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NACA 2415 (naca2415-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 2415 (naca2415-il)
Reynolds number: 50,000
Max Cl/Cd: 31.41 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca2415-il-50000-n5.txt
Download as CSV file: xf-naca2415-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2415                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.5299   0.10111   0.09265  -0.0426   1.0000   0.0950
 -11.500  -0.5757   0.08737   0.07895  -0.0507   1.0000   0.0956
 -11.250  -0.6504   0.07155   0.06303  -0.0613   1.0000   0.0950
 -11.000  -0.7021   0.06391   0.05524  -0.0638   1.0000   0.0945
 -10.750  -0.7402   0.05964   0.05082  -0.0612   1.0000   0.0947
 -10.500  -0.7675   0.05593   0.04687  -0.0581   1.0000   0.0954
 -10.250  -0.7877   0.05253   0.04315  -0.0548   1.0000   0.0965
 -10.000  -0.7939   0.04990   0.04030  -0.0519   1.0000   0.0980
  -9.750  -0.7861   0.04835   0.03875  -0.0499   1.0000   0.0997
  -9.500  -0.7809   0.04668   0.03698  -0.0475   1.0000   0.1020
  -9.250  -0.7778   0.04478   0.03489  -0.0450   1.0000   0.1048
  -9.000  -0.7757   0.04260   0.03235  -0.0423   1.0000   0.1080
  -8.750  -0.7662   0.04109   0.03076  -0.0402   1.0000   0.1110
  -8.500  -0.7544   0.03992   0.02959  -0.0382   1.0000   0.1144
  -8.250  -0.7442   0.03848   0.02794  -0.0360   1.0000   0.1189
  -8.000  -0.7328   0.03703   0.02630  -0.0340   1.0000   0.1236
  -7.750  -0.7189   0.03610   0.02541  -0.0322   1.0000   0.1282
  -7.500  -0.7058   0.03490   0.02396  -0.0303   1.0000   0.1347
  -7.250  -0.6911   0.03398   0.02309  -0.0286   1.0000   0.1405
  -7.000  -0.6762   0.03305   0.02203  -0.0269   1.0000   0.1480
  -6.750  -0.6607   0.03222   0.02122  -0.0253   1.0000   0.1555
  -6.500  -0.6446   0.03141   0.02026  -0.0238   1.0000   0.1648
  -6.250  -0.6283   0.03076   0.01970  -0.0223   1.0000   0.1736
  -6.000  -0.6112   0.03009   0.01894  -0.0209   1.0000   0.1842
  -5.750  -0.5939   0.02954   0.01837  -0.0197   1.0000   0.1958
  -5.500  -0.5762   0.02904   0.01794  -0.0184   1.0000   0.2074
  -5.250  -0.5543   0.02857   0.01745  -0.0180   0.9986   0.2215
  -5.000  -0.5169   0.02811   0.01700  -0.0205   0.9915   0.2408
  -4.750  -0.4798   0.02768   0.01655  -0.0229   0.9838   0.2620
  -4.500  -0.4438   0.02727   0.01610  -0.0250   0.9757   0.2849
  -4.250  -0.4057   0.02689   0.01583  -0.0275   0.9683   0.3084
  -4.000  -0.3718   0.02652   0.01550  -0.0291   0.9590   0.3338
  -3.750  -0.3362   0.02617   0.01522  -0.0310   0.9504   0.3615
  -3.500  -0.3002   0.02585   0.01498  -0.0328   0.9417   0.3918
  -3.250  -0.2688   0.02554   0.01481  -0.0337   0.9316   0.4225
  -3.000  -0.2311   0.02525   0.01466  -0.0357   0.9237   0.4594
  -2.750  -0.2028   0.02501   0.01457  -0.0357   0.9124   0.4958
  -2.500  -0.1671   0.02478   0.01450  -0.0370   0.9040   0.5395
  -2.250  -0.1375   0.02458   0.01446  -0.0370   0.8930   0.5835
  -2.000  -0.1069   0.02442   0.01446  -0.0370   0.8829   0.6295
  -1.750  -0.0727   0.02425   0.01444  -0.0374   0.8739   0.6785
  -1.500  -0.0446   0.02419   0.01453  -0.0365   0.8627   0.7234
  -1.250  -0.0066   0.02409   0.01450  -0.0371   0.8548   0.7705
  -1.000   0.0242   0.02415   0.01462  -0.0366   0.8427   0.8119
  -0.750   0.0725   0.02408   0.01452  -0.0392   0.8359   0.8517
  -0.500   0.1115   0.02419   0.01458  -0.0407   0.8233   0.8867
  -0.250   0.1646   0.02415   0.01446  -0.0448   0.8143   0.9167
   0.000   0.2198   0.02409   0.01433  -0.0495   0.8037   0.9421
   0.250   0.2784   0.02399   0.01415  -0.0552   0.7925   0.9646
   0.500   0.3419   0.02369   0.01375  -0.0618   0.7827   0.9844
   0.750   0.3909   0.02355   0.01355  -0.0662   0.7686   1.0000
   1.000   0.4093   0.02349   0.01342  -0.0648   0.7545   1.0000
   1.250   0.4315   0.02340   0.01323  -0.0638   0.7420   1.0000
   1.500   0.4525   0.02338   0.01314  -0.0626   0.7288   1.0000
   1.750   0.4701   0.02351   0.01321  -0.0609   0.7145   1.0000
   2.000   0.4906   0.02361   0.01324  -0.0596   0.7016   1.0000
   2.250   0.5169   0.02356   0.01310  -0.0590   0.6906   1.0000
   2.500   0.5345   0.02381   0.01332  -0.0572   0.6763   1.0000
   2.750   0.5544   0.02403   0.01350  -0.0558   0.6632   1.0000
   3.000   0.5785   0.02414   0.01354  -0.0548   0.6513   1.0000
   3.250   0.6012   0.02429   0.01365  -0.0536   0.6383   1.0000
   3.500   0.6204   0.02456   0.01390  -0.0520   0.6239   1.0000
   3.750   0.6418   0.02477   0.01407  -0.0505   0.6100   1.0000
   4.000   0.6656   0.02492   0.01417  -0.0495   0.5968   1.0000
   4.250   0.6891   0.02510   0.01432  -0.0483   0.5835   1.0000
   4.500   0.7083   0.02548   0.01471  -0.0468   0.5694   1.0000
   4.750   0.7298   0.02581   0.01505  -0.0455   0.5562   1.0000
   5.000   0.7545   0.02604   0.01524  -0.0446   0.5439   1.0000
   5.250   0.7757   0.02641   0.01562  -0.0433   0.5304   1.0000
   5.500   0.7952   0.02685   0.01610  -0.0418   0.5165   1.0000
   5.750   0.8167   0.02723   0.01649  -0.0405   0.5030   1.0000
   6.000   0.8399   0.02752   0.01676  -0.0394   0.4895   1.0000
   6.250   0.8610   0.02787   0.01712  -0.0381   0.4749   1.0000
   6.500   0.8788   0.02833   0.01762  -0.0363   0.4592   1.0000
   6.750   0.8967   0.02878   0.01809  -0.0346   0.4432   1.0000
   7.000   0.9144   0.02923   0.01856  -0.0328   0.4271   1.0000
   7.250   0.9318   0.02970   0.01906  -0.0310   0.4110   1.0000
   7.500   0.9487   0.03020   0.01958  -0.0292   0.3949   1.0000
   7.750   0.9650   0.03074   0.02013  -0.0273   0.3788   1.0000
   8.000   0.9803   0.03131   0.02072  -0.0253   0.3625   1.0000
   8.250   0.9946   0.03194   0.02135  -0.0233   0.3462   1.0000
   8.500   1.0074   0.03262   0.02203  -0.0211   0.3298   1.0000
   8.750   1.0188   0.03338   0.02278  -0.0188   0.3133   1.0000
   9.000   1.0284   0.03421   0.02361  -0.0164   0.2970   1.0000
   9.250   1.0353   0.03510   0.02447  -0.0137   0.2814   1.0000
   9.500   1.0413   0.03610   0.02545  -0.0110   0.2662   1.0000
   9.750   1.0461   0.03729   0.02665  -0.0084   0.2512   1.0000
  10.000   1.0507   0.03862   0.02797  -0.0062   0.2368   1.0000
  10.250   1.0552   0.04007   0.02944  -0.0041   0.2232   1.0000
  10.500   1.0598   0.04164   0.03099  -0.0022   0.2107   1.0000
  10.750   1.0644   0.04326   0.03254  -0.0005   0.1992   1.0000
  11.000   1.0681   0.04506   0.03437   0.0011   0.1881   1.0000
  11.250   1.0709   0.04709   0.03648   0.0024   0.1777   1.0000
  11.500   1.0752   0.04899   0.03833   0.0036   0.1689   1.0000
  11.750   1.0773   0.05123   0.04068   0.0046   0.1601   1.0000
  12.000   1.0805   0.05344   0.04292   0.0055   0.1526   1.0000
  12.250   1.0833   0.05577   0.04531   0.0063   0.1456   1.0000
  12.500   1.0870   0.05808   0.04765   0.0070   0.1396   1.0000
  12.750   1.0875   0.06085   0.05056   0.0074   0.1337   1.0000
  13.000   1.0965   0.06258   0.05219   0.0081   0.1287   1.0000
  13.250   1.0917   0.06625   0.05614   0.0081   0.1242   1.0000
  13.500   1.0912   0.06933   0.05935   0.0081   0.1200   1.0000
  13.750   1.1022   0.07095   0.06087   0.0088   0.1160   1.0000
  14.000   1.0923   0.07551   0.06571   0.0081   0.1131   1.0000
  14.250   1.0800   0.08051   0.07097   0.0069   0.1105   1.0000
  14.500   1.0696   0.08537   0.07602   0.0057   0.1080   1.0000
  14.750   1.0689   0.08881   0.07951   0.0051   0.1054   1.0000
  15.000   1.0725   0.09169   0.08241   0.0048   0.1029   1.0000
  15.250   1.0303   0.10235   0.09342  -0.0003   0.1020   1.0000
  15.500   0.9167   0.13018   0.12167  -0.0163   0.1015   1.0000
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