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NACA 5-H-10 AIRFOIL (n5h10-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 5-H-10 AIRFOIL (n5h10-il)
Reynolds number: 200,000
Max Cl/Cd: 56.19 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n5h10-il-200000-n5.txt
Download as CSV file: xf-n5h10-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 5-H-10 AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4955   0.09001   0.08648  -0.0160   0.8476   0.0147
  -9.000  -0.4990   0.08556   0.08204  -0.0186   0.8419   0.0143
  -8.750  -0.5073   0.08078   0.07726  -0.0218   0.8363   0.0142
  -8.500  -0.5169   0.07639   0.07286  -0.0242   0.8297   0.0139
  -8.250  -0.5289   0.07226   0.06868  -0.0247   0.8242   0.0137
  -8.000  -0.5351   0.06753   0.06387  -0.0257   0.8187   0.0136
  -7.750  -0.5386   0.06261   0.05882  -0.0262   0.8137   0.0134
  -7.250  -0.5373   0.05254   0.04834  -0.0254   0.8046   0.0133
  -7.000  -0.5323   0.04775   0.04327  -0.0242   0.7999   0.0135
  -6.750  -0.5249   0.04330   0.03848  -0.0225   0.7959   0.0138
  -6.500  -0.5135   0.03917   0.03401  -0.0209   0.7910   0.0149
  -6.250  -0.5028   0.03425   0.02857  -0.0185   0.7864   0.0158
  -6.000  -0.4904   0.02933   0.02295  -0.0158   0.7826   0.0165
  -5.750  -0.4717   0.02607   0.01906  -0.0140   0.7785   0.0173
  -5.500  -0.4511   0.02391   0.01658  -0.0130   0.7737   0.0185
  -5.250  -0.4275   0.02355   0.01614  -0.0126   0.7693   0.0202
  -5.000  -0.4032   0.02232   0.01463  -0.0119   0.7652   0.0224
  -4.750  -0.3775   0.02072   0.01269  -0.0112   0.7600   0.0245
  -4.500  -0.3513   0.02018   0.01187  -0.0107   0.7556   0.0267
  -4.250  -0.3265   0.01858   0.01013  -0.0103   0.7523   0.0298
  -4.000  -0.3000   0.01782   0.00928  -0.0101   0.7471   0.0326
  -3.750  -0.2737   0.01726   0.00859  -0.0097   0.7425   0.0362
  -3.500  -0.2475   0.01666   0.00782  -0.0093   0.7387   0.0379
  -3.250  -0.2225   0.01572   0.00688  -0.0089   0.7338   0.0415
  -3.000  -0.1971   0.01523   0.00636  -0.0085   0.7291   0.0443
  -2.750  -0.1720   0.01475   0.00581  -0.0079   0.7253   0.0463
  -2.500  -0.1467   0.01435   0.00533  -0.0074   0.7214   0.0482
  -2.250  -0.1210   0.01405   0.00497  -0.0071   0.7165   0.0504
  -2.000  -0.0961   0.01366   0.00456  -0.0065   0.7124   0.0544
  -1.750  -0.0707   0.01338   0.00421  -0.0060   0.7091   0.0582
  -1.500  -0.0446   0.01316   0.00395  -0.0057   0.7041   0.0645
  -1.250  -0.0196   0.01282   0.00369  -0.0052   0.7000   0.0874
  -1.000  -0.0002   0.01194   0.00346  -0.0040   0.6967   0.2683
  -0.750   0.0031   0.01025   0.00389   0.0019   0.6935   0.8453
  -0.500   0.0248   0.01046   0.00407   0.0038   0.6892   0.8882
  -0.250   0.0597   0.01073   0.00429   0.0033   0.6855   0.9142
   0.000   0.1397   0.01145   0.00489  -0.0061   0.6827   0.9463
   0.250   0.2044   0.01174   0.00509  -0.0133   0.6786   0.9618
   0.500   0.2357   0.01172   0.00501  -0.0142   0.6733   0.9637
   0.750   0.2656   0.01167   0.00491  -0.0148   0.6690   0.9650
   1.000   0.2920   0.01163   0.00482  -0.0147   0.6653   0.9656
   1.250   0.3181   0.01161   0.00481  -0.0146   0.6605   0.9661
   1.500   0.3446   0.01158   0.00476  -0.0144   0.6558   0.9668
   1.750   0.3710   0.01156   0.00470  -0.0143   0.6523   0.9675
   2.000   0.3971   0.01157   0.00476  -0.0142   0.6479   0.9682
   2.250   0.4227   0.01157   0.00477  -0.0139   0.6428   0.9688
   2.500   0.4482   0.01155   0.00473  -0.0136   0.6380   0.9695
   2.750   0.4736   0.01154   0.00479  -0.0133   0.6301   0.9702
   3.000   0.4986   0.01151   0.00474  -0.0127   0.6217   0.9710
   3.250   0.5230   0.01146   0.00468  -0.0121   0.6079   0.9719
   3.500   0.5472   0.01142   0.00467  -0.0114   0.5895   0.9730
   3.750   0.5708   0.01140   0.00464  -0.0106   0.5685   0.9744
   4.000   0.5961   0.01142   0.00467  -0.0103   0.5476   0.9754
   4.250   0.6229   0.01146   0.00476  -0.0103   0.5262   0.9761
   4.500   0.6490   0.01155   0.00481  -0.0101   0.4900   0.9769
   4.750   0.6715   0.01199   0.00488  -0.0096   0.3956   0.9781
   5.000   0.6912   0.01293   0.00538  -0.0090   0.3105   0.9796
   5.250   0.7093   0.01408   0.00605  -0.0084   0.1926   0.9815
   5.500   0.7282   0.01506   0.00673  -0.0078   0.1348   0.9835
   5.750   0.7492   0.01566   0.00726  -0.0072   0.1040   0.9854
   6.000   0.7727   0.01635   0.00785  -0.0073   0.0716   0.9869
   6.250   0.7966   0.01708   0.00848  -0.0074   0.0506   0.9887
   6.500   0.8198   0.01781   0.00922  -0.0075   0.0434   0.9909
   6.750   0.8424   0.01846   0.00999  -0.0073   0.0396   0.9932
   7.000   0.8637   0.01930   0.01090  -0.0071   0.0354   0.9956
   7.250   0.8841   0.02037   0.01207  -0.0069   0.0318   0.9984
   7.500   0.9020   0.02113   0.01296  -0.0060   0.0290   1.0000
   7.750   0.9076   0.02179   0.01369  -0.0027   0.0263   1.0000
   8.000   0.9082   0.02260   0.01458   0.0014   0.0245   1.0000
   8.250   0.9039   0.02385   0.01584   0.0061   0.0229   1.0000
   8.500   0.9123   0.02449   0.01658   0.0089   0.0217   1.0000
   8.750   0.9194   0.02521   0.01740   0.0118   0.0200   1.0000
   9.000   0.9264   0.02610   0.01837   0.0146   0.0182   1.0000
   9.250   0.9352   0.02715   0.01949   0.0168   0.0171   1.0000
   9.500   0.9451   0.02829   0.02069   0.0187   0.0161   1.0000
   9.750   0.9549   0.02963   0.02208   0.0204   0.0151   1.0000
  10.000   0.9671   0.03120   0.02377   0.0220   0.0140   1.0000
  10.250   0.9800   0.03248   0.02522   0.0234   0.0131   1.0000
  10.500   0.9924   0.03413   0.02710   0.0248   0.0124   1.0000
  10.750   1.0028   0.03586   0.02903   0.0262   0.0118   1.0000
  11.000   1.0109   0.03776   0.03112   0.0276   0.0113   1.0000
  11.250   1.0167   0.03975   0.03330   0.0289   0.0109   1.0000
  11.500   1.0204   0.04183   0.03556   0.0302   0.0106   1.0000
  11.750   1.0221   0.04393   0.03781   0.0313   0.0103   1.0000
  12.000   1.0210   0.04655   0.04063   0.0323   0.0101   1.0000
  12.250   1.0163   0.04959   0.04386   0.0332   0.0099   1.0000
  12.500   1.0074   0.05299   0.04749   0.0337   0.0096   1.0000
  12.750   0.9954   0.05702   0.05182   0.0339   0.0094   1.0000
  13.000   0.9829   0.06123   0.05626   0.0336   0.0094   1.0000
  13.250   0.9680   0.06594   0.06122   0.0327   0.0093   1.0000
  13.500   0.9493   0.07150   0.06704   0.0309   0.0089   1.0000
  13.750   0.9333   0.07700   0.07268   0.0287   0.0093   1.0000
  14.000   0.9126   0.08386   0.07973   0.0254   0.0093   1.0000
  14.250   0.8921   0.09160   0.08765   0.0210   0.0093   1.0000
  14.500   0.8738   0.09966   0.09583   0.0163   0.0095   1.0000
  14.750   0.8532   0.10917   0.10543   0.0106   0.0097   1.0000
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