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NACA CYH (nacacyh-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA CYH (nacacyh-il)
Reynolds number: 200,000
Max Cl/Cd: 64.7 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nacacyh-il-200000-n5.txt
Download as CSV file: xf-nacacyh-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5129   0.09005   0.08648  -0.0219   1.0000   0.0304
 -10.750  -0.5242   0.08309   0.07956  -0.0266   1.0000   0.0306
 -10.500  -0.5455   0.07375   0.07029  -0.0346   1.0000   0.0306
 -10.250  -0.6151   0.05417   0.05044  -0.0486   1.0000   0.0302
 -10.000  -0.6479   0.04483   0.04058  -0.0490   1.0000   0.0307
  -9.750  -0.6578   0.03965   0.03492  -0.0471   1.0000   0.0316
  -9.500  -0.6606   0.03588   0.03067  -0.0444   1.0000   0.0324
  -9.250  -0.6444   0.03239   0.02659  -0.0446   0.9887   0.0331
  -9.000  -0.6198   0.02960   0.02332  -0.0455   0.9746   0.0337
  -8.750  -0.5925   0.02759   0.02114  -0.0465   0.9611   0.0346
  -8.500  -0.5637   0.02636   0.01978  -0.0472   0.9465   0.0355
  -8.250  -0.5362   0.02510   0.01829  -0.0475   0.9306   0.0363
  -8.000  -0.5100   0.02377   0.01671  -0.0473   0.9141   0.0370
  -7.750  -0.4846   0.02258   0.01528  -0.0469   0.8977   0.0376
  -7.500  -0.4596   0.02153   0.01400  -0.0462   0.8822   0.0383
  -7.250  -0.4348   0.02064   0.01289  -0.0454   0.8675   0.0391
  -7.000  -0.4099   0.01988   0.01193  -0.0447   0.8542   0.0401
  -6.750  -0.3847   0.01916   0.01103  -0.0439   0.8422   0.0408
  -6.500  -0.3595   0.01848   0.01018  -0.0432   0.8313   0.0412
  -6.250  -0.3347   0.01763   0.00923  -0.0424   0.8212   0.0419
  -6.000  -0.3097   0.01696   0.00850  -0.0417   0.8116   0.0428
  -5.500  -0.2586   0.01597   0.00739  -0.0405   0.7945   0.0446
  -5.000  -0.2068   0.01520   0.00647  -0.0394   0.7790   0.0475
  -4.750  -0.1807   0.01488   0.00606  -0.0389   0.7722   0.0493
  -4.500  -0.1546   0.01452   0.00566  -0.0384   0.7645   0.0513
  -4.250  -0.1286   0.01421   0.00531  -0.0379   0.7567   0.0538
  -4.000  -0.1022   0.01394   0.00500  -0.0374   0.7480   0.0574
  -3.750  -0.0760   0.01368   0.00469  -0.0369   0.7397   0.0629
  -3.500  -0.0494   0.01342   0.00443  -0.0365   0.7303   0.0737
  -3.250  -0.0233   0.01316   0.00418  -0.0360   0.7224   0.0911
  -3.000   0.0029   0.01288   0.00399  -0.0356   0.7129   0.1167
  -2.750   0.0286   0.01257   0.00382  -0.0352   0.7041   0.1580
  -2.500   0.0542   0.01226   0.00370  -0.0347   0.6950   0.2126
  -2.250   0.0800   0.01199   0.00359  -0.0343   0.6873   0.2706
  -2.000   0.1052   0.01167   0.00349  -0.0339   0.6795   0.3350
  -1.750   0.1279   0.01114   0.00339  -0.0330   0.6724   0.4500
  -1.500   0.1478   0.00996   0.00366  -0.0302   0.6651   0.8404
  -1.250   0.1851   0.01009   0.00378  -0.0314   0.6574   0.9062
  -1.000   0.2230   0.01023   0.00386  -0.0329   0.6481   0.9360
  -0.750   0.2674   0.01043   0.00396  -0.0358   0.6387   0.9621
  -0.500   0.3161   0.01055   0.00397  -0.0399   0.6290   0.9764
  -0.250   0.3586   0.01060   0.00395  -0.0430   0.6186   0.9856
   0.000   0.4022   0.01064   0.00389  -0.0463   0.6076   0.9936
   0.250   0.4463   0.01064   0.00380  -0.0499   0.5951   1.0000
   0.500   0.4718   0.01067   0.00375  -0.0495   0.5830   1.0000
   0.750   0.4972   0.01071   0.00373  -0.0492   0.5704   1.0000
   1.000   0.5223   0.01076   0.00372  -0.0488   0.5578   1.0000
   1.250   0.5472   0.01083   0.00373  -0.0483   0.5445   1.0000
   1.500   0.5719   0.01092   0.00375  -0.0478   0.5301   1.0000
   1.750   0.5963   0.01103   0.00379  -0.0473   0.5142   1.0000
   2.000   0.6205   0.01116   0.00384  -0.0467   0.4978   1.0000
   2.250   0.6445   0.01130   0.00391  -0.0461   0.4816   1.0000
   2.500   0.6682   0.01146   0.00402  -0.0455   0.4653   1.0000
   2.750   0.6916   0.01165   0.00413  -0.0449   0.4488   1.0000
   3.000   0.7147   0.01185   0.00427  -0.0442   0.4326   1.0000
   3.250   0.7376   0.01208   0.00443  -0.0434   0.4173   1.0000
   3.500   0.7601   0.01233   0.00460  -0.0426   0.4016   1.0000
   3.750   0.7823   0.01260   0.00480  -0.0418   0.3870   1.0000
   4.000   0.8044   0.01287   0.00502  -0.0410   0.3741   1.0000
   4.250   0.8263   0.01316   0.00525  -0.0401   0.3627   1.0000
   4.500   0.8480   0.01346   0.00550  -0.0392   0.3506   1.0000
   4.750   0.8699   0.01374   0.00576  -0.0384   0.3388   1.0000
   5.000   0.8917   0.01404   0.00604  -0.0376   0.3289   1.0000
   5.250   0.9135   0.01434   0.00633  -0.0367   0.3202   1.0000
   5.500   0.9357   0.01461   0.00663  -0.0360   0.3127   1.0000
   5.750   0.9575   0.01491   0.00696  -0.0352   0.3049   1.0000
   6.000   0.9794   0.01520   0.00728  -0.0344   0.2967   1.0000
   6.250   1.0007   0.01553   0.00761  -0.0335   0.2876   1.0000
   6.500   1.0228   0.01581   0.00795  -0.0328   0.2778   1.0000
   6.750   1.0442   0.01614   0.00833  -0.0320   0.2684   1.0000
   7.000   1.0653   0.01648   0.00870  -0.0312   0.2570   1.0000
   7.250   1.0858   0.01685   0.00908  -0.0304   0.2407   1.0000
   7.500   1.1052   0.01729   0.00949  -0.0294   0.2171   1.0000
   7.750   1.1216   0.01794   0.01001  -0.0281   0.1887   1.0000
   8.000   1.1369   0.01870   0.01065  -0.0267   0.1656   1.0000
   8.250   1.1525   0.01945   0.01134  -0.0254   0.1489   1.0000
   8.500   1.1677   0.02021   0.01206  -0.0241   0.1342   1.0000
   8.750   1.1823   0.02099   0.01281  -0.0227   0.1217   1.0000
   9.000   1.1962   0.02178   0.01361  -0.0212   0.1114   1.0000
   9.250   1.2085   0.02258   0.01441  -0.0196   0.1027   1.0000
   9.500   1.2202   0.02336   0.01523  -0.0178   0.0957   1.0000
   9.750   1.2301   0.02430   0.01618  -0.0161   0.0893   1.0000
  10.000   1.2412   0.02522   0.01716  -0.0147   0.0819   1.0000
  10.250   1.2503   0.02635   0.01833  -0.0133   0.0747   1.0000
  10.500   1.2601   0.02751   0.01952  -0.0121   0.0664   1.0000
  10.750   1.2674   0.02893   0.02093  -0.0110   0.0547   1.0000
  11.000   1.2713   0.03070   0.02266  -0.0099   0.0392   1.0000
  11.250   1.2701   0.03304   0.02491  -0.0088   0.0273   1.0000
  11.500   1.2701   0.03539   0.02728  -0.0080   0.0234   1.0000
  11.750   1.2704   0.03782   0.02977  -0.0074   0.0213   1.0000
  12.000   1.2714   0.04027   0.03232  -0.0071   0.0201   1.0000
  12.250   1.2721   0.04281   0.03501  -0.0069   0.0191   1.0000
  12.500   1.2712   0.04561   0.03793  -0.0068   0.0182   1.0000
  12.750   1.2682   0.04871   0.04115  -0.0069   0.0176   1.0000
  13.000   1.2633   0.05215   0.04472  -0.0072   0.0170   1.0000
  13.250   1.2562   0.05597   0.04868  -0.0078   0.0166   1.0000
  13.500   1.2500   0.05982   0.05266  -0.0085   0.0163   1.0000
  13.750   1.2445   0.06374   0.05673  -0.0094   0.0160   1.0000
  14.000   1.2379   0.06795   0.06108  -0.0105   0.0158   1.0000
  14.250   1.2304   0.07246   0.06574  -0.0119   0.0156   1.0000
  14.500   1.2221   0.07720   0.07063  -0.0134   0.0154   1.0000
  14.750   1.2132   0.08216   0.07573  -0.0151   0.0152   1.0000
  15.000   1.2040   0.08727   0.08098  -0.0169   0.0150   1.0000
  15.250   1.1945   0.09253   0.08636  -0.0188   0.0148   1.0000
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