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NACA 0010 (naca0010-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 0010 (naca0010-il)
Reynolds number: 100,000
Max Cl/Cd: 33.51 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca0010-il-100000-n5.txt
Download as CSV file: xf-naca0010-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0010                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.7784   0.09853   0.09336   0.0003   1.0000   0.0361
 -11.750  -0.8751   0.07116   0.06575  -0.0210   1.0000   0.0324
 -11.500  -0.9141   0.06246   0.05674  -0.0267   1.0000   0.0318
 -11.250  -0.9337   0.05792   0.05197  -0.0274   1.0000   0.0320
 -11.000  -0.9465   0.05463   0.04847  -0.0263   1.0000   0.0324
 -10.750  -0.9536   0.05181   0.04544  -0.0247   1.0000   0.0331
 -10.500  -0.9554   0.04902   0.04239  -0.0232   1.0000   0.0342
 -10.250  -0.9559   0.04597   0.03897  -0.0216   1.0000   0.0356
 -10.000  -0.9537   0.04279   0.03532  -0.0198   1.0000   0.0369
  -9.750  -0.9471   0.03983   0.03182  -0.0181   1.0000   0.0381
  -9.500  -0.9344   0.03741   0.02923  -0.0169   1.0000   0.0397
  -9.250  -0.9180   0.03598   0.02773  -0.0160   1.0000   0.0417
  -9.000  -0.9014   0.03432   0.02580  -0.0149   1.0000   0.0439
  -8.750  -0.8836   0.03245   0.02361  -0.0138   1.0000   0.0460
  -8.500  -0.8644   0.03092   0.02171  -0.0127   1.0000   0.0484
  -8.250  -0.8449   0.02930   0.02010  -0.0119   1.0000   0.0509
  -8.000  -0.8241   0.02803   0.01874  -0.0110   1.0000   0.0532
  -7.750  -0.8027   0.02686   0.01741  -0.0101   1.0000   0.0562
  -7.500  -0.7806   0.02580   0.01608  -0.0092   1.0000   0.0592
  -7.250  -0.7599   0.02450   0.01479  -0.0083   1.0000   0.0618
  -7.000  -0.7387   0.02348   0.01375  -0.0073   1.0000   0.0645
  -6.750  -0.7171   0.02259   0.01277  -0.0063   1.0000   0.0683
  -6.500  -0.6955   0.02174   0.01183  -0.0053   1.0000   0.0728
  -6.250  -0.6751   0.02084   0.01093  -0.0042   1.0000   0.0778
  -6.000  -0.6537   0.02006   0.01007  -0.0031   1.0000   0.0839
  -5.750  -0.6331   0.01922   0.00928  -0.0020   1.0000   0.0920
  -5.500  -0.6120   0.01846   0.00855  -0.0009   1.0000   0.1043
  -5.250  -0.5908   0.01774   0.00790   0.0002   1.0000   0.1248
  -5.000  -0.5698   0.01703   0.00734   0.0012   1.0000   0.1544
  -4.750  -0.5486   0.01637   0.00685   0.0022   1.0000   0.1905
  -4.500  -0.5273   0.01578   0.00644   0.0032   1.0000   0.2324
  -4.250  -0.5062   0.01519   0.00608   0.0043   1.0000   0.2846
  -4.000  -0.4856   0.01461   0.00581   0.0054   1.0000   0.3474
  -3.750  -0.4647   0.01412   0.00559   0.0066   1.0000   0.4083
  -3.500  -0.4429   0.01373   0.00538   0.0078   1.0000   0.4584
  -3.250  -0.4208   0.01341   0.00522   0.0090   1.0000   0.5041
  -3.000  -0.3986   0.01311   0.00509   0.0102   1.0000   0.5503
  -2.750  -0.3763   0.01286   0.00501   0.0114   1.0000   0.5965
  -2.500  -0.3538   0.01265   0.00495   0.0127   1.0000   0.6422
  -2.250  -0.3310   0.01249   0.00494   0.0140   1.0000   0.6857
  -2.000  -0.3077   0.01239   0.00496   0.0153   1.0000   0.7269
  -1.750  -0.2847   0.01233   0.00501   0.0166   1.0000   0.7668
  -1.500  -0.2611   0.01234   0.00510   0.0179   1.0000   0.8051
  -1.250  -0.2362   0.01239   0.00522   0.0188   1.0000   0.8420
  -1.000  -0.1959   0.01251   0.00535   0.0166   0.9941   0.8751
  -0.750  -0.1497   0.01263   0.00546   0.0131   0.9856   0.9025
  -0.500  -0.1007   0.01272   0.00554   0.0090   0.9767   0.9237
  -0.250  -0.0505   0.01278   0.00559   0.0045   0.9669   0.9412
   0.000   0.0000   0.01280   0.00560   0.0000   0.9554   0.9554
   0.250   0.0505   0.01278   0.00559  -0.0045   0.9412   0.9669
   0.500   0.1007   0.01272   0.00554  -0.0090   0.9237   0.9767
   0.750   0.1497   0.01263   0.00546  -0.0131   0.9025   0.9856
   1.000   0.1959   0.01251   0.00535  -0.0166   0.8751   0.9941
   1.250   0.2362   0.01239   0.00522  -0.0188   0.8420   1.0000
   1.500   0.2611   0.01234   0.00510  -0.0179   0.8052   1.0000
   1.750   0.2846   0.01233   0.00501  -0.0166   0.7668   1.0000
   2.000   0.3077   0.01239   0.00496  -0.0153   0.7269   1.0000
   2.250   0.3310   0.01249   0.00494  -0.0140   0.6857   1.0000
   2.500   0.3538   0.01265   0.00495  -0.0127   0.6422   1.0000
   2.750   0.3763   0.01286   0.00501  -0.0114   0.5965   1.0000
   3.000   0.3986   0.01311   0.00509  -0.0102   0.5503   1.0000
   3.250   0.4208   0.01340   0.00522  -0.0090   0.5041   1.0000
   3.500   0.4429   0.01373   0.00538  -0.0078   0.4584   1.0000
   3.750   0.4646   0.01412   0.00559  -0.0066   0.4083   1.0000
   4.000   0.4855   0.01461   0.00581  -0.0054   0.3474   1.0000
   4.250   0.5062   0.01519   0.00608  -0.0043   0.2847   1.0000
   4.500   0.5272   0.01578   0.00643  -0.0032   0.2324   1.0000
   4.750   0.5486   0.01637   0.00685  -0.0022   0.1905   1.0000
   5.000   0.5698   0.01703   0.00734  -0.0012   0.1544   1.0000
   5.250   0.5908   0.01774   0.00790  -0.0002   0.1248   1.0000
   5.500   0.6120   0.01846   0.00855   0.0009   0.1043   1.0000
   5.750   0.6331   0.01922   0.00928   0.0020   0.0920   1.0000
   6.000   0.6537   0.02006   0.01007   0.0031   0.0839   1.0000
   6.250   0.6751   0.02084   0.01093   0.0042   0.0778   1.0000
   6.500   0.6956   0.02173   0.01183   0.0053   0.0729   1.0000
   6.750   0.7171   0.02259   0.01277   0.0063   0.0683   1.0000
   7.000   0.7387   0.02348   0.01374   0.0073   0.0645   1.0000
   7.250   0.7599   0.02450   0.01479   0.0083   0.0618   1.0000
   7.500   0.7806   0.02580   0.01608   0.0092   0.0592   1.0000
   7.750   0.8028   0.02686   0.01741   0.0101   0.0562   1.0000
   8.000   0.8241   0.02803   0.01874   0.0110   0.0532   1.0000
   8.250   0.8449   0.02930   0.02010   0.0119   0.0509   1.0000
   8.500   0.8644   0.03092   0.02171   0.0126   0.0484   1.0000
   8.750   0.8836   0.03245   0.02361   0.0138   0.0460   1.0000
   9.000   0.9015   0.03432   0.02580   0.0149   0.0439   1.0000
   9.250   0.9181   0.03598   0.02773   0.0160   0.0417   1.0000
   9.500   0.9345   0.03741   0.02923   0.0169   0.0397   1.0000
   9.750   0.9472   0.03984   0.03183   0.0180   0.0381   1.0000
  10.000   0.9538   0.04280   0.03533   0.0198   0.0369   1.0000
  10.250   0.9560   0.04598   0.03898   0.0216   0.0356   1.0000
  10.500   0.9556   0.04904   0.04241   0.0232   0.0342   1.0000
  10.750   0.9538   0.05183   0.04546   0.0246   0.0331   1.0000
  11.000   0.9469   0.05465   0.04849   0.0262   0.0324   1.0000
  11.250   0.9342   0.05793   0.05197   0.0273   0.0319   1.0000
  11.500   0.9145   0.06251   0.05678   0.0265   0.0318   1.0000
  11.750   0.8751   0.07130   0.06590   0.0208   0.0324   1.0000
  12.000   0.7786   0.09881   0.09365  -0.0006   0.0361   1.0000
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