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NACA 65-210 (naca65210-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 65-210 (naca65210-il)
Reynolds number: 100,000
Max Cl/Cd: 43.04 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca65210-il-100000-n5.txt
Download as CSV file: xf-naca65210-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4379   0.09166   0.08687  -0.0289   1.0000   0.0330
 -10.000  -0.4450   0.08583   0.08108  -0.0314   1.0000   0.0317
  -9.750  -0.4574   0.07865   0.07395  -0.0350   1.0000   0.0302
  -9.250  -0.5724   0.07292   0.06783  -0.0452   1.0000   0.0272
  -9.000  -0.5839   0.06904   0.06394  -0.0457   1.0000   0.0269
  -8.750  -0.5945   0.06535   0.06018  -0.0455   1.0000   0.0267
  -8.500  -0.6024   0.06144   0.05615  -0.0452   1.0000   0.0265
  -8.250  -0.6075   0.05765   0.05221  -0.0444   1.0000   0.0263
  -8.000  -0.6105   0.05390   0.04825  -0.0431   1.0000   0.0262
  -7.750  -0.6110   0.05040   0.04451  -0.0415   1.0000   0.0262
  -7.500  -0.6101   0.04705   0.04088  -0.0394   1.0000   0.0262
  -7.250  -0.6073   0.04398   0.03743  -0.0370   1.0000   0.0266
  -7.000  -0.6016   0.04196   0.03495  -0.0343   1.0000   0.0275
  -6.750  -0.5995   0.03831   0.03107  -0.0320   1.0000   0.0287
  -6.500  -0.5914   0.03607   0.02864  -0.0299   1.0000   0.0297
  -6.250  -0.5809   0.03384   0.02611  -0.0277   1.0000   0.0301
  -6.000  -0.5565   0.03124   0.02311  -0.0279   0.9963   0.0308
  -5.750  -0.5253   0.02880   0.02027  -0.0293   0.9907   0.0319
  -5.500  -0.4921   0.02705   0.01818  -0.0309   0.9858   0.0348
  -5.250  -0.4600   0.02532   0.01607  -0.0318   0.9800   0.0369
  -5.000  -0.4256   0.02365   0.01412  -0.0332   0.9758   0.0380
  -4.750  -0.3940   0.02238   0.01265  -0.0339   0.9700   0.0392
  -4.500  -0.3623   0.02074   0.01107  -0.0353   0.9655   0.0424
  -4.250  -0.3312   0.01983   0.01011  -0.0364   0.9597   0.0470
  -4.000  -0.2994   0.01893   0.00911  -0.0374   0.9542   0.0501
  -3.750  -0.2675   0.01806   0.00815  -0.0387   0.9490   0.0542
  -3.500  -0.2383   0.01747   0.00749  -0.0393   0.9418   0.0635
  -3.250  -0.2055   0.01674   0.00675  -0.0407   0.9370   0.0803
  -3.000  -0.1844   0.01504   0.00606  -0.0407   0.9286   0.2755
  -2.750  -0.1674   0.01378   0.00647  -0.0382   0.9228   0.6616
  -2.500  -0.1476   0.01402   0.00683  -0.0354   0.9145   0.7368
  -2.250  -0.1254   0.01444   0.00731  -0.0323   0.9090   0.7883
  -2.000  -0.1049   0.01468   0.00747  -0.0298   0.9010   0.8144
  -1.750  -0.0745   0.01463   0.00727  -0.0302   0.8956   0.8245
  -1.500  -0.0473   0.01461   0.00714  -0.0301   0.8888   0.8317
  -1.250  -0.0182   0.01455   0.00696  -0.0304   0.8827   0.8398
  -1.000   0.0105   0.01452   0.00684  -0.0305   0.8769   0.8470
  -0.750   0.0374   0.01449   0.00675  -0.0304   0.8701   0.8549
  -0.500   0.0681   0.01444   0.00664  -0.0310   0.8655   0.8621
  -0.250   0.0931   0.01446   0.00662  -0.0305   0.8577   0.8702
   0.000   0.1227   0.01443   0.00655  -0.0309   0.8526   0.8780
   0.250   0.1492   0.01444   0.00657  -0.0307   0.8458   0.8858
   0.500   0.1767   0.01444   0.00655  -0.0307   0.8398   0.8949
   0.750   0.2065   0.01443   0.00657  -0.0311   0.8345   0.9021
   1.000   0.2332   0.01447   0.00663  -0.0310   0.8275   0.9114
   1.250   0.2648   0.01444   0.00665  -0.0318   0.8228   0.9195
   1.500   0.2931   0.01451   0.00678  -0.0321   0.8155   0.9287
   1.750   0.3239   0.01451   0.00684  -0.0328   0.8100   0.9382
   2.000   0.3576   0.01455   0.00698  -0.0342   0.8037   0.9461
   2.250   0.3912   0.01459   0.00714  -0.0355   0.7973   0.9547
   2.500   0.4265   0.01461   0.00728  -0.0372   0.7915   0.9632
   2.750   0.4626   0.01465   0.00748  -0.0391   0.7834   0.9712
   3.000   0.4989   0.01462   0.00764  -0.0409   0.7739   0.9795
   3.250   0.5327   0.01410   0.00717  -0.0409   0.7450   0.9879
   3.500   0.5613   0.01338   0.00628  -0.0392   0.6716   0.9997
   3.750   0.5737   0.01333   0.00604  -0.0356   0.6017   1.0000
   4.000   0.5826   0.01381   0.00587  -0.0316   0.4477   1.0000
   4.250   0.5793   0.01603   0.00654  -0.0271   0.1791   1.0000
   4.500   0.5909   0.01757   0.00739  -0.0251   0.0784   1.0000
   4.750   0.6102   0.01842   0.00821  -0.0238   0.0632   1.0000
   5.000   0.6299   0.01927   0.00906  -0.0227   0.0544   1.0000
   5.250   0.6499   0.02010   0.00993  -0.0217   0.0480   1.0000
   5.500   0.6680   0.02122   0.01111  -0.0204   0.0450   1.0000
   5.750   0.6884   0.02225   0.01225  -0.0193   0.0428   1.0000
   6.000   0.7101   0.02333   0.01341  -0.0185   0.0398   1.0000
   6.250   0.7324   0.02445   0.01454  -0.0179   0.0365   1.0000
   6.500   0.7558   0.02609   0.01617  -0.0175   0.0345   1.0000
   6.750   0.7822   0.02829   0.01848  -0.0174   0.0333   1.0000
   7.000   0.8081   0.03006   0.02050  -0.0170   0.0325   1.0000
   7.250   0.8331   0.03215   0.02288  -0.0165   0.0319   1.0000
   7.500   0.8556   0.03433   0.02544  -0.0157   0.0308   1.0000
   7.750   0.8755   0.03640   0.02789  -0.0147   0.0290   1.0000
   8.000   0.8931   0.03886   0.03074  -0.0136   0.0277   1.0000
   8.250   0.9077   0.04182   0.03415  -0.0121   0.0272   1.0000
   8.500   0.9189   0.04505   0.03781  -0.0105   0.0269   1.0000
   8.750   0.9260   0.04854   0.04172  -0.0086   0.0266   1.0000
   9.000   0.9291   0.05219   0.04576  -0.0066   0.0265   1.0000
   9.250   0.9306   0.05543   0.04929  -0.0049   0.0259   1.0000
   9.500   0.9330   0.05807   0.05209  -0.0035   0.0250   1.0000
   9.750   0.9320   0.06092   0.05509  -0.0021   0.0243   1.0000
  10.000   0.9231   0.06425   0.05855  -0.0004   0.0237   1.0000
  10.250   0.9086   0.06780   0.06228   0.0015   0.0235   1.0000
  10.500   0.8926   0.07154   0.06620   0.0024   0.0235   1.0000
  10.750   0.8746   0.07584   0.07067   0.0022   0.0235   1.0000
  11.000   0.8559   0.08074   0.07572   0.0007   0.0235   1.0000
  11.250   0.8344   0.08690   0.08206  -0.0028   0.0239   1.0000
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