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NACA CYH (nacacyh-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA CYH (nacacyh-il)
Reynolds number: 500,000
Max Cl/Cd: 90.52 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nacacyh-il-500000.txt
Download as CSV file: xf-nacacyh-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4044   0.07917   0.07708  -0.0301   1.0000   0.0390
 -10.500  -0.3982   0.07672   0.07464  -0.0301   1.0000   0.0395
 -10.250  -0.3964   0.07335   0.07129  -0.0310   1.0000   0.0401
 -10.000  -0.6651   0.04210   0.03880  -0.0482   1.0000   0.0318
  -9.750  -0.6671   0.03841   0.03480  -0.0458   1.0000   0.0317
  -9.500  -0.6684   0.03539   0.03152  -0.0425   1.0000   0.0317
  -9.250  -0.6491   0.03006   0.02567  -0.0442   0.9918   0.0318
  -9.000  -0.6254   0.02592   0.02116  -0.0456   0.9819   0.0324
  -8.750  -0.5932   0.02489   0.02013  -0.0470   0.9703   0.0334
  -8.500  -0.5645   0.02373   0.01886  -0.0475   0.9540   0.0342
  -8.250  -0.5423   0.02209   0.01695  -0.0465   0.9317   0.0346
  -8.000  -0.5216   0.02075   0.01534  -0.0450   0.9091   0.0351
  -7.750  -0.5000   0.01966   0.01400  -0.0436   0.8879   0.0357
  -7.500  -0.4769   0.01880   0.01291  -0.0425   0.8697   0.0364
  -7.250  -0.4530   0.01794   0.01182  -0.0415   0.8546   0.0370
  -7.000  -0.4282   0.01714   0.01082  -0.0406   0.8416   0.0373
  -6.750  -0.4028   0.01649   0.01000  -0.0399   0.8298   0.0377
  -6.500  -0.3767   0.01588   0.00925  -0.0393   0.8195   0.0381
  -6.250  -0.3526   0.01450   0.00774  -0.0386   0.8107   0.0390
  -6.000  -0.3268   0.01384   0.00704  -0.0381   0.8016   0.0400
  -5.750  -0.3008   0.01336   0.00648  -0.0375   0.7935   0.0407
  -5.500  -0.2744   0.01291   0.00598  -0.0370   0.7847   0.0414
  -5.250  -0.2482   0.01253   0.00552  -0.0364   0.7763   0.0423
  -5.000  -0.2218   0.01215   0.00509  -0.0359   0.7676   0.0432
  -4.750  -0.1952   0.01184   0.00470  -0.0355   0.7602   0.0442
  -4.500  -0.1682   0.01157   0.00438  -0.0351   0.7524   0.0453
  -4.250  -0.1422   0.01118   0.00392  -0.0345   0.7452   0.0471
  -4.000  -0.1153   0.01086   0.00361  -0.0342   0.7373   0.0492
  -3.750  -0.0883   0.01067   0.00336  -0.0338   0.7304   0.0517
  -3.250  -0.0339   0.01022   0.00290  -0.0331   0.7152   0.0638
  -3.000  -0.0073   0.00986   0.00269  -0.0328   0.7080   0.0959
  -2.750   0.0189   0.00952   0.00253  -0.0325   0.7014   0.1470
  -2.500   0.0452   0.00920   0.00244  -0.0322   0.6951   0.2133
  -2.250   0.0717   0.00893   0.00237  -0.0319   0.6882   0.2729
  -2.000   0.0980   0.00870   0.00229  -0.0316   0.6820   0.3330
  -1.750   0.1229   0.00825   0.00221  -0.0311   0.6745   0.4341
  -1.500   0.1361   0.00701   0.00212  -0.0282   0.6679   0.7489
  -1.250   0.1589   0.00682   0.00233  -0.0262   0.6605   0.8949
  -1.000   0.1879   0.00690   0.00240  -0.0259   0.6530   0.9274
  -0.750   0.2203   0.00703   0.00251  -0.0263   0.6453   0.9482
  -0.500   0.2576   0.00721   0.00262  -0.0278   0.6369   0.9632
  -0.250   0.3069   0.00741   0.00276  -0.0320   0.6275   0.9739
   0.000   0.3493   0.00757   0.00282  -0.0349   0.6178   0.9821
   0.250   0.4004   0.00765   0.00284  -0.0398   0.6058   0.9876
   0.500   0.4446   0.00773   0.00286  -0.0433   0.5940   0.9940
   0.750   0.4905   0.00775   0.00281  -0.0473   0.5812   0.9980
   1.000   0.5259   0.00778   0.00277  -0.0491   0.5681   1.0000
   1.250   0.5519   0.00783   0.00275  -0.0488   0.5544   1.0000
   1.500   0.5778   0.00788   0.00275  -0.0486   0.5388   1.0000
   1.750   0.6036   0.00796   0.00276  -0.0484   0.5217   1.0000
   2.000   0.6292   0.00805   0.00278  -0.0482   0.5032   1.0000
   2.250   0.6545   0.00818   0.00282  -0.0479   0.4819   1.0000
   2.500   0.6795   0.00835   0.00288  -0.0476   0.4568   1.0000
   2.750   0.7039   0.00857   0.00297  -0.0472   0.4308   1.0000
   3.000   0.7280   0.00878   0.00307  -0.0467   0.4079   1.0000
   3.250   0.7517   0.00900   0.00320  -0.0462   0.3892   1.0000
   3.500   0.7754   0.00921   0.00334  -0.0457   0.3747   1.0000
   3.750   0.7989   0.00941   0.00349  -0.0451   0.3630   1.0000
   4.000   0.8219   0.00963   0.00365  -0.0444   0.3523   1.0000
   4.250   0.8452   0.00981   0.00382  -0.0438   0.3438   1.0000
   4.500   0.8682   0.01001   0.00400  -0.0431   0.3368   1.0000
   4.750   0.8913   0.01018   0.00418  -0.0425   0.3296   1.0000
   5.000   0.9136   0.01042   0.00438  -0.0417   0.3224   1.0000
   5.250   0.9369   0.01057   0.00457  -0.0410   0.3152   1.0000
   5.500   0.9588   0.01083   0.00479  -0.0402   0.3082   1.0000
   5.750   0.9822   0.01097   0.00497  -0.0396   0.3006   1.0000
   6.000   1.0040   0.01122   0.00520  -0.0388   0.2913   1.0000
   6.250   1.0270   0.01139   0.00539  -0.0381   0.2809   1.0000
   6.500   1.0495   0.01160   0.00560  -0.0374   0.2693   1.0000
   6.750   1.0717   0.01184   0.00583  -0.0367   0.2560   1.0000
   7.000   1.0934   0.01212   0.00607  -0.0360   0.2402   1.0000
   7.250   1.1140   0.01248   0.00635  -0.0350   0.2193   1.0000
   7.500   1.1330   0.01298   0.00672  -0.0339   0.1924   1.0000
   7.750   1.1500   0.01365   0.00723  -0.0326   0.1647   1.0000
   8.000   1.1673   0.01430   0.00778  -0.0313   0.1436   1.0000
   8.250   1.1854   0.01491   0.00831  -0.0302   0.1268   1.0000
   8.500   1.2038   0.01550   0.00885  -0.0292   0.1136   1.0000
   8.750   1.2223   0.01608   0.00939  -0.0282   0.1035   1.0000
   9.250   1.2587   0.01723   0.01051  -0.0262   0.0865   1.0000
   9.500   1.2763   0.01782   0.01109  -0.0252   0.0785   1.0000
   9.750   1.2919   0.01851   0.01174  -0.0239   0.0675   1.0000
  10.000   1.3022   0.01942   0.01254  -0.0219   0.0508   1.0000
  10.250   1.3030   0.02084   0.01378  -0.0188   0.0287   1.0000
  10.500   1.3087   0.02210   0.01503  -0.0166   0.0234   1.0000
  10.750   1.3164   0.02333   0.01631  -0.0149   0.0214   1.0000
  11.000   1.3231   0.02473   0.01778  -0.0135   0.0199   1.0000
  11.250   1.3317   0.02607   0.01922  -0.0124   0.0191   1.0000
  11.500   1.3386   0.02765   0.02089  -0.0115   0.0182   1.0000
  11.750   1.3432   0.02951   0.02284  -0.0107   0.0176   1.0000
  12.000   1.3445   0.03177   0.02519  -0.0101   0.0170   1.0000
  12.250   1.3417   0.03454   0.02806  -0.0095   0.0165   1.0000
  12.500   1.3426   0.03703   0.03066  -0.0092   0.0162   1.0000
  12.750   1.3443   0.03952   0.03325  -0.0091   0.0159   1.0000
  13.000   1.3438   0.04228   0.03613  -0.0091   0.0156   1.0000
  13.250   1.3419   0.04529   0.03925  -0.0092   0.0154   1.0000
  13.500   1.3384   0.04854   0.04260  -0.0094   0.0151   1.0000
  13.750   1.3338   0.05202   0.04619  -0.0099   0.0149   1.0000
  14.000   1.3282   0.05572   0.04999  -0.0104   0.0147   1.0000
  14.250   1.3219   0.05965   0.05401  -0.0112   0.0145   1.0000
  14.500   1.3153   0.06375   0.05822  -0.0122   0.0143   1.0000
  14.750   1.3079   0.06804   0.06260  -0.0132   0.0142   1.0000
  15.000   1.3003   0.07246   0.06710  -0.0144   0.0140   1.0000
  15.250   1.2926   0.07694   0.07167  -0.0156   0.0138   1.0000
  15.500   1.2845   0.08146   0.07627  -0.0169   0.0137   1.0000
  15.750   1.2765   0.08593   0.08080  -0.0180   0.0135   1.0000
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