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NACA 65-210 (naca65210-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 65-210 (naca65210-il)
Reynolds number: 200,000
Max Cl/Cd: 58.98 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca65210-il-200000.txt
Download as CSV file: xf-naca65210-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-210                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5283   0.08744   0.08391  -0.0320   1.0000   0.0452
  -9.250  -0.5360   0.08139   0.07791  -0.0374   1.0000   0.0459
  -9.000  -0.5484   0.07555   0.07208  -0.0426   1.0000   0.0460
  -8.750  -0.5666   0.07118   0.06768  -0.0449   1.0000   0.0463
  -8.500  -0.5837   0.06766   0.06402  -0.0456   1.0000   0.0472
  -8.250  -0.5984   0.06580   0.06183  -0.0448   1.0000   0.0481
  -8.000  -0.6038   0.06373   0.05950  -0.0430   1.0000   0.0483
  -7.750  -0.6112   0.05575   0.05158  -0.0425   1.0000   0.0497
  -7.500  -0.6048   0.05264   0.04855  -0.0411   1.0000   0.0510
  -7.250  -0.6025   0.05039   0.04630  -0.0388   1.0000   0.0527
  -7.000  -0.6038   0.04833   0.04415  -0.0357   1.0000   0.0547
  -6.750  -0.6080   0.04975   0.04496  -0.0307   1.0000   0.0611
  -6.500  -0.6127   0.04396   0.03911  -0.0287   1.0000   0.0631
  -6.250  -0.6050   0.04164   0.03695  -0.0270   1.0000   0.0660
  -6.000  -0.5773   0.03856   0.03335  -0.0294   0.9955   0.0771
  -5.750  -0.5464   0.03570   0.03042  -0.0317   0.9913   0.0841
  -5.500  -0.5155   0.03286   0.02734  -0.0341   0.9864   0.0967
  -5.250  -0.4703   0.02599   0.01902  -0.0328   0.9837   0.0469
  -5.000  -0.4377   0.02325   0.01595  -0.0338   0.9790   0.0460
  -4.750  -0.4029   0.02095   0.01336  -0.0350   0.9749   0.0450
  -4.500  -0.3654   0.01928   0.01148  -0.0367   0.9718   0.0455
  -4.250  -0.3275   0.01860   0.01059  -0.0387   0.9681   0.0483
  -4.000  -0.2973   0.01670   0.00872  -0.0393   0.9627   0.0505
  -3.750  -0.2611   0.01559   0.00765  -0.0413   0.9589   0.0541
  -3.500  -0.2214   0.01485   0.00687  -0.0440   0.9563   0.0605
  -3.250  -0.1925   0.01402   0.00605  -0.0447   0.9492   0.0700
  -3.000  -0.1573   0.01310   0.00526  -0.0466   0.9446   0.1059
  -2.750  -0.1441   0.01064   0.00519  -0.0448   0.9373   0.6715
  -2.500  -0.1151   0.01073   0.00535  -0.0443   0.9314   0.7278
  -2.250  -0.0860   0.01103   0.00572  -0.0433   0.9275   0.7760
  -2.000  -0.0677   0.01139   0.00614  -0.0401   0.9186   0.8065
  -1.750  -0.0415   0.01163   0.00636  -0.0386   0.9139   0.8306
  -1.500  -0.0208   0.01178   0.00648  -0.0365   0.9058   0.8451
  -1.250   0.0081   0.01175   0.00639  -0.0363   0.9008   0.8513
  -1.000   0.0338   0.01172   0.00630  -0.0360   0.8936   0.8597
  -0.750   0.0607   0.01168   0.00623  -0.0355   0.8877   0.8659
  -0.500   0.0875   0.01165   0.00615  -0.0354   0.8818   0.8741
  -0.250   0.1121   0.01164   0.00613  -0.0346   0.8748   0.8807
   0.000   0.1403   0.01158   0.00603  -0.0345   0.8704   0.8887
   0.250   0.1630   0.01161   0.00608  -0.0335   0.8623   0.8961
   0.500   0.1900   0.01155   0.00601  -0.0331   0.8573   0.9041
   0.750   0.2141   0.01158   0.00607  -0.0324   0.8502   0.9127
   1.000   0.2408   0.01154   0.00604  -0.0321   0.8445   0.9205
   1.250   0.2666   0.01154   0.00605  -0.0316   0.8387   0.9302
   1.500   0.2955   0.01154   0.00610  -0.0318   0.8321   0.9379
   1.750   0.3268   0.01148   0.00606  -0.0324   0.8276   0.9459
   2.000   0.3582   0.01152   0.00619  -0.0334   0.8200   0.9544
   2.250   0.3953   0.01144   0.00617  -0.0352   0.8143   0.9607
   2.500   0.4310   0.01132   0.00612  -0.0366   0.8034   0.9676
   2.750   0.4676   0.01085   0.00563  -0.0374   0.7852   0.9730
   3.000   0.5033   0.01024   0.00499  -0.0377   0.7487   0.9789
   3.250   0.5397   0.00993   0.00461  -0.0388   0.7132   0.9853
   3.500   0.5762   0.00977   0.00441  -0.0403   0.6603   0.9924
   3.750   0.5941   0.01058   0.00417  -0.0384   0.4199   1.0000
   4.000   0.5753   0.01302   0.00499  -0.0315   0.1149   1.0000
   4.250   0.5822   0.01399   0.00570  -0.0282   0.0717   1.0000
   4.500   0.5990   0.01476   0.00648  -0.0265   0.0615   1.0000
   4.750   0.6174   0.01569   0.00737  -0.0252   0.0545   1.0000
   5.000   0.6381   0.01657   0.00828  -0.0242   0.0499   1.0000
   5.250   0.6599   0.01753   0.00925  -0.0233   0.0467   1.0000
   5.500   0.6825   0.01866   0.01039  -0.0226   0.0444   1.0000
   5.750   0.7070   0.02022   0.01192  -0.0221   0.0426   1.0000
   6.000   0.7346   0.02276   0.01450  -0.0221   0.0408   1.0000
   6.250   0.7607   0.02377   0.01571  -0.0217   0.0394   1.0000
   6.500   0.7877   0.02581   0.01797  -0.0213   0.0391   1.0000
   6.750   0.8134   0.02851   0.02097  -0.0208   0.0396   1.0000
   7.000   0.8395   0.03198   0.02463  -0.0204   0.0416   1.0000
  10.500   0.6849   0.09136   0.08837  -0.0089   0.0602   1.0000
  10.750   0.6684   0.09953   0.09652  -0.0138   0.0595   1.0000
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