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NACA CYH (nacacyh-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA CYH (nacacyh-il)
Reynolds number: 200,000
Max Cl/Cd: 65.44 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nacacyh-il-200000.txt
Download as CSV file: xf-nacacyh-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA CYH                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4515   0.09208   0.08863  -0.0202   1.0000   0.0725
  -9.750  -0.4751   0.08476   0.08140  -0.0328   1.0000   0.0761
  -9.500  -0.5133   0.07744   0.07388  -0.0427   1.0000   0.0768
  -9.250  -0.5052   0.07174   0.06831  -0.0419   1.0000   0.0781
  -9.000  -0.4865   0.07057   0.06723  -0.0389   1.0000   0.0794
  -8.750  -0.4775   0.06829   0.06497  -0.0380   1.0000   0.0811
  -8.500  -0.4751   0.06513   0.06181  -0.0384   1.0000   0.0831
  -8.250  -0.4825   0.06192   0.05858  -0.0378   1.0000   0.0855
  -8.000  -0.4984   0.05444   0.05058  -0.0423   0.9905   0.0917
  -7.750  -0.4658   0.05123   0.04745  -0.0449   0.9849   0.0934
  -7.500  -0.4339   0.04845   0.04460  -0.0478   0.9775   0.0971
  -7.250  -0.4282   0.03175   0.02602  -0.0501   0.9623   0.0630
  -7.000  -0.3979   0.02802   0.02185  -0.0515   0.9545   0.0612
  -6.750  -0.3700   0.02564   0.01906  -0.0517   0.9430   0.0614
  -6.500  -0.3422   0.02381   0.01689  -0.0516   0.9317   0.0620
  -6.250  -0.3144   0.02214   0.01490  -0.0513   0.9217   0.0621
  -6.000  -0.2883   0.02084   0.01334  -0.0506   0.9106   0.0626
  -5.750  -0.2625   0.01979   0.01207  -0.0498   0.8995   0.0633
  -5.500  -0.2364   0.01906   0.01114  -0.0489   0.8901   0.0645
  -5.250  -0.2112   0.01787   0.00986  -0.0481   0.8799   0.0664
  -5.000  -0.1858   0.01707   0.00904  -0.0474   0.8706   0.0683
  -4.750  -0.1603   0.01645   0.00837  -0.0465   0.8618   0.0704
  -4.500  -0.1348   0.01591   0.00779  -0.0458   0.8523   0.0731
  -4.000  -0.0857   0.01479   0.00661  -0.0438   0.8330   0.0814
  -3.750  -0.0607   0.01444   0.00621  -0.0428   0.8233   0.0896
  -3.500  -0.0373   0.01379   0.00563  -0.0417   0.8136   0.1071
  -3.250  -0.0146   0.01303   0.00522  -0.0406   0.8036   0.1695
  -3.000   0.0080   0.01246   0.00502  -0.0395   0.7948   0.2710
  -2.750   0.0305   0.01195   0.00488  -0.0385   0.7843   0.3670
  -2.500   0.0486   0.01113   0.00472  -0.0365   0.7761   0.5328
  -2.250   0.0799   0.01049   0.00525  -0.0350   0.7682   0.8956
  -2.000   0.1317   0.01095   0.00557  -0.0382   0.7612   0.9538
  -1.750   0.2122   0.01122   0.00564  -0.0482   0.7521   0.9850
  -1.500   0.2747   0.01118   0.00543  -0.0552   0.7434   1.0000
  -1.250   0.3002   0.01117   0.00531  -0.0548   0.7343   1.0000
  -1.000   0.3259   0.01117   0.00522  -0.0545   0.7257   1.0000
  -0.750   0.3514   0.01117   0.00511  -0.0540   0.7168   1.0000
  -0.500   0.3770   0.01117   0.00505  -0.0537   0.7069   1.0000
   0.000   0.4280   0.01118   0.00490  -0.0528   0.6875   1.0000
   0.250   0.4535   0.01119   0.00485  -0.0523   0.6780   1.0000
   0.500   0.4788   0.01119   0.00478  -0.0518   0.6680   1.0000
   0.750   0.5039   0.01120   0.00476  -0.0514   0.6566   1.0000
   1.000   0.5288   0.01121   0.00471  -0.0508   0.6454   1.0000
   1.250   0.5537   0.01122   0.00464  -0.0502   0.6338   1.0000
   1.500   0.5783   0.01123   0.00462  -0.0496   0.6204   1.0000
   1.750   0.6028   0.01126   0.00461  -0.0490   0.6063   1.0000
   2.000   0.6271   0.01130   0.00461  -0.0483   0.5912   1.0000
   2.250   0.6512   0.01137   0.00461  -0.0476   0.5748   1.0000
   2.500   0.6750   0.01146   0.00462  -0.0469   0.5573   1.0000
   2.750   0.6986   0.01160   0.00469  -0.0461   0.5386   1.0000
   3.000   0.7219   0.01177   0.00480  -0.0454   0.5192   1.0000
   3.250   0.7450   0.01197   0.00491  -0.0446   0.5001   1.0000
   3.500   0.7677   0.01221   0.00505  -0.0438   0.4819   1.0000
   3.750   0.7904   0.01246   0.00521  -0.0430   0.4653   1.0000
   4.000   0.8132   0.01272   0.00542  -0.0422   0.4505   1.0000
   4.250   0.8356   0.01298   0.00564  -0.0414   0.4359   1.0000
   4.500   0.8578   0.01325   0.00585  -0.0405   0.4214   1.0000
   4.750   0.8799   0.01353   0.00610  -0.0397   0.4082   1.0000
   5.000   0.9022   0.01385   0.00636  -0.0389   0.3974   1.0000
   5.250   0.9245   0.01417   0.00666  -0.0381   0.3871   1.0000
   5.500   0.9469   0.01447   0.00699  -0.0373   0.3768   1.0000
   5.750   0.9690   0.01483   0.00731  -0.0366   0.3675   1.0000
   6.000   0.9910   0.01515   0.00767  -0.0358   0.3578   1.0000
   6.250   1.0128   0.01549   0.00804  -0.0350   0.3480   1.0000
   6.500   1.0344   0.01590   0.00840  -0.0342   0.3382   1.0000
   6.750   1.0556   0.01619   0.00878  -0.0333   0.3272   1.0000
   7.000   1.0767   0.01655   0.00920  -0.0324   0.3163   1.0000
   7.250   1.0971   0.01692   0.00958  -0.0315   0.3043   1.0000
   7.500   1.1166   0.01725   0.00994  -0.0304   0.2899   1.0000
   7.750   1.1356   0.01755   0.01031  -0.0293   0.2725   1.0000
   8.000   1.1541   0.01789   0.01070  -0.0282   0.2523   1.0000
   8.250   1.1712   0.01835   0.01114  -0.0269   0.2299   1.0000
   8.500   1.1864   0.01898   0.01169  -0.0255   0.2043   1.0000
   8.750   1.1997   0.01980   0.01241  -0.0238   0.1816   1.0000
   9.000   1.2115   0.02073   0.01326  -0.0220   0.1649   1.0000
   9.250   1.2233   0.02165   0.01416  -0.0203   0.1523   1.0000
   9.500   1.2336   0.02257   0.01507  -0.0183   0.1423   1.0000
   9.750   1.2408   0.02359   0.01604  -0.0160   0.1335   1.0000
  10.000   1.2531   0.02441   0.01696  -0.0145   0.1253   1.0000
  10.250   1.2612   0.02551   0.01808  -0.0129   0.1180   1.0000
  10.500   1.2717   0.02653   0.01916  -0.0117   0.1093   1.0000
  10.750   1.2818   0.02767   0.02037  -0.0106   0.1014   1.0000
  11.000   1.2879   0.02915   0.02186  -0.0095   0.0931   1.0000
  11.250   1.2941   0.03075   0.02351  -0.0086   0.0821   1.0000
  11.500   1.2995   0.03256   0.02535  -0.0079   0.0661   1.0000
  11.750   1.2977   0.03510   0.02784  -0.0071   0.0521   1.0000
  12.000   1.2951   0.03783   0.03056  -0.0064   0.0442   1.0000
  12.250   1.2922   0.04069   0.03346  -0.0060   0.0400   1.0000
  12.500   1.2890   0.04367   0.03650  -0.0058   0.0372   1.0000
  13.000   1.2783   0.05038   0.04339  -0.0059   0.0341   1.0000
  13.250   1.2740   0.05376   0.04689  -0.0061   0.0330   1.0000
  13.500   1.2686   0.05733   0.05056  -0.0065   0.0320   1.0000
  13.750   1.2626   0.06110   0.05443  -0.0071   0.0312   1.0000
  14.000   1.2555   0.06511   0.05851  -0.0078   0.0305   1.0000
  14.250   1.2478   0.06923   0.06268  -0.0086   0.0298   1.0000
  14.500   1.2431   0.07300   0.06654  -0.0092   0.0292   1.0000
  14.750   1.2407   0.07661   0.07028  -0.0100   0.0286   1.0000
  15.000   1.2382   0.08028   0.07406  -0.0108   0.0279   1.0000
  15.250   1.2357   0.08399   0.07787  -0.0117   0.0273   1.0000
  15.500   1.2335   0.08770   0.08167  -0.0127   0.0266   1.0000
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