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NACA CYH (nacacyh-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA CYH (nacacyh-il)
Reynolds number: 100,000
Max Cl/Cd: 49.38 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nacacyh-il-100000-n5.txt
Download as CSV file: xf-nacacyh-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4811   0.09058   0.08558  -0.0257   1.0000   0.0480
 -10.250  -0.4861   0.08515   0.08020  -0.0293   1.0000   0.0475
 -10.000  -0.4950   0.07894   0.07404  -0.0343   1.0000   0.0471
  -9.750  -0.5110   0.07202   0.06714  -0.0399   1.0000   0.0466
  -9.500  -0.5279   0.06474   0.05978  -0.0438   1.0000   0.0462
  -9.250  -0.5429   0.05802   0.05286  -0.0456   1.0000   0.0462
  -9.000  -0.5531   0.05269   0.04728  -0.0453   1.0000   0.0467
  -8.750  -0.5605   0.04833   0.04263  -0.0436   1.0000   0.0474
  -8.500  -0.5667   0.04477   0.03877  -0.0407   1.0000   0.0479
  -8.250  -0.5573   0.04064   0.03415  -0.0406   0.9928   0.0483
  -8.000  -0.5326   0.03650   0.02938  -0.0424   0.9807   0.0489
  -7.750  -0.5051   0.03329   0.02553  -0.0438   0.9695   0.0498
  -7.500  -0.4747   0.03108   0.02303  -0.0453   0.9593   0.0513
  -7.250  -0.4448   0.02955   0.02130  -0.0463   0.9476   0.0526
  -7.000  -0.4151   0.02790   0.01937  -0.0470   0.9360   0.0535
  -6.750  -0.3845   0.02639   0.01759  -0.0477   0.9255   0.0545
  -6.500  -0.3542   0.02504   0.01600  -0.0481   0.9150   0.0556
  -6.250  -0.3256   0.02388   0.01461  -0.0482   0.9035   0.0569
  -6.000  -0.2964   0.02292   0.01343  -0.0482   0.8933   0.0589
  -5.750  -0.2680   0.02204   0.01239  -0.0481   0.8834   0.0610
  -5.500  -0.2416   0.02124   0.01157  -0.0478   0.8727   0.0630
  -5.250  -0.2146   0.02053   0.01080  -0.0474   0.8637   0.0651
  -5.000  -0.1885   0.01989   0.01008  -0.0468   0.8539   0.0676
  -4.750  -0.1627   0.01932   0.00941  -0.0461   0.8447   0.0706
  -4.500  -0.1371   0.01872   0.00876  -0.0455   0.8364   0.0744
  -4.250  -0.1117   0.01826   0.00828  -0.0449   0.8273   0.0809
  -4.000  -0.0858   0.01777   0.00779  -0.0442   0.8197   0.0916
  -3.750  -0.0607   0.01730   0.00737  -0.0436   0.8108   0.1087
  -3.500  -0.0350   0.01684   0.00699  -0.0430   0.8036   0.1362
  -3.250  -0.0099   0.01644   0.00678  -0.0425   0.7944   0.1799
  -3.000   0.0153   0.01601   0.00659  -0.0418   0.7863   0.2522
  -2.750   0.0386   0.01544   0.00647  -0.0409   0.7755   0.3565
  -2.500   0.0589   0.01453   0.00629  -0.0393   0.7649   0.5282
  -2.250   0.1082   0.01395   0.00667  -0.0409   0.7541   0.8771
  -2.000   0.1464   0.01413   0.00669  -0.0419   0.7423   0.9307
  -1.750   0.2106   0.01432   0.00667  -0.0484   0.7326   0.9750
  -1.500   0.2768   0.01424   0.00636  -0.0561   0.7237   1.0000
  -1.250   0.3016   0.01426   0.00627  -0.0557   0.7136   1.0000
  -1.000   0.3262   0.01428   0.00615  -0.0550   0.7047   1.0000
  -0.750   0.3507   0.01431   0.00609  -0.0544   0.6947   1.0000
  -0.500   0.3751   0.01435   0.00604  -0.0538   0.6850   1.0000
  -0.250   0.3995   0.01439   0.00596  -0.0531   0.6758   1.0000
   0.000   0.4238   0.01444   0.00597  -0.0526   0.6647   1.0000
   0.250   0.4479   0.01450   0.00594  -0.0519   0.6541   1.0000
   0.500   0.4720   0.01454   0.00590  -0.0511   0.6439   1.0000
   0.750   0.4960   0.01461   0.00594  -0.0505   0.6318   1.0000
   1.000   0.5199   0.01469   0.00598  -0.0498   0.6201   1.0000
   1.250   0.5437   0.01476   0.00600  -0.0490   0.6080   1.0000
   1.500   0.5673   0.01484   0.00601  -0.0482   0.5953   1.0000
   1.750   0.5908   0.01493   0.00606  -0.0474   0.5819   1.0000
   2.000   0.6142   0.01504   0.00613  -0.0466   0.5678   1.0000
   2.250   0.6375   0.01517   0.00622  -0.0458   0.5535   1.0000
   2.500   0.6606   0.01532   0.00633  -0.0449   0.5387   1.0000
   2.750   0.6835   0.01549   0.00645  -0.0440   0.5234   1.0000
   3.000   0.7063   0.01568   0.00660  -0.0432   0.5082   1.0000
   3.250   0.7290   0.01590   0.00678  -0.0423   0.4936   1.0000
   3.500   0.7516   0.01614   0.00698  -0.0414   0.4792   1.0000
   3.750   0.7740   0.01641   0.00721  -0.0406   0.4652   1.0000
   4.000   0.7963   0.01669   0.00745  -0.0397   0.4518   1.0000
   4.250   0.8183   0.01699   0.00772  -0.0388   0.4382   1.0000
   4.500   0.8400   0.01731   0.00799  -0.0378   0.4249   1.0000
   4.750   0.8617   0.01765   0.00829  -0.0369   0.4123   1.0000
   5.000   0.8834   0.01800   0.00866  -0.0360   0.4004   1.0000
   5.250   0.9047   0.01837   0.00902  -0.0351   0.3880   1.0000
   5.500   0.9255   0.01875   0.00938  -0.0341   0.3747   1.0000
   5.750   0.9461   0.01916   0.00976  -0.0331   0.3618   1.0000
   6.000   0.9667   0.01959   0.01016  -0.0322   0.3498   1.0000
   6.250   0.9876   0.02000   0.01065  -0.0313   0.3386   1.0000
   6.500   1.0084   0.02045   0.01114  -0.0305   0.3282   1.0000
   6.750   1.0287   0.02093   0.01162  -0.0295   0.3179   1.0000
   7.000   1.0490   0.02138   0.01220  -0.0286   0.3066   1.0000
   7.250   1.0688   0.02186   0.01276  -0.0277   0.2955   1.0000
   7.500   1.0878   0.02237   0.01333  -0.0267   0.2836   1.0000
   7.750   1.1059   0.02289   0.01393  -0.0256   0.2706   1.0000
   8.000   1.1234   0.02343   0.01457  -0.0244   0.2564   1.0000
   8.250   1.1400   0.02401   0.01524  -0.0232   0.2414   1.0000
   8.500   1.1556   0.02465   0.01596  -0.0219   0.2249   1.0000
   8.750   1.1689   0.02540   0.01673  -0.0203   0.2061   1.0000
   9.000   1.1791   0.02631   0.01761  -0.0185   0.1879   1.0000
   9.250   1.1870   0.02737   0.01860  -0.0165   0.1723   1.0000
   9.500   1.1927   0.02849   0.01970  -0.0142   0.1590   1.0000
   9.750   1.1988   0.02971   0.02093  -0.0122   0.1478   1.0000
  10.000   1.2043   0.03105   0.02229  -0.0105   0.1386   1.0000
  10.250   1.2098   0.03249   0.02378  -0.0090   0.1301   1.0000
  10.500   1.2164   0.03396   0.02534  -0.0078   0.1231   1.0000
  10.750   1.2205   0.03568   0.02714  -0.0068   0.1161   1.0000
  11.000   1.2256   0.03743   0.02900  -0.0060   0.1088   1.0000
  11.250   1.2267   0.03959   0.03121  -0.0054   0.1019   1.0000
  11.500   1.2305   0.04165   0.03341  -0.0049   0.0944   1.0000
  11.750   1.2288   0.04430   0.03609  -0.0047   0.0874   1.0000
  12.000   1.2292   0.04688   0.03881  -0.0046   0.0797   1.0000
  12.250   1.2269   0.04984   0.04187  -0.0047   0.0735   1.0000
  12.500   1.2231   0.05309   0.04524  -0.0050   0.0663   1.0000
  12.750   1.2185   0.05657   0.04884  -0.0055   0.0589   1.0000
  13.000   1.2098   0.06068   0.05306  -0.0063   0.0525   1.0000
  13.250   1.2001   0.06509   0.05755  -0.0073   0.0466   1.0000
  13.500   1.1889   0.06986   0.06241  -0.0086   0.0424   1.0000
  13.750   1.1769   0.07500   0.06764  -0.0101   0.0391   1.0000
  14.000   1.1639   0.08049   0.07320  -0.0120   0.0369   1.0000
  14.250   1.1525   0.08587   0.07870  -0.0138   0.0348   1.0000
  14.500   1.1407   0.09147   0.08440  -0.0158   0.0333   1.0000
  14.750   1.1286   0.09723   0.09025  -0.0180   0.0320   1.0000
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