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NACA 65-410 (naca65410-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 65-410 (naca65410-il)
Reynolds number: 200,000
Max Cl/Cd: 68.73 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca65410-il-200000-n5.txt
Download as CSV file: xf-naca65410-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-410                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4400   0.08851   0.08489  -0.0429   1.0000   0.0146
  -9.250  -0.4436   0.08428   0.08071  -0.0447   1.0000   0.0146
  -9.000  -0.4500   0.07960   0.07610  -0.0469   1.0000   0.0149
  -8.750  -0.4571   0.07562   0.07218  -0.0485   1.0000   0.0144
  -8.500  -0.4727   0.07105   0.06770  -0.0508   1.0000   0.0144
  -8.250  -0.4962   0.06817   0.06487  -0.0499   1.0000   0.0141
  -8.000  -0.4969   0.06210   0.05870  -0.0555   0.9940   0.0138
  -7.750  -0.4842   0.05453   0.05085  -0.0629   0.9851   0.0148
  -7.500  -0.4693   0.04743   0.04335  -0.0677   0.9770   0.0153
  -7.250  -0.4527   0.04175   0.03728  -0.0706   0.9692   0.0153
  -7.000  -0.4298   0.03597   0.03097  -0.0734   0.9645   0.0154
  -6.750  -0.4096   0.03135   0.02574  -0.0742   0.9564   0.0158
  -6.500  -0.3832   0.02733   0.02118  -0.0759   0.9520   0.0165
  -6.250  -0.3578   0.02621   0.01995  -0.0766   0.9452   0.0177
  -6.000  -0.3282   0.02484   0.01835  -0.0778   0.9402   0.0195
  -5.750  -0.2987   0.02255   0.01562  -0.0786   0.9355   0.0206
  -5.500  -0.2712   0.02079   0.01350  -0.0786   0.9289   0.0216
  -5.250  -0.2399   0.01969   0.01209  -0.0794   0.9244   0.0229
  -5.000  -0.2139   0.01805   0.01036  -0.0795   0.9179   0.0252
  -4.750  -0.1853   0.01704   0.00923  -0.0798   0.9122   0.0265
  -4.500  -0.1568   0.01614   0.00823  -0.0801   0.9066   0.0280
  -4.250  -0.1301   0.01543   0.00744  -0.0800   0.8997   0.0301
  -3.750  -0.0756   0.01419   0.00605  -0.0800   0.8870   0.0337
  -3.500  -0.0484   0.01339   0.00518  -0.0802   0.8814   0.0365
  -3.250  -0.0220   0.01296   0.00470  -0.0802   0.8742   0.0398
  -3.000   0.0060   0.01264   0.00428  -0.0803   0.8682   0.0451
  -2.750   0.0331   0.01225   0.00386  -0.0803   0.8616   0.0523
  -2.500   0.0605   0.01187   0.00350  -0.0804   0.8553   0.0735
  -2.250   0.0837   0.01001   0.00312  -0.0812   0.8492   0.4573
  -2.000   0.1067   0.00957   0.00333  -0.0801   0.8424   0.6485
  -1.750   0.1314   0.00957   0.00346  -0.0789   0.8370   0.7159
  -1.500   0.1558   0.00963   0.00356  -0.0778   0.8301   0.7509
  -1.250   0.1815   0.00967   0.00358  -0.0770   0.8247   0.7712
  -1.000   0.2085   0.00969   0.00354  -0.0768   0.8183   0.7825
  -0.750   0.2355   0.00968   0.00349  -0.0766   0.8123   0.7888
  -0.250   0.2902   0.00970   0.00343  -0.0764   0.8007   0.8027
   0.000   0.3184   0.00972   0.00339  -0.0765   0.7955   0.8103
   0.250   0.3447   0.00974   0.00343  -0.0762   0.7892   0.8167
   0.500   0.3723   0.00977   0.00344  -0.0761   0.7835   0.8246
   0.750   0.3990   0.00979   0.00347  -0.0758   0.7782   0.8311
   1.000   0.4260   0.00984   0.00354  -0.0757   0.7719   0.8393
   1.250   0.4524   0.00986   0.00358  -0.0754   0.7667   0.8463
   1.500   0.4791   0.00992   0.00368  -0.0752   0.7604   0.8546
   1.750   0.5048   0.00996   0.00376  -0.0747   0.7546   0.8620
   2.000   0.5312   0.01001   0.00387  -0.0744   0.7491   0.8707
   2.250   0.5564   0.01006   0.00400  -0.0738   0.7425   0.8795
   2.500   0.5824   0.01010   0.00408  -0.0733   0.7367   0.8881
   2.750   0.6071   0.01012   0.00418  -0.0725   0.7251   0.8982
   3.000   0.6311   0.01009   0.00416  -0.0714   0.7089   0.9088
   3.250   0.6537   0.01005   0.00413  -0.0701   0.6848   0.9204
   3.500   0.6760   0.01003   0.00404  -0.0685   0.6500   0.9333
   3.750   0.6969   0.01014   0.00398  -0.0668   0.5871   0.9488
   4.000   0.7174   0.01068   0.00401  -0.0654   0.4686   0.9696
   4.250   0.7287   0.01229   0.00463  -0.0634   0.2790   1.0000
   4.500   0.7399   0.01397   0.00547  -0.0615   0.1196   1.0000
   4.750   0.7580   0.01507   0.00619  -0.0604   0.0550   1.0000
   5.000   0.7807   0.01572   0.00684  -0.0599   0.0434   1.0000
   5.250   0.8030   0.01639   0.00751  -0.0593   0.0366   1.0000
   5.500   0.8250   0.01707   0.00825  -0.0586   0.0326   1.0000
   5.750   0.8467   0.01775   0.00903  -0.0578   0.0302   1.0000
   6.000   0.8673   0.01853   0.00987  -0.0569   0.0281   1.0000
   6.250   0.8867   0.01943   0.01085  -0.0558   0.0264   1.0000
   6.500   0.9042   0.02062   0.01206  -0.0544   0.0251   1.0000
   6.750   0.9225   0.02201   0.01350  -0.0532   0.0238   1.0000
   7.000   0.9449   0.02282   0.01441  -0.0526   0.0227   1.0000
   7.250   0.9671   0.02389   0.01558  -0.0519   0.0215   1.0000
   7.500   0.9901   0.02518   0.01701  -0.0514   0.0207   1.0000
   7.750   1.0139   0.02660   0.01856  -0.0509   0.0199   1.0000
   8.000   1.0377   0.02815   0.02026  -0.0506   0.0192   1.0000
   8.250   1.0608   0.02981   0.02210  -0.0501   0.0186   1.0000
   8.500   1.0815   0.03125   0.02367  -0.0495   0.0177   1.0000
   8.750   1.1009   0.03349   0.02602  -0.0490   0.0167   1.0000
   9.000   1.1181   0.03588   0.02877  -0.0479   0.0161   1.0000
   9.250   1.1331   0.03825   0.03152  -0.0464   0.0157   1.0000
   9.500   1.1441   0.04109   0.03477  -0.0444   0.0153   1.0000
   9.750   1.1503   0.04427   0.03837  -0.0421   0.0149   1.0000
  10.000   1.1524   0.04742   0.04191  -0.0394   0.0143   1.0000
  10.250   1.1503   0.05025   0.04504  -0.0365   0.0137   1.0000
  10.500   1.1457   0.05259   0.04761  -0.0334   0.0132   1.0000
  10.750   1.1369   0.05541   0.05067  -0.0305   0.0129   1.0000
  11.000   1.1276   0.05819   0.05364  -0.0283   0.0126   1.0000
  11.250   1.1133   0.06182   0.05751  -0.0264   0.0125   1.0000
  11.500   1.0963   0.06603   0.06194  -0.0253   0.0124   1.0000
  11.750   1.0759   0.07105   0.06719  -0.0252   0.0124   1.0000
  12.000   1.0529   0.07694   0.07329  -0.0264   0.0124   1.0000
  12.250   1.0239   0.08465   0.08123  -0.0293   0.0126   1.0000
  12.500   0.9907   0.09463   0.09141  -0.0348   0.0128   1.0000
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