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NACA 65(2)-215 (naca652215-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 65(2)-215 (naca652215-il)
Reynolds number: 100,000
Max Cl/Cd: 39.81 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca652215-il-100000-n5.txt
Download as CSV file: xf-naca652215-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(2)-215                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.5954   0.09141   0.08596  -0.0528   1.0000   0.0348
 -12.750  -0.6241   0.08272   0.07718  -0.0584   1.0000   0.0345
 -12.500  -0.6504   0.07587   0.07020  -0.0622   1.0000   0.0342
 -12.250  -0.6759   0.07011   0.06430  -0.0646   1.0000   0.0340
 -12.000  -0.6985   0.06533   0.05935  -0.0658   1.0000   0.0339
 -11.750  -0.7191   0.06123   0.05506  -0.0660   1.0000   0.0338
 -11.500  -0.7366   0.05773   0.05137  -0.0652   1.0000   0.0338
 -11.250  -0.7521   0.05470   0.04814  -0.0636   1.0000   0.0338
 -11.000  -0.7662   0.05211   0.04534  -0.0611   1.0000   0.0339
 -10.750  -0.7808   0.04992   0.04296  -0.0575   1.0000   0.0340
 -10.500  -0.7922   0.04802   0.04087  -0.0535   1.0000   0.0341
 -10.250  -0.8054   0.04641   0.03908  -0.0488   1.0000   0.0343
 -10.000  -0.8104   0.04454   0.03695  -0.0455   0.9962   0.0347
  -9.750  -0.7926   0.04170   0.03356  -0.0466   0.9856   0.0357
  -9.500  -0.7687   0.03910   0.03071  -0.0480   0.9779   0.0368
  -9.250  -0.7394   0.03696   0.02839  -0.0499   0.9724   0.0378
  -9.000  -0.7104   0.03497   0.02617  -0.0513   0.9656   0.0387
  -8.750  -0.6776   0.03308   0.02406  -0.0532   0.9609   0.0396
  -8.500  -0.6475   0.03148   0.02228  -0.0542   0.9538   0.0409
  -8.250  -0.6138   0.03006   0.02065  -0.0559   0.9487   0.0429
  -8.000  -0.5835   0.02876   0.01919  -0.0568   0.9418   0.0448
  -7.750  -0.5524   0.02745   0.01792  -0.0580   0.9358   0.0465
  -7.500  -0.5246   0.02639   0.01684  -0.0585   0.9288   0.0483
  -7.250  -0.4996   0.02546   0.01584  -0.0586   0.9210   0.0503
  -7.000  -0.4764   0.02471   0.01497  -0.0583   0.9131   0.0534
  -6.750  -0.4580   0.02384   0.01412  -0.0574   0.9046   0.0565
  -6.500  -0.4400   0.02317   0.01340  -0.0562   0.8962   0.0602
  -6.250  -0.4212   0.02254   0.01264  -0.0551   0.8883   0.0643
  -6.000  -0.4052   0.02185   0.01197  -0.0536   0.8804   0.0702
  -5.750  -0.3876   0.02119   0.01131  -0.0523   0.8731   0.0812
  -5.500  -0.3712   0.02046   0.01067  -0.0509   0.8662   0.1018
  -5.250  -0.3604   0.01941   0.01000  -0.0488   0.8582   0.1668
  -5.000  -0.3568   0.01780   0.00924  -0.0459   0.8513   0.3234
  -4.750  -0.3488   0.01711   0.00952  -0.0424   0.8437   0.5003
  -4.500  -0.3261   0.01719   0.00964  -0.0410   0.8390   0.5679
  -4.250  -0.3041   0.01750   0.00992  -0.0394   0.8331   0.6085
  -4.000  -0.2826   0.01830   0.01077  -0.0369   0.8272   0.6535
  -3.750  -0.2576   0.01916   0.01161  -0.0346   0.8230   0.6833
  -3.500  -0.2322   0.01942   0.01177  -0.0336   0.8181   0.6945
  -3.250  -0.2075   0.01951   0.01174  -0.0330   0.8126   0.7014
  -3.000  -0.1810   0.01950   0.01161  -0.0326   0.8083   0.7077
  -2.750  -0.1551   0.01930   0.01125  -0.0325   0.8046   0.7147
  -2.500  -0.1312   0.01937   0.01126  -0.0319   0.7983   0.7184
  -2.250  -0.1054   0.01930   0.01111  -0.0317   0.7937   0.7232
  -2.000  -0.0795   0.01908   0.01075  -0.0318   0.7902   0.7294
  -1.750  -0.0540   0.01910   0.01072  -0.0315   0.7855   0.7328
  -1.500  -0.0293   0.01913   0.01070  -0.0311   0.7803   0.7367
  -1.250  -0.0030   0.01903   0.01053  -0.0311   0.7762   0.7414
  -1.000   0.0243   0.01888   0.01028  -0.0314   0.7731   0.7468
  -0.750   0.0478   0.01900   0.01041  -0.0308   0.7679   0.7502
  -0.500   0.0729   0.01903   0.01042  -0.0305   0.7632   0.7541
  -0.250   0.0997   0.01896   0.01030  -0.0306   0.7595   0.7592
   0.000   0.1279   0.01888   0.01016  -0.0309   0.7568   0.7639
   0.250   0.1497   0.01907   0.01040  -0.0302   0.7511   0.7675
   0.500   0.1747   0.01912   0.01047  -0.0299   0.7467   0.7720
   0.750   0.2020   0.01908   0.01040  -0.0301   0.7433   0.7776
   1.000   0.2304   0.01907   0.01039  -0.0302   0.7407   0.7815
   1.250   0.2506   0.01933   0.01073  -0.0293   0.7347   0.7857
   1.500   0.2756   0.01941   0.01084  -0.0291   0.7303   0.7909
   1.750   0.3030   0.01942   0.01087  -0.0293   0.7271   0.7963
   2.000   0.3315   0.01944   0.01093  -0.0293   0.7247   0.8002
   2.250   0.3495   0.01978   0.01138  -0.0282   0.7180   0.8058
   2.500   0.3751   0.01988   0.01152  -0.0282   0.7138   0.8118
   2.750   0.4023   0.01992   0.01165  -0.0280   0.7107   0.8159
   3.000   0.4266   0.02008   0.01189  -0.0276   0.7065   0.8216
   3.250   0.4466   0.02038   0.01229  -0.0268   0.7002   0.8283
   3.500   0.4731   0.02042   0.01244  -0.0264   0.6961   0.8330
   3.750   0.5038   0.02031   0.01241  -0.0267   0.6930   0.8385
   4.000   0.5191   0.02070   0.01294  -0.0251   0.6842   0.8457
   4.250   0.5474   0.02060   0.01296  -0.0249   0.6794   0.8514
   4.500   0.5696   0.02071   0.01320  -0.0241   0.6721   0.8592
   4.750   0.5954   0.02056   0.01318  -0.0233   0.6645   0.8648
   5.000   0.6185   0.02043   0.01320  -0.0222   0.6544   0.8724
   5.250   0.6452   0.01977   0.01263  -0.0209   0.6381   0.8792
   5.500   0.6686   0.01879   0.01165  -0.0187   0.6079   0.8873
   5.750   0.6862   0.01824   0.01111  -0.0159   0.5704   0.8961
   6.000   0.7024   0.01810   0.01102  -0.0136   0.5350   0.9068
   6.250   0.7182   0.01804   0.01086  -0.0110   0.4744   0.9175
   6.500   0.7244   0.01858   0.01072  -0.0072   0.3592   0.9312
   6.750   0.7206   0.02001   0.01153  -0.0032   0.2538   0.9504
   7.000   0.7252   0.02188   0.01279  -0.0017   0.1517   0.9731
   7.250   0.7330   0.02331   0.01384  -0.0006   0.0994   1.0000
   7.500   0.7405   0.02446   0.01481   0.0012   0.0788   1.0000
   7.750   0.7512   0.02558   0.01583   0.0025   0.0684   1.0000
   8.000   0.7636   0.02665   0.01692   0.0037   0.0614   1.0000
   8.250   0.7750   0.02783   0.01808   0.0048   0.0571   1.0000
   8.500   0.7883   0.02891   0.01923   0.0058   0.0527   1.0000
   8.750   0.8001   0.03014   0.02044   0.0069   0.0496   1.0000
   9.000   0.8129   0.03139   0.02172   0.0079   0.0474   1.0000
   9.250   0.8282   0.03255   0.02295   0.0088   0.0456   1.0000
   9.500   0.8444   0.03374   0.02420   0.0096   0.0435   1.0000
   9.750   0.8612   0.03493   0.02538   0.0102   0.0417   1.0000
  10.000   0.8798   0.03630   0.02667   0.0107   0.0397   1.0000
  10.250   0.9014   0.03749   0.02801   0.0112   0.0382   1.0000
  10.500   0.9252   0.03885   0.02952   0.0114   0.0370   1.0000
  10.750   0.9492   0.04034   0.03113   0.0116   0.0360   1.0000
  11.000   0.9719   0.04200   0.03293   0.0118   0.0350   1.0000
  11.250   0.9912   0.04372   0.03476   0.0121   0.0341   1.0000
  11.500   1.0088   0.04553   0.03665   0.0124   0.0331   1.0000
  11.750   1.0276   0.04779   0.03899   0.0125   0.0323   1.0000
  12.000   1.0330   0.05002   0.04157   0.0138   0.0317   1.0000
  12.250   1.0365   0.05255   0.04442   0.0149   0.0311   1.0000
  12.500   1.0376   0.05539   0.04757   0.0160   0.0308   1.0000
  12.750   1.0345   0.05851   0.05098   0.0171   0.0305   1.0000
  13.000   1.0284   0.06184   0.05460   0.0179   0.0303   1.0000
  13.250   1.0183   0.06556   0.05861   0.0185   0.0302   1.0000
  13.500   1.0059   0.06957   0.06288   0.0186   0.0301   1.0000
  13.750   0.9894   0.07415   0.06773   0.0183   0.0300   1.0000
  14.000   0.9705   0.07922   0.07305   0.0173   0.0301   1.0000
  14.250   0.9492   0.08491   0.07898   0.0156   0.0301   1.0000
  14.500   0.9242   0.09156   0.08586   0.0128   0.0302   1.0000
  14.750   0.8974   0.09924   0.09376   0.0088   0.0304   1.0000
  15.000   0.8664   0.10879   0.10350   0.0031   0.0307   1.0000
  15.250   0.8338   0.12045   0.11530  -0.0044   0.0311   1.0000
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