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NACA 64-210 (naca64210-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-210 (naca64210-il)
Reynolds number: 50,000
Max Cl/Cd: 32.19 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64210-il-50000-n5.txt
Download as CSV file: xf-naca64210-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-210                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5569   0.09848   0.09133  -0.0223   1.0000   0.0524
  -9.750  -0.5592   0.09323   0.08613  -0.0253   1.0000   0.0518
  -9.500  -0.5643   0.08737   0.08032  -0.0293   1.0000   0.0514
  -9.250  -0.5723   0.08163   0.07462  -0.0334   1.0000   0.0506
  -9.000  -0.5847   0.07644   0.06945  -0.0368   1.0000   0.0500
  -8.750  -0.5984   0.07200   0.06499  -0.0387   1.0000   0.0494
  -8.500  -0.6084   0.06759   0.06047  -0.0400   1.0000   0.0493
  -8.250  -0.6147   0.06340   0.05612  -0.0408   1.0000   0.0495
  -8.000  -0.6169   0.05941   0.05189  -0.0410   1.0000   0.0500
  -7.750  -0.6157   0.05555   0.04773  -0.0409   1.0000   0.0506
  -7.500  -0.6111   0.05180   0.04361  -0.0404   1.0000   0.0512
  -7.250  -0.6029   0.04822   0.03965  -0.0396   1.0000   0.0513
  -7.000  -0.5918   0.04485   0.03587  -0.0387   1.0000   0.0514
  -6.750  -0.5782   0.04175   0.03234  -0.0376   1.0000   0.0518
  -6.500  -0.5625   0.03891   0.02902  -0.0364   1.0000   0.0524
  -6.250  -0.5451   0.03649   0.02609  -0.0350   1.0000   0.0542
  -6.000  -0.5272   0.03422   0.02358  -0.0339   1.0000   0.0569
  -5.750  -0.5081   0.03236   0.02158  -0.0328   1.0000   0.0597
  -5.500  -0.4875   0.03058   0.01959  -0.0314   1.0000   0.0617
  -5.250  -0.4664   0.02899   0.01780  -0.0299   1.0000   0.0642
  -5.000  -0.4458   0.02776   0.01630  -0.0283   1.0000   0.0686
  -4.750  -0.4279   0.02653   0.01514  -0.0267   1.0000   0.0742
  -4.500  -0.4097   0.02551   0.01399  -0.0248   1.0000   0.0793
  -4.250  -0.3931   0.02449   0.01290  -0.0230   1.0000   0.0848
  -4.000  -0.3766   0.02365   0.01199  -0.0214   1.0000   0.0960
  -3.750  -0.3601   0.02265   0.01096  -0.0200   1.0000   0.1096
  -3.500  -0.3428   0.02148   0.00995  -0.0191   1.0000   0.1342
  -3.250  -0.3301   0.01887   0.00900  -0.0185   1.0000   0.3639
  -3.000  -0.3224   0.01845   0.00949  -0.0137   1.0000   0.6063
  -2.750  -0.3143   0.01872   0.00997  -0.0086   0.9994   0.7017
  -2.500  -0.3029   0.01961   0.01110  -0.0015   0.9879   0.8014
  -2.250  -0.2806   0.02010   0.01146   0.0021   0.9786   0.8540
  -2.000  -0.2434   0.02008   0.01114   0.0001   0.9701   0.8701
  -1.750  -0.2029   0.02006   0.01085  -0.0028   0.9623   0.8840
  -1.500  -0.1643   0.02001   0.01055  -0.0055   0.9536   0.8972
  -1.250  -0.1230   0.01998   0.01032  -0.0087   0.9459   0.9103
  -1.000  -0.0797   0.01997   0.01013  -0.0123   0.9383   0.9231
  -0.750  -0.0333   0.01996   0.00996  -0.0166   0.9313   0.9348
  -0.500   0.0153   0.01995   0.00983  -0.0213   0.9245   0.9458
  -0.250   0.0654   0.01994   0.00972  -0.0264   0.9181   0.9567
   0.000   0.1144   0.01993   0.00965  -0.0313   0.9108   0.9678
   0.250   0.1658   0.01990   0.00959  -0.0367   0.9045   0.9782
   0.500   0.2131   0.01988   0.00958  -0.0414   0.8963   0.9905
   0.750   0.2514   0.01992   0.00963  -0.0444   0.8875   1.0000
   1.000   0.2782   0.02000   0.00972  -0.0450   0.8778   1.0000
   1.250   0.2956   0.02018   0.00994  -0.0440   0.8657   1.0000
   1.500   0.3139   0.02041   0.01018  -0.0430   0.8544   1.0000
   1.750   0.3368   0.02063   0.01043  -0.0427   0.8448   1.0000
   2.000   0.3618   0.02088   0.01073  -0.0428   0.8356   1.0000
   2.250   0.3831   0.02121   0.01114  -0.0422   0.8250   1.0000
   2.500   0.4101   0.02149   0.01151  -0.0424   0.8163   1.0000
   2.750   0.4363   0.02179   0.01191  -0.0424   0.8067   1.0000
   3.000   0.4598   0.02214   0.01242  -0.0420   0.7956   1.0000
   3.250   0.4865   0.02243   0.01285  -0.0420   0.7852   1.0000
   3.500   0.5167   0.02261   0.01322  -0.0421   0.7757   1.0000
   3.750   0.5408   0.02293   0.01374  -0.0415   0.7630   1.0000
   4.000   0.5680   0.02300   0.01407  -0.0408   0.7483   1.0000
   4.250   0.5958   0.02234   0.01361  -0.0384   0.7198   1.0000
   4.500   0.6177   0.02072   0.01195  -0.0328   0.6551   1.0000
   4.750   0.6345   0.02006   0.01113  -0.0283   0.5728   1.0000
   5.000   0.6496   0.02018   0.01090  -0.0246   0.4289   1.0000
   5.250   0.6504   0.02269   0.01165  -0.0208   0.1882   1.0000
   5.500   0.6603   0.02492   0.01325  -0.0191   0.1223   1.0000
   5.750   0.6749   0.02659   0.01474  -0.0177   0.1003   1.0000
   6.000   0.6923   0.02803   0.01622  -0.0163   0.0887   1.0000
   6.250   0.7118   0.02940   0.01768  -0.0152   0.0786   1.0000
   6.500   0.7337   0.03094   0.01925  -0.0144   0.0715   1.0000
   6.750   0.7620   0.03248   0.02100  -0.0138   0.0661   1.0000
   7.000   0.7889   0.03427   0.02274  -0.0137   0.0606   1.0000
   7.250   0.8182   0.03626   0.02505  -0.0134   0.0566   1.0000
   7.500   0.8460   0.03869   0.02780  -0.0131   0.0543   1.0000
   7.750   0.8703   0.04131   0.03080  -0.0126   0.0526   1.0000
   8.000   0.8908   0.04388   0.03362  -0.0120   0.0503   1.0000
   8.250   0.9088   0.04708   0.03688  -0.0117   0.0479   1.0000
   8.500   0.9209   0.05004   0.04048  -0.0102   0.0466   1.0000
   8.750   0.9303   0.05356   0.04451  -0.0088   0.0460   1.0000
   9.000   0.9356   0.05731   0.04872  -0.0074   0.0457   1.0000
   9.250   0.9369   0.06117   0.05298  -0.0061   0.0456   1.0000
   9.500   0.9337   0.06513   0.05729  -0.0048   0.0456   1.0000
   9.750   0.9261   0.06913   0.06159  -0.0037   0.0456   1.0000
  10.000   0.9136   0.07302   0.06571  -0.0026   0.0458   1.0000
  10.250   0.8977   0.07705   0.06992  -0.0020   0.0459   1.0000
  10.500   0.8806   0.08154   0.07455  -0.0027   0.0462   1.0000
  10.750   0.8629   0.08667   0.07979  -0.0047   0.0464   1.0000
  11.000   0.8460   0.09244   0.08564  -0.0077   0.0467   1.0000
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