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NACA 1-H-15 AIRFOIL (n1h15-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 1-H-15 AIRFOIL (n1h15-il)
Reynolds number: 500,000
Max Cl/Cd: 103.65 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n1h15-il-500000.txt
Download as CSV file: xf-n1h15-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 1-H-15 AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2454   0.09090   0.08791  -0.0560   0.7196   0.0300
  -9.250  -0.2529   0.08620   0.08325  -0.0603   0.7183   0.0301
  -9.000  -0.2591   0.08179   0.07886  -0.0643   0.7170   0.0301
  -8.750  -0.2697   0.07731   0.07435  -0.0675   0.7158   0.0302
  -8.500  -0.2723   0.07380   0.07086  -0.0664   0.7149   0.0305
  -8.250  -0.2731   0.07160   0.06864  -0.0656   0.7139   0.0307
  -8.000  -0.2716   0.06896   0.06595  -0.0658   0.7131   0.0309
  -7.750  -0.2669   0.06659   0.06354  -0.0658   0.7122   0.0313
  -7.500  -0.2628   0.06393   0.06082  -0.0662   0.7112   0.0316
  -7.250  -0.2547   0.06112   0.05799  -0.0674   0.7096   0.0321
  -7.000  -0.2454   0.05817   0.05500  -0.0686   0.7075   0.0329
  -6.750  -0.2458   0.05168   0.04796  -0.0692   0.7053   0.0359
  -6.500  -0.2419   0.04696   0.04320  -0.0688   0.7038   0.0365
  -6.250  -0.2266   0.04514   0.04135  -0.0684   0.7025   0.0369
  -6.000  -0.2105   0.04349   0.03963  -0.0678   0.7015   0.0373
  -5.750  -0.1943   0.04173   0.03778  -0.0670   0.7005   0.0380
  -5.500  -0.1779   0.03984   0.03575  -0.0661   0.6997   0.0391
  -5.250  -0.1605   0.03843   0.03371  -0.0633   0.6989   0.0427
  -5.000  -0.1519   0.03375   0.02892  -0.0619   0.6982   0.0439
  -4.750  -0.1314   0.03253   0.02767  -0.0614   0.6975   0.0447
  -4.500  -0.1106   0.03145   0.02653  -0.0607   0.6968   0.0457
  -4.250  -0.0866   0.03063   0.02560  -0.0611   0.6942   0.0481
  -4.000  -0.0671   0.02902   0.02361  -0.0602   0.6905   0.0524
  -3.750  -0.0438   0.02793   0.02252  -0.0601   0.6889   0.0535
  -3.500  -0.0204   0.02706   0.02159  -0.0598   0.6877   0.0552
  -3.250   0.0044   0.02672   0.02106  -0.0590   0.6867   0.0592
  -3.000   0.0248   0.02504   0.01915  -0.0579   0.6858   0.0632
  -2.750   0.0513   0.02156   0.01492  -0.0555   0.6851   0.0432
  -2.500   0.0787   0.01999   0.01329  -0.0554   0.6845   0.0413
  -2.250   0.1060   0.01903   0.01222  -0.0552   0.6840   0.0409
  -2.000   0.1334   0.01826   0.01136  -0.0550   0.6834   0.0406
  -1.750   0.1605   0.01765   0.01069  -0.0548   0.6828   0.0408
  -1.500   0.1872   0.01713   0.01012  -0.0545   0.6822   0.0409
  -1.250   0.2111   0.01865   0.01178  -0.0569   0.6739   0.0414
  -1.000   0.2369   0.01844   0.01155  -0.0567   0.6728   0.0421
  -0.750   0.2624   0.01821   0.01130  -0.0564   0.6718   0.0427
  -0.500   0.2870   0.01775   0.01083  -0.0558   0.6711   0.0432
  -0.250   0.3114   0.01731   0.01038  -0.0550   0.6704   0.0442
   0.000   0.3124   0.02029   0.01345  -0.0547   0.6589   0.0450
   0.250   0.3361   0.02015   0.01332  -0.0541   0.6578   0.0466
   0.500   0.3617   0.01991   0.01308  -0.0536   0.6573   0.0483
   0.750   0.3879   0.01966   0.01282  -0.0532   0.6567   0.0504
   1.000   0.4140   0.01938   0.01256  -0.0528   0.6562   0.0557
   1.250   0.4400   0.01909   0.01234  -0.0524   0.6557   0.0745
   1.500   0.4318   0.01707   0.01216  -0.0455   0.6548   0.6904
   1.750   0.7365   0.01397   0.00961  -0.0975   0.6688   1.0000
   2.000   0.7607   0.01390   0.00951  -0.0969   0.6681   1.0000
   2.250   0.7849   0.01386   0.00944  -0.0963   0.6674   1.0000
   2.500   0.8125   0.01625   0.01200  -0.1002   0.6592   1.0000
   2.750   0.8365   0.01637   0.01212  -0.1000   0.6578   1.0000
   3.000   0.8607   0.01631   0.01206  -0.0995   0.6569   1.0000
   3.250   0.8850   0.01619   0.01193  -0.0989   0.6561   1.0000
   3.500   0.9111   0.01536   0.01106  -0.0977   0.6557   1.0000
   3.750   0.9367   0.01474   0.01042  -0.0968   0.6551   1.0000
   4.000   0.9624   0.01407   0.00972  -0.0957   0.6542   1.0000
   4.250   0.9879   0.01344   0.00904  -0.0946   0.6533   1.0000
   4.500   1.0128   0.01429   0.01001  -0.0958   0.6487   1.0000
   4.750   1.0382   0.01439   0.01015  -0.0960   0.6451   1.0000
   5.000   1.0656   0.01362   0.00937  -0.0952   0.6429   1.0000
   5.250   1.0922   0.01300   0.00873  -0.0945   0.6411   1.0000
   5.500   1.1188   0.01198   0.00763  -0.0931   0.6384   1.0000
   5.750   1.1475   0.01210   0.00787  -0.0943   0.6293   1.0000
   6.000   1.1744   0.01133   0.00703  -0.0934   0.6238   1.0000
   6.250   1.2047   0.01181   0.00763  -0.0956   0.6127   1.0000
   6.500   1.2326   0.01219   0.00807  -0.0970   0.5992   1.0000
   6.750   1.2562   0.01272   0.00857  -0.0976   0.5782   1.0000
   7.000   1.2629   0.01401   0.00972  -0.0960   0.5383   1.0000
   7.250   1.2389   0.01559   0.01113  -0.0885   0.5066   1.0000
   7.500   1.2074   0.01698   0.01239  -0.0792   0.4833   1.0000
   7.750   1.1747   0.01902   0.01422  -0.0707   0.4481   1.0000
   8.000   1.1438   0.02153   0.01647  -0.0633   0.4060   1.0000
   8.250   1.1124   0.02448   0.01913  -0.0565   0.3555   1.0000
   8.500   1.0798   0.02786   0.02212  -0.0501   0.2906   1.0000
   9.000   1.0335   0.03408   0.02748  -0.0405   0.1464   1.0000
   9.250   1.0216   0.03664   0.02963  -0.0370   0.0839   1.0000
   9.500   1.0233   0.03835   0.03119  -0.0348   0.0625   1.0000
   9.750   1.0322   0.03956   0.03237  -0.0333   0.0559   1.0000
  10.000   1.0403   0.04086   0.03365  -0.0318   0.0515   1.0000
  10.250   1.0496   0.04211   0.03493  -0.0304   0.0492   1.0000
  10.500   1.0605   0.04326   0.03612  -0.0292   0.0475   1.0000
  10.750   1.0711   0.04443   0.03731  -0.0280   0.0458   1.0000
  11.000   1.0802   0.04572   0.03862  -0.0268   0.0441   1.0000
  11.250   1.0867   0.04727   0.04018  -0.0253   0.0425   1.0000
  11.500   1.0922   0.04892   0.04187  -0.0239   0.0413   1.0000
  11.750   1.1036   0.05009   0.04309  -0.0229   0.0404   1.0000
  12.000   1.1141   0.05133   0.04438  -0.0219   0.0394   1.0000
  12.250   1.1243   0.05262   0.04571  -0.0208   0.0384   1.0000
  12.500   1.1339   0.05398   0.04709  -0.0199   0.0372   1.0000
  12.750   1.1425   0.05542   0.04856  -0.0188   0.0362   1.0000
  13.000   1.1495   0.05694   0.05009  -0.0176   0.0352   1.0000
  13.250   1.1564   0.05837   0.05155  -0.0162   0.0341   1.0000
  13.500   1.1684   0.05956   0.05280  -0.0155   0.0334   1.0000
  13.750   1.1793   0.06081   0.05410  -0.0146   0.0326   1.0000
  14.000   1.1901   0.06209   0.05543  -0.0138   0.0317   1.0000
  14.250   1.2008   0.06335   0.05673  -0.0130   0.0309   1.0000
  14.500   1.2114   0.06461   0.05801  -0.0122   0.0301   1.0000
  14.750   1.2218   0.06579   0.05917  -0.0113   0.0292   1.0000
  15.000   1.2345   0.06650   0.05991  -0.0100   0.0281   1.0000
  15.250   1.2454   0.06784   0.06134  -0.0093   0.0276   1.0000
  15.500   1.2559   0.06921   0.06279  -0.0087   0.0268   1.0000
  15.750   1.2658   0.07065   0.06430  -0.0081   0.0260   1.0000
  16.000   1.2755   0.07210   0.06581  -0.0075   0.0254   1.0000
  16.250   1.2845   0.07361   0.06736  -0.0069   0.0247   1.0000
  16.500   1.2936   0.07513   0.06889  -0.0064   0.0242   1.0000
  16.750   1.3093   0.07543   0.06919  -0.0051   0.0232   1.0000
  17.000   1.3146   0.07755   0.07144  -0.0047   0.0228   1.0000
  17.250   1.3211   0.07947   0.07349  -0.0042   0.0223   1.0000
  17.500   1.3268   0.08151   0.07564  -0.0038   0.0217   1.0000
  17.750   1.3324   0.08352   0.07775  -0.0034   0.0212   1.0000
  18.000   1.3372   0.08566   0.07998  -0.0031   0.0207   1.0000
  18.250   1.3415   0.08788   0.08228  -0.0029   0.0203   1.0000
  18.500   1.3455   0.09018   0.08464  -0.0028   0.0200   1.0000
  18.750   1.3505   0.09228   0.08676  -0.0027   0.0195   1.0000
  19.000   1.3558   0.09409   0.08865  -0.0018   0.0189   1.0000
  19.250   1.3536   0.09731   0.09204  -0.0019   0.0188   1.0000
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