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NACA 2415 (n2415-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 2415 (n2415-il)
Reynolds number: 50,000
Max Cl/Cd: 26.26 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n2415-il-50000.txt
Download as CSV file: xf-n2415-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3912   0.11156   0.10358  -0.0163   1.0000   0.3643
  -9.250  -0.3530   0.10599   0.09794  -0.0159   1.0000   0.3742
  -9.000  -0.5952   0.07639   0.06879  -0.0413   1.0000   0.2033
  -8.750  -0.6146   0.07153   0.06390  -0.0401   1.0000   0.2014
  -8.500  -0.6369   0.06677   0.05912  -0.0383   1.0000   0.2003
  -8.250  -0.6614   0.06198   0.05419  -0.0360   1.0000   0.1997
  -8.000  -0.6830   0.05732   0.04930  -0.0335   1.0000   0.1999
  -7.750  -0.7001   0.05284   0.04442  -0.0308   1.0000   0.2013
  -7.500  -0.6985   0.04978   0.04121  -0.0286   1.0000   0.2050
  -7.250  -0.6861   0.04822   0.03967  -0.0266   1.0000   0.2109
  -7.000  -0.6854   0.04513   0.03618  -0.0245   1.0000   0.2165
  -6.750  -0.6780   0.04255   0.03332  -0.0226   1.0000   0.2225
  -6.500  -0.6636   0.04113   0.03188  -0.0209   1.0000   0.2310
  -6.250  -0.6530   0.03884   0.02923  -0.0193   1.0000   0.2395
  -6.000  -0.6367   0.03761   0.02797  -0.0178   1.0000   0.2499
  -5.750  -0.6209   0.03611   0.02635  -0.0165   1.0000   0.2607
  -5.500  -0.6046   0.03465   0.02463  -0.0153   1.0000   0.2739
  -5.250  -0.5864   0.03364   0.02359  -0.0141   1.0000   0.2880
  -5.000  -0.5677   0.03270   0.02269  -0.0129   1.0000   0.3035
  -4.750  -0.5484   0.03178   0.02175  -0.0119   1.0000   0.3206
  -4.500  -0.5290   0.03097   0.02092  -0.0109   1.0000   0.3401
  -4.250  -0.5094   0.03022   0.02014  -0.0100   1.0000   0.3617
  -4.000  -0.4898   0.02954   0.01949  -0.0091   1.0000   0.3849
  -3.750  -0.4707   0.02904   0.01915  -0.0079   1.0000   0.4090
  -3.500  -0.4514   0.02858   0.01875  -0.0070   1.0000   0.4375
  -3.250  -0.4326   0.02822   0.01857  -0.0058   1.0000   0.4662
  -3.000  -0.4136   0.02793   0.01840  -0.0047   1.0000   0.4995
  -2.750  -0.3956   0.02773   0.01834  -0.0034   1.0000   0.5356
  -2.500  -0.3783   0.02761   0.01842  -0.0019   1.0000   0.5742
  -2.250  -0.3618   0.02757   0.01860   0.0000   1.0000   0.6161
  -2.000  -0.3462   0.02759   0.01885   0.0021   1.0000   0.6643
  -1.750  -0.3328   0.02766   0.01919   0.0050   1.0000   0.7176
  -1.500  -0.3223   0.02781   0.01960   0.0088   1.0000   0.7797
  -1.250  -0.2881   0.02858   0.02060   0.0096   0.9914   0.8697
  -1.000  -0.1290   0.03133   0.02303  -0.0137   0.9817   0.9823
  -0.750  -0.0564   0.03155   0.02296  -0.0264   0.9661   1.0000
  -0.500  -0.0295   0.03157   0.02278  -0.0297   0.9487   1.0000
  -0.250   0.0013   0.03191   0.02291  -0.0326   0.9328   1.0000
   0.000   0.0354   0.03239   0.02321  -0.0355   0.9176   1.0000
   0.250   0.0742   0.03295   0.02361  -0.0389   0.9035   1.0000
   0.500   0.1101   0.03348   0.02401  -0.0415   0.8888   1.0000
   0.750   0.1351   0.03404   0.02445  -0.0421   0.8736   1.0000
   1.000   0.1620   0.03465   0.02495  -0.0430   0.8587   1.0000
   1.250   0.1927   0.03527   0.02549  -0.0443   0.8448   1.0000
   1.500   0.2371   0.03576   0.02591  -0.0475   0.8323   1.0000
   1.750   0.2630   0.03637   0.02647  -0.0478   0.8178   1.0000
   2.000   0.2833   0.03711   0.02715  -0.0473   0.8031   1.0000
   2.250   0.3095   0.03780   0.02781  -0.0476   0.7893   1.0000
   2.500   0.3567   0.03805   0.02804  -0.0505   0.7775   1.0000
   2.750   0.3788   0.03875   0.02873  -0.0500   0.7630   1.0000
   3.000   0.3950   0.03968   0.02964  -0.0488   0.7482   1.0000
   3.250   0.4198   0.04041   0.03037  -0.0486   0.7344   1.0000
   3.500   0.4827   0.03981   0.02983  -0.0525   0.7240   1.0000
   3.750   0.4894   0.04106   0.03107  -0.0501   0.7082   1.0000
   4.000   0.5023   0.04219   0.03220  -0.0484   0.6930   1.0000
   4.250   0.5249   0.04297   0.03300  -0.0477   0.6788   1.0000
   4.500   0.5958   0.04128   0.03142  -0.0509   0.6690   1.0000
   4.750   0.6050   0.04258   0.03273  -0.0487   0.6528   1.0000
   5.000   0.6167   0.04379   0.03398  -0.0468   0.6370   1.0000
   5.250   0.6344   0.04469   0.03492  -0.0453   0.6218   1.0000
   5.500   0.6721   0.04436   0.03466  -0.0451   0.6082   1.0000
   5.750   0.7356   0.04215   0.03255  -0.0463   0.5963   1.0000
   6.000   0.7501   0.04308   0.03354  -0.0442   0.5796   1.0000
   6.250   0.7676   0.04383   0.03435  -0.0423   0.5632   1.0000
   6.500   0.7910   0.04414   0.03473  -0.0407   0.5468   1.0000
   6.750   0.8212   0.04391   0.03455  -0.0395   0.5303   1.0000
   7.000   0.8559   0.04330   0.03402  -0.0384   0.5134   1.0000
   7.250   0.8911   0.04262   0.03338  -0.0374   0.4955   1.0000
   7.500   0.9251   0.04200   0.03280  -0.0363   0.4767   1.0000
   7.750   0.9584   0.04143   0.03223  -0.0351   0.4570   1.0000
   8.000   0.9929   0.04079   0.03156  -0.0341   0.4365   1.0000
   8.250   1.0337   0.03979   0.03044  -0.0337   0.4149   1.0000
   8.500   1.0527   0.04024   0.03088  -0.0317   0.3943   1.0000
   8.750   1.0665   0.04101   0.03168  -0.0292   0.3742   1.0000
   9.000   1.0831   0.04167   0.03235  -0.0270   0.3541   1.0000
   9.250   1.1021   0.04222   0.03285  -0.0250   0.3341   1.0000
   9.500   1.1230   0.04277   0.03331  -0.0233   0.3146   1.0000
   9.750   1.1421   0.04359   0.03405  -0.0216   0.2964   1.0000
  10.000   1.1540   0.04495   0.03542  -0.0194   0.2804   1.0000
  10.250   1.1604   0.04674   0.03729  -0.0168   0.2664   1.0000
  10.500   1.1701   0.04850   0.03908  -0.0146   0.2534   1.0000
  10.750   1.1862   0.05002   0.04055  -0.0131   0.2404   1.0000
  11.000   1.2115   0.05133   0.04170  -0.0125   0.2272   1.0000
  11.250   1.1836   0.05499   0.04581  -0.0075   0.2227   1.0000
  11.500   0.9228   0.08297   0.07459  -0.0066   0.2505   1.0000
  11.750   0.8865   0.09334   0.08496  -0.0102   0.2456   1.0000
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