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NACA 64A210 (naca64a210-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 64A210 (naca64a210-il)
Reynolds number: 100,000
Max Cl/Cd: 46.5 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64a210-il-100000-n5.txt
Download as CSV file: xf-naca64a210-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64A210                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5571   0.09073   0.08572  -0.0261   1.0000   0.0279
  -9.500  -0.5617   0.08472   0.07975  -0.0302   1.0000   0.0277
  -9.250  -0.5696   0.07749   0.07256  -0.0364   1.0000   0.0272
  -9.000  -0.5834   0.07099   0.06605  -0.0418   1.0000   0.0267
  -8.750  -0.5976   0.06590   0.06087  -0.0440   1.0000   0.0264
  -8.500  -0.6068   0.06117   0.05599  -0.0451   1.0000   0.0265
  -8.250  -0.6122   0.05686   0.05148  -0.0451   1.0000   0.0268
  -8.000  -0.6148   0.05284   0.04721  -0.0443   1.0000   0.0274
  -7.750  -0.6149   0.04907   0.04315  -0.0429   1.0000   0.0280
  -7.500  -0.6130   0.04548   0.03923  -0.0409   1.0000   0.0283
  -7.250  -0.6086   0.04204   0.03544  -0.0388   1.0000   0.0283
  -7.000  -0.6017   0.03885   0.03185  -0.0366   1.0000   0.0285
  -6.750  -0.5922   0.03594   0.02851  -0.0344   1.0000   0.0288
  -6.500  -0.5801   0.03331   0.02543  -0.0323   1.0000   0.0293
  -6.250  -0.5653   0.03136   0.02299  -0.0303   1.0000   0.0305
  -6.000  -0.5500   0.02909   0.02044  -0.0287   1.0000   0.0321
  -5.750  -0.5325   0.02738   0.01854  -0.0274   1.0000   0.0333
  -5.500  -0.5134   0.02579   0.01674  -0.0261   1.0000   0.0343
  -5.250  -0.4933   0.02439   0.01515  -0.0249   1.0000   0.0354
  -5.000  -0.4670   0.02301   0.01357  -0.0248   0.9983   0.0370
  -4.750  -0.4325   0.02189   0.01224  -0.0263   0.9942   0.0406
  -4.500  -0.4001   0.02059   0.01088  -0.0276   0.9894   0.0439
  -4.250  -0.3666   0.01952   0.00980  -0.0293   0.9850   0.0475
  -4.000  -0.3343   0.01869   0.00884  -0.0305   0.9791   0.0528
  -3.750  -0.3003   0.01791   0.00803  -0.0323   0.9742   0.0636
  -3.500  -0.2683   0.01715   0.00724  -0.0335   0.9678   0.0805
  -3.250  -0.2343   0.01593   0.00653  -0.0356   0.9634   0.1657
  -3.000  -0.2124   0.01409   0.00627  -0.0356   0.9563   0.5130
  -2.750  -0.1805   0.01384   0.00635  -0.0360   0.9512   0.6320
  -2.500  -0.1545   0.01381   0.00648  -0.0349   0.9433   0.7047
  -2.250  -0.1275   0.01384   0.00664  -0.0336   0.9373   0.7682
  -2.000  -0.1012   0.01382   0.00658  -0.0327   0.9294   0.8002
  -1.750  -0.0682   0.01373   0.00639  -0.0335   0.9234   0.8156
  -1.500  -0.0385   0.01366   0.00624  -0.0338   0.9155   0.8291
  -1.250  -0.0057   0.01358   0.00608  -0.0346   0.9092   0.8422
  -1.000   0.0241   0.01353   0.00597  -0.0349   0.9012   0.8559
  -0.750   0.0572   0.01346   0.00586  -0.0358   0.8948   0.8699
  -0.500   0.0883   0.01342   0.00579  -0.0364   0.8868   0.8849
  -0.250   0.1234   0.01337   0.00570  -0.0377   0.8804   0.8999
   0.000   0.1577   0.01335   0.00567  -0.0390   0.8725   0.9159
   0.250   0.1958   0.01330   0.00561  -0.0411   0.8660   0.9314
   0.500   0.2331   0.01329   0.00560  -0.0432   0.8579   0.9479
   0.750   0.2730   0.01325   0.00556  -0.0457   0.8511   0.9635
   1.000   0.3125   0.01324   0.00559  -0.0484   0.8425   0.9797
   1.250   0.3537   0.01319   0.00556  -0.0514   0.8357   0.9948
   1.500   0.3812   0.01324   0.00563  -0.0517   0.8251   1.0000
   1.750   0.4045   0.01330   0.00572  -0.0511   0.8154   1.0000
   2.000   0.4300   0.01334   0.00578  -0.0506   0.8068   1.0000
   2.250   0.4533   0.01347   0.00595  -0.0499   0.7961   1.0000
   2.500   0.4781   0.01357   0.00610  -0.0494   0.7863   1.0000
   2.750   0.5044   0.01363   0.00624  -0.0489   0.7769   1.0000
   3.000   0.5293   0.01371   0.00639  -0.0482   0.7646   1.0000
   3.250   0.5544   0.01371   0.00645  -0.0473   0.7491   1.0000
   3.500   0.5769   0.01358   0.00631  -0.0454   0.7188   1.0000
   3.750   0.5981   0.01348   0.00614  -0.0431   0.6744   1.0000
   4.000   0.6192   0.01354   0.00610  -0.0411   0.6249   1.0000
   4.250   0.6398   0.01376   0.00614  -0.0392   0.5622   1.0000
   4.500   0.6568   0.01432   0.00624  -0.0367   0.4461   1.0000
   4.750   0.6633   0.01617   0.00687  -0.0335   0.2290   1.0000
   5.000   0.6755   0.01789   0.00782  -0.0315   0.1084   1.0000
   5.250   0.6931   0.01904   0.00875  -0.0301   0.0744   1.0000
   5.500   0.7123   0.02001   0.00969  -0.0288   0.0595   1.0000
   5.750   0.7308   0.02105   0.01071  -0.0274   0.0513   1.0000
   6.000   0.7502   0.02202   0.01184  -0.0261   0.0465   1.0000
   6.250   0.7692   0.02308   0.01293  -0.0248   0.0423   1.0000
   6.500   0.7881   0.02433   0.01421  -0.0236   0.0388   1.0000
   6.750   0.8093   0.02554   0.01554  -0.0226   0.0363   1.0000
   7.000   0.8314   0.02696   0.01706  -0.0217   0.0345   1.0000
   7.250   0.8544   0.02851   0.01872  -0.0209   0.0330   1.0000
   7.500   0.8776   0.03024   0.02061  -0.0203   0.0319   1.0000
   7.750   0.9004   0.03229   0.02279  -0.0197   0.0308   1.0000
   8.000   0.9213   0.03502   0.02572  -0.0191   0.0295   1.0000
   8.250   0.9403   0.03683   0.02797  -0.0178   0.0280   1.0000
   8.500   0.9571   0.03943   0.03100  -0.0164   0.0272   1.0000
   8.750   0.9704   0.04243   0.03445  -0.0147   0.0267   1.0000
   9.000   0.9798   0.04571   0.03818  -0.0127   0.0263   1.0000
   9.250   0.9848   0.04924   0.04218  -0.0106   0.0261   1.0000
   9.500   0.9853   0.05294   0.04629  -0.0083   0.0259   1.0000
   9.750   0.9817   0.05659   0.05031  -0.0059   0.0255   1.0000
  10.000   0.9740   0.06016   0.05418  -0.0037   0.0251   1.0000
  10.250   0.9608   0.06357   0.05784  -0.0012   0.0248   1.0000
  10.500   0.9445   0.06732   0.06180   0.0004   0.0246   1.0000
  10.750   0.9249   0.07178   0.06647   0.0007   0.0247   1.0000
  11.000   0.9026   0.07720   0.07208  -0.0006   0.0249   1.0000
  11.250   0.8782   0.08394   0.07897  -0.0039   0.0253   1.0000
  11.500   0.8536   0.09221   0.08731  -0.0092   0.0260   1.0000
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