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NACA 5-H-10 AIRFOIL (n5h10-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 5-H-10 AIRFOIL (n5h10-il)
Reynolds number: 100,000
Max Cl/Cd: 48.44 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n5h10-il-100000.txt
Download as CSV file: xf-n5h10-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4097   0.10541   0.10134  -0.0111   1.0000   0.0853
  -9.750  -0.4216   0.10184   0.09782  -0.0155   1.0000   0.0869
  -9.500  -0.4359   0.09800   0.09404  -0.0206   1.0000   0.0875
  -9.250  -0.4048   0.09238   0.08839  -0.0166   1.0000   0.0925
  -9.000  -0.4023   0.08832   0.08435  -0.0183   1.0000   0.0965
  -8.750  -0.4114   0.08397   0.08005  -0.0224   1.0000   0.0999
  -8.500  -0.4311   0.07935   0.07550  -0.0290   1.0000   0.1012
  -8.250  -0.5021   0.08375   0.07965  -0.0226   1.0000   0.0940
  -8.000  -0.5068   0.08021   0.07612  -0.0249   1.0000   0.0976
  -7.750  -0.5232   0.07731   0.07310  -0.0296   1.0000   0.1013
  -7.500  -0.5284   0.07320   0.06895  -0.0305   1.0000   0.1032
  -7.250  -0.5135   0.06974   0.06562  -0.0283   1.0000   0.1073
  -7.000  -0.5294   0.06848   0.06438  -0.0245   1.0000   0.1093
  -6.750  -0.5273   0.06472   0.06027  -0.0284   0.9873   0.1178
  -6.500  -0.4997   0.06055   0.05612  -0.0306   0.9806   0.1271
  -6.250  -0.4770   0.05624   0.05167  -0.0336   0.9725   0.1386
  -6.000  -0.4596   0.05336   0.04834  -0.0365   0.9627   0.1609
  -5.750  -0.4313   0.04926   0.04438  -0.0382   0.9571   0.1799
  -5.500  -0.4114   0.04663   0.04166  -0.0386   0.9490   0.2092
  -5.250  -0.3462   0.02735   0.02282  -0.0418   0.9269   0.2574
  -5.000  -0.3758   0.04186   0.03686  -0.0373   0.9337   0.2819
  -4.750  -0.3246   0.03288   0.02538  -0.0393   0.9265   0.0986
  -4.500  -0.3027   0.03039   0.02247  -0.0380   0.9182   0.0946
  -4.250  -0.2714   0.02867   0.01992  -0.0370   0.9123   0.0872
  -4.000  -0.2467   0.02674   0.01771  -0.0362   0.9051   0.0865
  -3.750  -0.2177   0.02499   0.01572  -0.0363   0.8996   0.0905
  -3.500  -0.1899   0.02377   0.01436  -0.0362   0.8933   0.0930
  -3.250  -0.1598   0.02272   0.01319  -0.0363   0.8874   0.0959
  -3.000  -0.1320   0.02214   0.01245  -0.0361   0.8818   0.1025
  -2.750  -0.1059   0.02118   0.01164  -0.0360   0.8759   0.1085
  -2.500   0.1400   0.01674   0.00992  -0.0705   0.8897   1.0000
  -2.250   0.1623   0.01696   0.00992  -0.0698   0.8833   1.0000
  -2.000   0.1856   0.01715   0.00996  -0.0697   0.8762   1.0000
  -1.750   0.2068   0.01741   0.01007  -0.0687   0.8702   1.0000
  -1.500   0.2308   0.01764   0.01018  -0.0688   0.8636   1.0000
  -1.250   0.2533   0.01791   0.01034  -0.0682   0.8582   1.0000
  -1.000   0.2766   0.01822   0.01057  -0.0681   0.8529   1.0000
  -0.750   0.2996   0.01852   0.01081  -0.0678   0.8470   1.0000
  -0.500   0.3211   0.01885   0.01106  -0.0669   0.8425   1.0000
  -0.250   0.3456   0.01923   0.01142  -0.0673   0.8371   1.0000
   0.000   0.3683   0.01960   0.01177  -0.0671   0.8323   1.0000
   0.250   0.3899   0.01998   0.01211  -0.0661   0.8281   1.0000
   0.500   0.4127   0.02044   0.01260  -0.0663   0.8219   1.0000
   0.750   0.4341   0.02083   0.01298  -0.0655   0.8167   1.0000
   1.000   0.4549   0.02128   0.01346  -0.0648   0.8103   1.0000
   1.250   0.4752   0.02164   0.01383  -0.0637   0.8034   1.0000
   1.500   0.4954   0.02210   0.01434  -0.0628   0.7971   1.0000
   1.750   0.5155   0.02251   0.01480  -0.0618   0.7901   1.0000
   2.000   0.5351   0.02291   0.01524  -0.0605   0.7834   1.0000
   2.250   0.5546   0.02327   0.01566  -0.0592   0.7755   1.0000
   2.500   0.5740   0.02371   0.01620  -0.0580   0.7689   1.0000
   2.750   0.5931   0.02422   0.01680  -0.0570   0.7620   1.0000
   3.000   0.6132   0.02456   0.01722  -0.0555   0.7561   1.0000
   3.250   0.6316   0.02475   0.01751  -0.0537   0.7461   1.0000
   3.500   0.6497   0.02449   0.01733  -0.0507   0.7329   1.0000
   3.750   0.6685   0.02356   0.01647  -0.0466   0.7175   1.0000
   4.000   0.6873   0.02215   0.01508  -0.0418   0.7015   1.0000
   4.250   0.7052   0.02105   0.01405  -0.0378   0.6831   1.0000
   4.500   0.7258   0.02024   0.01331  -0.0348   0.6710   1.0000
   4.750   0.7466   0.01952   0.01273  -0.0320   0.6582   1.0000
   5.000   0.7656   0.01864   0.01198  -0.0288   0.6355   1.0000
   5.250   0.7850   0.01748   0.01087  -0.0252   0.6061   1.0000
   5.500   0.8031   0.01658   0.01000  -0.0217   0.5569   1.0000
   5.750   0.8040   0.01735   0.00946  -0.0161   0.3048   1.0000
   6.000   0.7933   0.02078   0.01152  -0.0116   0.1354   1.0000
   6.250   0.7994   0.02224   0.01284  -0.0084   0.1095   1.0000
   6.500   0.8075   0.02340   0.01394  -0.0053   0.0973   1.0000
   6.750   0.8164   0.02463   0.01510  -0.0022   0.0902   1.0000
   7.000   0.8288   0.02568   0.01612   0.0004   0.0826   1.0000
   7.250   0.8450   0.02708   0.01746   0.0025   0.0763   1.0000
   7.500   0.8658   0.02849   0.01895   0.0042   0.0721   1.0000
   7.750   0.8877   0.03036   0.02074   0.0052   0.0673   1.0000
   8.000   0.9075   0.03210   0.02273   0.0069   0.0636   1.0000
   8.250   0.9285   0.03432   0.02522   0.0085   0.0620   1.0000
   8.500   0.9461   0.03684   0.02807   0.0104   0.0609   1.0000
   8.750   0.9599   0.03918   0.03069   0.0126   0.0592   1.0000
   9.000   0.9745   0.04136   0.03295   0.0141   0.0567   1.0000
   9.250   0.9834   0.04446   0.03646   0.0167   0.0568   1.0000
   9.500   0.9810   0.04848   0.04119   0.0205   0.0594   1.0000
   9.750   0.9795   0.05272   0.04586   0.0234   0.0619   1.0000
  10.000   0.9798   0.05720   0.05058   0.0255   0.0644   1.0000
  10.250   0.9574   0.06173   0.05575   0.0298   0.0720   1.0000
  10.500   0.9303   0.06733   0.06175   0.0330   0.0845   1.0000
  10.750   0.8458   0.05812   0.05272   0.0382   0.0717   1.0000
  11.000   0.8150   0.06275   0.05752   0.0391   0.0730   1.0000
  11.250   0.7849   0.06799   0.06290   0.0388   0.0739   1.0000
  11.500   0.7542   0.07399   0.06901   0.0374   0.0746   1.0000
  11.750   0.7235   0.08090   0.07600   0.0349   0.0756   1.0000
  12.000   0.6545   0.09620   0.09140   0.0253   0.0854   1.0000
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