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NACA 2410 (naca2410-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 2410 (naca2410-il)
Reynolds number: 50,000
Max Cl/Cd: 36.08 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca2410-il-50000-n5.txt
Download as CSV file: xf-naca2410-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2410                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5281   0.09780   0.09035  -0.0247   1.0000   0.0669
  -9.500  -0.5327   0.09260   0.08522  -0.0275   1.0000   0.0666
  -9.250  -0.5395   0.08706   0.07975  -0.0308   1.0000   0.0665
  -9.000  -0.5500   0.08089   0.07366  -0.0352   1.0000   0.0664
  -8.750  -0.5646   0.07404   0.06684  -0.0402   1.0000   0.0662
  -8.500  -0.5783   0.06772   0.06048  -0.0435   1.0000   0.0663
  -8.250  -0.5897   0.06196   0.05453  -0.0454   1.0000   0.0669
  -8.000  -0.5969   0.05664   0.04892  -0.0463   1.0000   0.0679
  -7.750  -0.5999   0.05161   0.04346  -0.0462   1.0000   0.0692
  -7.500  -0.5976   0.04702   0.03831  -0.0456   1.0000   0.0703
  -7.250  -0.5880   0.04363   0.03455  -0.0446   1.0000   0.0719
  -7.000  -0.5725   0.04197   0.03285  -0.0436   1.0000   0.0753
  -6.750  -0.5581   0.03956   0.03012  -0.0425   1.0000   0.0788
  -6.500  -0.5426   0.03671   0.02675  -0.0414   1.0000   0.0814
  -6.250  -0.5247   0.03417   0.02364  -0.0403   1.0000   0.0844
  -6.000  -0.5058   0.03280   0.02230  -0.0393   1.0000   0.0887
  -5.750  -0.4858   0.03123   0.02044  -0.0383   1.0000   0.0935
  -5.500  -0.4641   0.02950   0.01829  -0.0372   1.0000   0.0973
  -5.250  -0.4429   0.02812   0.01687  -0.0363   1.0000   0.1012
  -5.000  -0.4214   0.02707   0.01570  -0.0353   1.0000   0.1083
  -4.750  -0.3997   0.02603   0.01459  -0.0343   1.0000   0.1164
  -4.500  -0.3773   0.02506   0.01344  -0.0333   1.0000   0.1254
  -4.250  -0.3551   0.02414   0.01255  -0.0324   1.0000   0.1358
  -4.000  -0.3325   0.02337   0.01176  -0.0316   1.0000   0.1532
  -3.750  -0.3097   0.02263   0.01109  -0.0310   1.0000   0.1757
  -3.500  -0.2874   0.02196   0.01051  -0.0304   1.0000   0.2070
  -3.250  -0.2650   0.02136   0.01007  -0.0299   1.0000   0.2494
  -3.000  -0.2428   0.02076   0.00971  -0.0293   1.0000   0.3017
  -2.750  -0.2207   0.02017   0.00940  -0.0287   1.0000   0.3646
  -2.500  -0.1990   0.01960   0.00921  -0.0279   1.0000   0.4437
  -2.250  -0.1790   0.01905   0.00917  -0.0264   1.0000   0.5487
  -2.000  -0.1620   0.01859   0.00925  -0.0236   1.0000   0.6772
  -1.750  -0.1412   0.01832   0.00938  -0.0209   1.0000   0.8391
  -1.500  -0.0892   0.01833   0.00923  -0.0260   0.9953   1.0000
  -1.250  -0.0452   0.01857   0.00913  -0.0299   0.9850   1.0000
  -1.000  -0.0023   0.01879   0.00909  -0.0336   0.9741   1.0000
  -0.750   0.0392   0.01899   0.00906  -0.0369   0.9624   1.0000
  -0.500   0.0792   0.01916   0.00906  -0.0398   0.9499   1.0000
  -0.250   0.1181   0.01932   0.00908  -0.0424   0.9370   1.0000
   0.000   0.1571   0.01946   0.00910  -0.0449   0.9241   1.0000
   0.250   0.1968   0.01958   0.00914  -0.0474   0.9115   1.0000
   0.500   0.2368   0.01967   0.00916  -0.0498   0.8991   1.0000
   0.750   0.2749   0.01973   0.00916  -0.0517   0.8862   1.0000
   1.000   0.3099   0.01978   0.00919  -0.0530   0.8720   1.0000
   1.250   0.3432   0.01983   0.00923  -0.0538   0.8572   1.0000
   1.500   0.3757   0.01987   0.00926  -0.0545   0.8421   1.0000
   1.750   0.4065   0.01993   0.00933  -0.0547   0.8263   1.0000
   2.000   0.4360   0.02000   0.00942  -0.0546   0.8097   1.0000
   2.250   0.4649   0.02009   0.00953  -0.0544   0.7929   1.0000
   2.500   0.4934   0.02018   0.00965  -0.0541   0.7757   1.0000
   2.750   0.5219   0.02027   0.00978  -0.0538   0.7584   1.0000
   3.000   0.5502   0.02038   0.00993  -0.0533   0.7408   1.0000
   3.250   0.5783   0.02048   0.01007  -0.0527   0.7230   1.0000
   3.500   0.6063   0.02059   0.01021  -0.0521   0.7050   1.0000
   3.750   0.6315   0.02081   0.01050  -0.0512   0.6846   1.0000
   4.000   0.6573   0.02100   0.01074  -0.0503   0.6642   1.0000
   4.250   0.6840   0.02115   0.01093  -0.0493   0.6440   1.0000
   4.500   0.7078   0.02143   0.01129  -0.0481   0.6208   1.0000
   4.750   0.7332   0.02162   0.01150  -0.0470   0.5979   1.0000
   5.000   0.7560   0.02191   0.01184  -0.0455   0.5712   1.0000
   5.250   0.7784   0.02218   0.01216  -0.0440   0.5423   1.0000
   5.500   0.7999   0.02248   0.01247  -0.0423   0.5106   1.0000
   5.750   0.8205   0.02283   0.01279  -0.0405   0.4764   1.0000
   6.000   0.8393   0.02326   0.01322  -0.0386   0.4371   1.0000
   6.250   0.8562   0.02378   0.01366  -0.0364   0.3899   1.0000
   6.500   0.8710   0.02449   0.01416  -0.0342   0.3336   1.0000
   6.750   0.8846   0.02549   0.01487  -0.0320   0.2729   1.0000
   7.000   0.8971   0.02683   0.01586  -0.0301   0.2178   1.0000
   7.250   0.9094   0.02840   0.01715  -0.0283   0.1759   1.0000
   7.500   0.9226   0.03001   0.01861  -0.0266   0.1485   1.0000
   7.750   0.9365   0.03162   0.02013  -0.0249   0.1303   1.0000
   8.000   0.9511   0.03319   0.02166  -0.0234   0.1167   1.0000
   8.250   0.9664   0.03470   0.02319  -0.0219   0.1062   1.0000
   8.500   0.9851   0.03627   0.02490  -0.0206   0.0990   1.0000
   8.750   1.0044   0.03789   0.02660  -0.0195   0.0935   1.0000
   9.000   1.0257   0.03967   0.02851  -0.0186   0.0884   1.0000
   9.250   1.0445   0.04141   0.03046  -0.0176   0.0827   1.0000
   9.500   1.0645   0.04332   0.03231  -0.0169   0.0785   1.0000
   9.750   1.0844   0.04573   0.03509  -0.0159   0.0756   1.0000
  10.250   1.1105   0.05035   0.04033  -0.0133   0.0687   1.0000
  10.500   1.1254   0.05280   0.04278  -0.0125   0.0659   1.0000
  10.750   1.1283   0.05603   0.04647  -0.0105   0.0644   1.0000
  11.000   1.1240   0.05936   0.05026  -0.0082   0.0629   1.0000
  11.250   1.1143   0.06264   0.05390  -0.0058   0.0615   1.0000
  11.500   1.1019   0.06617   0.05773  -0.0039   0.0603   1.0000
  11.750   1.0869   0.07008   0.06191  -0.0029   0.0594   1.0000
  12.000   1.0684   0.07464   0.06672  -0.0028   0.0589   1.0000
  12.250   1.0444   0.08032   0.07265  -0.0043   0.0589   1.0000
  12.500   1.0122   0.08797   0.08054  -0.0079   0.0596   1.0000
  12.750   0.9747   0.09801   0.09076  -0.0141   0.0610   1.0000
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