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NACA 2415 (n2415-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 2415 (n2415-il)
Reynolds number: 50,000
Max Cl/Cd: 31.59 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n2415-il-50000-n5.txt
Download as CSV file: xf-n2415-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  -0.5222   0.10284   0.09441  -0.0413   1.0000   0.0963
 -11.500  -0.5432   0.09462   0.08624  -0.0455   1.0000   0.0978
 -11.250  -0.6144   0.07692   0.06854  -0.0570   1.0000   0.0978
 -11.000  -0.6957   0.06443   0.05585  -0.0635   1.0000   0.0964
 -10.750  -0.7361   0.05987   0.05115  -0.0613   1.0000   0.0965
 -10.500  -0.7598   0.05647   0.04758  -0.0584   1.0000   0.0974
 -10.250  -0.7773   0.05333   0.04421  -0.0553   1.0000   0.0988
 -10.000  -0.7913   0.05025   0.04081  -0.0520   1.0000   0.1007
  -9.750  -0.7976   0.04761   0.03785  -0.0490   1.0000   0.1029
  -9.500  -0.7865   0.04648   0.03678  -0.0470   1.0000   0.1055
  -9.250  -0.7809   0.04485   0.03504  -0.0446   1.0000   0.1086
  -9.000  -0.7778   0.04278   0.03266  -0.0420   1.0000   0.1120
  -8.750  -0.7705   0.04106   0.03075  -0.0397   1.0000   0.1155
  -8.500  -0.7580   0.04002   0.02972  -0.0377   1.0000   0.1192
  -8.250  -0.7479   0.03856   0.02806  -0.0356   1.0000   0.1237
  -8.000  -0.7363   0.03717   0.02649  -0.0336   1.0000   0.1285
  -7.750  -0.7223   0.03625   0.02560  -0.0318   1.0000   0.1333
  -7.500  -0.7091   0.03499   0.02405  -0.0299   1.0000   0.1395
  -7.250  -0.6939   0.03413   0.02326  -0.0282   1.0000   0.1451
  -7.000  -0.6787   0.03318   0.02219  -0.0266   1.0000   0.1521
  -6.750  -0.6628   0.03233   0.02132  -0.0250   1.0000   0.1591
  -6.500  -0.6464   0.03156   0.02044  -0.0235   1.0000   0.1675
  -6.250  -0.6296   0.03084   0.01974  -0.0221   1.0000   0.1757
  -6.000  -0.6122   0.03015   0.01890  -0.0207   1.0000   0.1864
  -5.750  -0.5948   0.02960   0.01844  -0.0194   1.0000   0.1959
  -5.500  -0.5767   0.02905   0.01788  -0.0183   1.0000   0.2075
  -5.250  -0.5553   0.02855   0.01733  -0.0177   0.9990   0.2213
  -5.000  -0.5177   0.02807   0.01688  -0.0202   0.9919   0.2397
  -4.750  -0.4807   0.02763   0.01648  -0.0226   0.9841   0.2599
  -4.500  -0.4446   0.02723   0.01611  -0.0248   0.9758   0.2822
  -4.250  -0.4057   0.02687   0.01573  -0.0274   0.9682   0.3082
  -4.000  -0.3717   0.02649   0.01547  -0.0290   0.9587   0.3330
  -3.750  -0.3359   0.02615   0.01516  -0.0309   0.9498   0.3621
  -3.500  -0.2996   0.02581   0.01496  -0.0328   0.9411   0.3927
  -3.250  -0.2681   0.02551   0.01476  -0.0337   0.9307   0.4249
  -3.000  -0.2298   0.02521   0.01462  -0.0357   0.9229   0.4627
  -2.750  -0.2018   0.02497   0.01452  -0.0358   0.9113   0.4994
  -2.500  -0.1667   0.02472   0.01444  -0.0369   0.9028   0.5423
  -2.250  -0.1367   0.02452   0.01441  -0.0369   0.8920   0.5861
  -2.000  -0.1059   0.02436   0.01440  -0.0370   0.8820   0.6322
  -1.750  -0.0721   0.02421   0.01442  -0.0372   0.8729   0.6794
  -1.500  -0.0440   0.02416   0.01448  -0.0364   0.8618   0.7250
  -1.250  -0.0068   0.02408   0.01448  -0.0369   0.8536   0.7710
  -1.000   0.0248   0.02415   0.01461  -0.0366   0.8419   0.8129
  -0.750   0.0724   0.02412   0.01455  -0.0391   0.8347   0.8534
  -0.500   0.1139   0.02424   0.01464  -0.0410   0.8228   0.8888
  -0.250   0.1707   0.02414   0.01444  -0.0456   0.8157   0.9198
   0.000   0.2231   0.02420   0.01443  -0.0501   0.8033   0.9454
   0.250   0.2834   0.02403   0.01417  -0.0560   0.7938   0.9677
   0.500   0.3441   0.02380   0.01387  -0.0623   0.7821   0.9868
   0.750   0.3898   0.02364   0.01365  -0.0661   0.7687   1.0000
   1.000   0.4106   0.02353   0.01345  -0.0650   0.7556   1.0000
   1.250   0.4337   0.02340   0.01323  -0.0642   0.7431   1.0000
   1.500   0.4506   0.02350   0.01326  -0.0624   0.7284   1.0000
   1.750   0.4699   0.02358   0.01327  -0.0609   0.7148   1.0000
   2.000   0.4940   0.02355   0.01316  -0.0600   0.7029   1.0000
   2.250   0.5148   0.02365   0.01320  -0.0586   0.6896   1.0000
   2.750   0.5561   0.02398   0.01343  -0.0558   0.6633   1.0000
   3.000   0.5810   0.02405   0.01343  -0.0549   0.6513   1.0000
   3.250   0.5993   0.02435   0.01372  -0.0532   0.6373   1.0000
   3.500   0.6206   0.02458   0.01392  -0.0519   0.6244   1.0000
   3.750   0.6468   0.02467   0.01393  -0.0511   0.6128   1.0000
   4.000   0.6659   0.02500   0.01428  -0.0495   0.5988   1.0000
   4.250   0.6862   0.02533   0.01461  -0.0481   0.5853   1.0000
   4.500   0.7097   0.02555   0.01480  -0.0470   0.5726   1.0000
   4.750   0.7339   0.02576   0.01498  -0.0460   0.5597   1.0000
   5.000   0.7527   0.02617   0.01542  -0.0443   0.5452   1.0000
   5.250   0.7734   0.02653   0.01578  -0.0429   0.5313   1.0000
   5.500   0.7961   0.02682   0.01605  -0.0417   0.5177   1.0000
   5.750   0.8203   0.02704   0.01625  -0.0407   0.5041   1.0000
   6.000   0.8382   0.02751   0.01677  -0.0390   0.4888   1.0000
   6.250   0.8570   0.02795   0.01724  -0.0373   0.4736   1.0000
   6.500   0.8763   0.02837   0.01769  -0.0358   0.4584   1.0000
   6.750   0.8957   0.02877   0.01810  -0.0342   0.4431   1.0000
   7.000   0.9147   0.02918   0.01851  -0.0326   0.4274   1.0000
   7.250   0.9330   0.02961   0.01895  -0.0309   0.4115   1.0000
   7.500   0.9503   0.03008   0.01940  -0.0291   0.3953   1.0000
   7.750   0.9663   0.03059   0.01993  -0.0271   0.3789   1.0000
   8.000   0.9803   0.03120   0.02057  -0.0250   0.3622   1.0000
   8.250   0.9935   0.03185   0.02124  -0.0228   0.3455   1.0000
   8.500   1.0057   0.03257   0.02196  -0.0206   0.3289   1.0000
   8.750   1.0168   0.03335   0.02275  -0.0183   0.3125   1.0000
   9.000   1.0265   0.03422   0.02362  -0.0159   0.2964   1.0000
   9.250   1.0340   0.03516   0.02457  -0.0133   0.2812   1.0000
   9.500   1.0409   0.03621   0.02561  -0.0107   0.2664   1.0000
   9.750   1.0477   0.03736   0.02675  -0.0084   0.2524   1.0000
  10.000   1.0543   0.03860   0.02796  -0.0062   0.2390   1.0000
  10.250   1.0611   0.03989   0.02919  -0.0042   0.2266   1.0000
  10.500   1.0655   0.04144   0.03080  -0.0022   0.2142   1.0000
  10.750   1.0701   0.04312   0.03252  -0.0005   0.2028   1.0000
  11.000   1.0756   0.04476   0.03414   0.0011   0.1927   1.0000
  11.250   1.0803   0.04654   0.03594   0.0025   0.1830   1.0000
  11.500   1.0836   0.04859   0.03809   0.0038   0.1739   1.0000
  11.750   1.0908   0.05025   0.03965   0.0049   0.1661   1.0000
  12.000   1.0911   0.05278   0.04237   0.0059   0.1582   1.0000
  12.250   1.0989   0.05449   0.04397   0.0068   0.1514   1.0000
  12.500   1.0971   0.05742   0.04716   0.0075   0.1449   1.0000
  12.750   1.1035   0.05937   0.04908   0.0082   0.1390   1.0000
  13.000   1.1014   0.06248   0.05237   0.0085   0.1337   1.0000
  13.250   1.1012   0.06538   0.05539   0.0088   0.1287   1.0000
  13.500   1.1093   0.06731   0.05726   0.0093   0.1241   1.0000
  13.750   1.0975   0.07186   0.06211   0.0088   0.1203   1.0000
  14.000   1.0920   0.07565   0.06605   0.0083   0.1166   1.0000
  14.250   1.1066   0.07678   0.06707   0.0091   0.1126   1.0000
  14.500   1.0833   0.08325   0.07389   0.0071   0.1103   1.0000
  14.750   1.0563   0.09077   0.08170   0.0043   0.1083   1.0000
  15.000   1.0222   0.10009   0.09130   0.0001   0.1065   1.0000
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