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NACA 65-210 (naca65210-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 65-210 (naca65210-il)
Reynolds number: 200,000
Max Cl/Cd: 50.83 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca65210-il-200000-n5.txt
Download as CSV file: xf-naca65210-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5519   0.08626   0.08270  -0.0304   1.0000   0.0147
  -9.750  -0.5674   0.07668   0.07318  -0.0376   1.0000   0.0140
  -9.500  -0.6009   0.06505   0.06146  -0.0463   1.0000   0.0134
  -9.250  -0.6222   0.05981   0.05611  -0.0473   1.0000   0.0133
  -9.000  -0.6379   0.05505   0.05116  -0.0465   1.0000   0.0131
  -8.750  -0.6468   0.05122   0.04717  -0.0455   1.0000   0.0132
  -8.500  -0.6511   0.04771   0.04346  -0.0442   1.0000   0.0134
  -8.250  -0.6513   0.04462   0.04017  -0.0425   1.0000   0.0136
  -8.000  -0.6423   0.04378   0.03928  -0.0412   1.0000   0.0142
  -7.750  -0.6383   0.04156   0.03689  -0.0391   1.0000   0.0148
  -7.500  -0.6347   0.03943   0.03457  -0.0364   1.0000   0.0157
  -7.250  -0.6136   0.03480   0.02942  -0.0376   0.9926   0.0165
  -7.000  -0.5881   0.03053   0.02455  -0.0389   0.9861   0.0170
  -6.750  -0.5608   0.02725   0.02070  -0.0397   0.9797   0.0179
  -6.500  -0.5302   0.02488   0.01784  -0.0409   0.9750   0.0192
  -6.250  -0.5023   0.02314   0.01598  -0.0420   0.9683   0.0207
  -6.000  -0.4702   0.02160   0.01421  -0.0434   0.9639   0.0218
  -5.750  -0.4412   0.02023   0.01264  -0.0439   0.9568   0.0229
  -5.500  -0.4093   0.01901   0.01122  -0.0449   0.9517   0.0243
  -5.250  -0.3801   0.01823   0.01030  -0.0454   0.9445   0.0264
  -5.000  -0.3498   0.01731   0.00926  -0.0460   0.9384   0.0273
  -4.750  -0.3235   0.01609   0.00798  -0.0460   0.9308   0.0285
  -4.500  -0.2969   0.01510   0.00694  -0.0461   0.9238   0.0303
  -4.250  -0.2714   0.01447   0.00627  -0.0459   0.9155   0.0324
  -4.000  -0.2440   0.01399   0.00572  -0.0460   0.9087   0.0360
  -3.750  -0.2186   0.01356   0.00520  -0.0457   0.9002   0.0387
  -3.250  -0.1668   0.01266   0.00415  -0.0452   0.8854   0.0500
  -3.000  -0.1410   0.01218   0.00375  -0.0450   0.8789   0.0752
  -2.750  -0.1207   0.01085   0.00328  -0.0446   0.8704   0.2868
  -2.500  -0.1026   0.00960   0.00319  -0.0433   0.8636   0.5800
  -2.250  -0.0802   0.00946   0.00338  -0.0418   0.8561   0.6816
  -2.000  -0.0554   0.00949   0.00346  -0.0407   0.8501   0.7240
  -1.750  -0.0302   0.00954   0.00351  -0.0398   0.8426   0.7483
  -1.500  -0.0039   0.00956   0.00347  -0.0392   0.8370   0.7654
  -1.250   0.0227   0.00956   0.00344  -0.0389   0.8300   0.7730
  -1.000   0.0504   0.00954   0.00335  -0.0389   0.8239   0.7804
  -0.750   0.0774   0.00953   0.00332  -0.0386   0.8174   0.7863
  -0.500   0.1049   0.00953   0.00326  -0.0386   0.8113   0.7937
  -0.250   0.1320   0.00953   0.00325  -0.0384   0.8056   0.7996
   0.000   0.1593   0.00954   0.00324  -0.0383   0.7989   0.8067
   0.250   0.1865   0.00955   0.00324  -0.0381   0.7937   0.8130
   0.500   0.2135   0.00957   0.00328  -0.0380   0.7869   0.8202
   0.750   0.2406   0.00958   0.00330  -0.0378   0.7811   0.8267
   1.000   0.2676   0.00961   0.00336  -0.0376   0.7751   0.8340
   1.250   0.2944   0.00964   0.00343  -0.0374   0.7688   0.8411
   1.500   0.3213   0.00968   0.00350  -0.0371   0.7633   0.8484
   1.750   0.3478   0.00972   0.00360  -0.0368   0.7564   0.8556
   2.000   0.3745   0.00976   0.00370  -0.0365   0.7509   0.8635
   2.250   0.4004   0.00980   0.00384  -0.0361   0.7430   0.8711
   2.500   0.4261   0.00980   0.00387  -0.0355   0.7300   0.8797
   2.750   0.4498   0.00974   0.00379  -0.0341   0.7053   0.8876
   3.000   0.4728   0.00971   0.00372  -0.0327   0.6680   0.8969
   3.250   0.4941   0.00980   0.00362  -0.0309   0.6068   0.9069
   3.500   0.5139   0.01011   0.00361  -0.0291   0.5123   0.9172
   3.750   0.5223   0.01156   0.00399  -0.0260   0.2874   0.9314
   4.000   0.5364   0.01307   0.00465  -0.0245   0.1054   0.9465
   4.250   0.5613   0.01389   0.00523  -0.0245   0.0529   0.9605
   4.500   0.5918   0.01445   0.00579  -0.0255   0.0417   0.9751
   4.750   0.6226   0.01505   0.00644  -0.0267   0.0363   1.0000
   5.000   0.6436   0.01580   0.00723  -0.0259   0.0328   1.0000
   5.250   0.6667   0.01634   0.00787  -0.0254   0.0300   1.0000
   5.500   0.6889   0.01703   0.00861  -0.0247   0.0278   1.0000
   5.750   0.7105   0.01783   0.00945  -0.0240   0.0262   1.0000
   6.000   0.7317   0.01877   0.01041  -0.0232   0.0249   1.0000
   6.250   0.7522   0.02012   0.01179  -0.0224   0.0237   1.0000
   6.500   0.7749   0.02172   0.01347  -0.0217   0.0229   1.0000
   6.750   0.7994   0.02283   0.01470  -0.0213   0.0224   1.0000
   7.000   0.8239   0.02384   0.01587  -0.0210   0.0212   1.0000
   7.250   0.8480   0.02509   0.01728  -0.0206   0.0201   1.0000
   7.500   0.8717   0.02671   0.01911  -0.0201   0.0193   1.0000
   7.750   0.8943   0.02850   0.02114  -0.0195   0.0187   1.0000
   8.000   0.9153   0.03043   0.02334  -0.0187   0.0180   1.0000
   8.250   0.9345   0.03212   0.02525  -0.0179   0.0173   1.0000
   8.500   0.9522   0.03350   0.02674  -0.0172   0.0163   1.0000
   8.750   0.9639   0.03664   0.03021  -0.0159   0.0154   1.0000
   9.000   0.9746   0.03948   0.03349  -0.0140   0.0151   1.0000
   9.250   0.9803   0.04295   0.03743  -0.0118   0.0147   1.0000
   9.500   0.9802   0.04687   0.04177  -0.0093   0.0144   1.0000
   9.750   0.9750   0.05092   0.04619  -0.0067   0.0143   1.0000
  10.000   0.9629   0.05491   0.05050  -0.0037   0.0141   1.0000
  10.250   0.9468   0.05857   0.05439  -0.0009   0.0140   1.0000
  10.500   0.9290   0.06247   0.05850   0.0008   0.0139   1.0000
  10.750   0.9087   0.06704   0.06325   0.0011   0.0139   1.0000
  11.000   0.8874   0.07227   0.06865  -0.0001   0.0140   1.0000
  11.250   0.8658   0.07834   0.07485  -0.0029   0.0142   1.0000
  11.500   0.8435   0.08582   0.08245  -0.0076   0.0144   1.0000
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