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NACA CYH (nacacyh-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA CYH (nacacyh-il)
Reynolds number: 50,000
Max Cl/Cd: 33.25 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nacacyh-il-50000-n5.txt
Download as CSV file: xf-nacacyh-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4508   0.09759   0.09052  -0.0244   1.0000   0.0795
 -10.000  -0.4547   0.09258   0.08557  -0.0277   1.0000   0.0776
  -9.500  -0.5030   0.07654   0.06954  -0.0421   1.0000   0.0720
  -9.250  -0.5056   0.07226   0.06522  -0.0429   1.0000   0.0717
  -9.000  -0.5116   0.06775   0.06060  -0.0436   1.0000   0.0716
  -8.750  -0.5193   0.06326   0.05592  -0.0436   1.0000   0.0719
  -8.250  -0.5169   0.05709   0.04961  -0.0410   1.0000   0.0736
  -8.000  -0.5156   0.05446   0.04687  -0.0391   1.0000   0.0743
  -7.750  -0.5170   0.05159   0.04380  -0.0367   1.0000   0.0745
  -7.500  -0.5185   0.04888   0.04084  -0.0340   1.0000   0.0745
  -7.250  -0.5177   0.04649   0.03816  -0.0313   1.0000   0.0747
  -7.000  -0.5143   0.04429   0.03569  -0.0288   1.0000   0.0750
  -6.750  -0.4895   0.04142   0.03240  -0.0300   0.9928   0.0759
  -6.500  -0.4572   0.03897   0.02957  -0.0322   0.9838   0.0782
  -6.250  -0.4253   0.03671   0.02685  -0.0340   0.9744   0.0814
  -6.000  -0.3925   0.03452   0.02410  -0.0355   0.9654   0.0838
  -5.750  -0.3564   0.03256   0.02162  -0.0373   0.9578   0.0855
  -5.500  -0.3226   0.03094   0.01985  -0.0388   0.9492   0.0878
  -5.250  -0.2862   0.02964   0.01841  -0.0406   0.9417   0.0912
  -5.000  -0.2503   0.02858   0.01713  -0.0421   0.9336   0.0974
  -4.750  -0.2133   0.02752   0.01600  -0.0439   0.9264   0.1043
  -4.500  -0.1780   0.02663   0.01496  -0.0451   0.9180   0.1124
  -4.250  -0.1404   0.02572   0.01402  -0.0468   0.9110   0.1239
  -4.000  -0.1073   0.02498   0.01329  -0.0479   0.9021   0.1457
  -3.750  -0.0752   0.02420   0.01273  -0.0488   0.8939   0.1822
  -3.500  -0.0464   0.02345   0.01237  -0.0493   0.8850   0.2538
  -3.250  -0.0224   0.02255   0.01207  -0.0488   0.8758   0.3629
  -3.000  -0.0004   0.02129   0.01178  -0.0473   0.8679   0.5443
  -2.750   0.1600   0.02067   0.01162  -0.0687   0.8740   1.0000
  -2.500   0.1874   0.02070   0.01137  -0.0687   0.8631   1.0000
  -2.250   0.2138   0.02073   0.01116  -0.0684   0.8514   1.0000
  -2.000   0.2375   0.02079   0.01099  -0.0675   0.8374   1.0000
  -1.750   0.2608   0.02082   0.01083  -0.0664   0.8228   1.0000
  -1.500   0.2835   0.02086   0.01068  -0.0651   0.8082   1.0000
  -1.250   0.3059   0.02093   0.01058  -0.0638   0.7942   1.0000
  -1.000   0.3284   0.02102   0.01051  -0.0626   0.7815   1.0000
  -0.750   0.3520   0.02109   0.01043  -0.0614   0.7704   1.0000
  -0.500   0.3733   0.02127   0.01051  -0.0602   0.7578   1.0000
  -0.250   0.3950   0.02146   0.01061  -0.0590   0.7455   1.0000
   0.000   0.4177   0.02162   0.01067  -0.0579   0.7339   1.0000
   0.250   0.4415   0.02170   0.01064  -0.0568   0.7232   1.0000
   0.500   0.4626   0.02193   0.01082  -0.0555   0.7099   1.0000
   0.750   0.4841   0.02215   0.01099  -0.0543   0.6971   1.0000
   1.000   0.5061   0.02233   0.01112  -0.0531   0.6847   1.0000
   1.250   0.5289   0.02247   0.01120  -0.0519   0.6726   1.0000
   1.500   0.5514   0.02261   0.01130  -0.0507   0.6601   1.0000
   1.750   0.5725   0.02285   0.01152  -0.0495   0.6462   1.0000
   2.000   0.5937   0.02307   0.01174  -0.0482   0.6324   1.0000
   2.250   0.6152   0.02329   0.01194  -0.0470   0.6186   1.0000
   2.500   0.6369   0.02350   0.01214  -0.0458   0.6050   1.0000
   2.750   0.6589   0.02371   0.01235  -0.0446   0.5916   1.0000
   3.000   0.6813   0.02390   0.01252  -0.0434   0.5786   1.0000
   3.250   0.7045   0.02407   0.01266  -0.0423   0.5661   1.0000
   3.500   0.7256   0.02440   0.01303  -0.0412   0.5522   1.0000
   3.750   0.7469   0.02476   0.01341  -0.0401   0.5388   1.0000
   4.000   0.7685   0.02513   0.01380  -0.0391   0.5260   1.0000
   4.250   0.7908   0.02549   0.01419  -0.0381   0.5140   1.0000
   4.500   0.8145   0.02577   0.01444  -0.0373   0.5032   1.0000
   4.750   0.8353   0.02625   0.01498  -0.0362   0.4906   1.0000
   5.000   0.8560   0.02675   0.01554  -0.0352   0.4782   1.0000
   5.250   0.8773   0.02719   0.01604  -0.0342   0.4660   1.0000
   5.500   0.8993   0.02757   0.01644  -0.0333   0.4542   1.0000
   5.750   0.9216   0.02793   0.01681  -0.0323   0.4424   1.0000
   6.000   0.9407   0.02852   0.01752  -0.0312   0.4295   1.0000
   6.250   0.9602   0.02908   0.01816  -0.0301   0.4168   1.0000
   6.500   0.9797   0.02959   0.01873  -0.0290   0.4037   1.0000
   6.750   0.9988   0.03008   0.01926  -0.0277   0.3898   1.0000
   7.000   1.0172   0.03059   0.01984  -0.0265   0.3754   1.0000
   7.250   1.0351   0.03115   0.02044  -0.0252   0.3612   1.0000
   7.500   1.0530   0.03175   0.02108  -0.0239   0.3473   1.0000
   7.750   1.0708   0.03238   0.02174  -0.0227   0.3337   1.0000
   8.000   1.0849   0.03324   0.02274  -0.0212   0.3196   1.0000
   8.250   1.0981   0.03415   0.02382  -0.0196   0.3055   1.0000
   8.500   1.1100   0.03512   0.02491  -0.0180   0.2914   1.0000
   8.750   1.1208   0.03615   0.02607  -0.0163   0.2774   1.0000
   9.000   1.1306   0.03725   0.02730  -0.0145   0.2640   1.0000
   9.250   1.1393   0.03840   0.02855  -0.0127   0.2512   1.0000
   9.500   1.1465   0.03955   0.02978  -0.0108   0.2393   1.0000
   9.750   1.1514   0.04084   0.03116  -0.0088   0.2280   1.0000
  10.000   1.1541   0.04251   0.03297  -0.0069   0.2173   1.0000
  10.250   1.1599   0.04410   0.03464  -0.0055   0.2081   1.0000
  10.500   1.1677   0.04558   0.03617  -0.0043   0.1998   1.0000
  10.750   1.1698   0.04774   0.03850  -0.0031   0.1916   1.0000
  11.000   1.1775   0.04919   0.03992  -0.0021   0.1838   1.0000
  11.250   1.1739   0.05193   0.04288  -0.0013   0.1761   1.0000
  11.500   1.1762   0.05392   0.04489  -0.0006   0.1683   1.0000
  11.750   1.1705   0.05698   0.04812  -0.0003   0.1608   1.0000
  12.000   1.1678   0.05963   0.05081   0.0000   0.1533   1.0000
  12.250   1.1595   0.06317   0.05449  -0.0003   0.1461   1.0000
  12.500   1.1532   0.06650   0.05788  -0.0006   0.1390   1.0000
  12.750   1.1419   0.07078   0.06233  -0.0015   0.1324   1.0000
  13.000   1.1346   0.07449   0.06608  -0.0023   0.1256   1.0000
  13.250   1.1191   0.07987   0.07168  -0.0040   0.1199   1.0000
  13.500   1.1129   0.08357   0.07535  -0.0051   0.1129   1.0000
  13.750   1.0938   0.09018   0.08222  -0.0075   0.1082   1.0000
  14.000   1.0941   0.09294   0.08489  -0.0083   0.1010   1.0000
  14.250   1.0713   0.10091   0.09316  -0.0115   0.0976   1.0000
  14.500   1.0520   0.10841   0.10085  -0.0147   0.0935   1.0000
  14.750   1.0504   0.11199   0.10440  -0.0160   0.0867   1.0000
  15.000   1.0181   0.12312   0.11576  -0.0210   0.0847   1.0000
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