0.04036  -0.0054   0.0342   1.0000
  13.000   1.1957   0.05011   0.04242  -0.0041   0.0337   1.0000
  13.250   1.2088   0.05229   0.04485  -0.0033   0.0333   1.0000
  13.500   1.2193   0.05477   0.04759  -0.0024   0.0330   1.0000
  13.750   1.2264   0.05766   0.05074  -0.0015   0.0329   1.0000
  14.000   1.2290   0.06085   0.05421  -0.0005   0.0330   1.0000
  14.250   1.2279   0.06438   0.05800   0.0005   0.0331   1.0000
  14.500   1.2238   0.06820   0.06207   0.0013   0.0333   1.0000
  14.750   1.2157   0.07244   0.06655   0.0020   0.0335   1.0000
  15.000   1.2075   0.07704   0.07137   0.0024   0.0338   1.0000
  15.250   1.2126   0.08230   0.07680   0.0023   0.0344   1.0000
  15.500   1.1958   0.08556   0.08027   0.0026   0.0346   1.0000
  15.750   1.0199   0.08817   0.08363   0.0053   0.0349   1.0000
  16.000   0.9385   0.09805   0.09410   0.0007   0.0361   1.0000
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