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HT22 (ht22-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HT22 (ht22-il)
Reynolds number: 500,000
Max Cl/Cd: 63.19 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ht22-il-500000-n5.txt
Download as CSV file: xf-ht22-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HT22                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.6856   0.11242   0.11017   0.0445   1.0001   0.0073
  -9.000  -0.6825   0.10860   0.10636   0.0429   1.0001   0.0072
  -8.750  -0.6801   0.10453   0.10230   0.0410   1.0001   0.0070
  -8.500  -0.6781   0.10032   0.09811   0.0389   1.0001   0.0069
  -8.250  -0.6767   0.09597   0.09378   0.0364   1.0001   0.0068
  -8.000  -0.6755   0.09149   0.08932   0.0336   1.0001   0.0068
  -7.750  -0.6739   0.08662   0.08447   0.0294   1.0001   0.0067
  -7.500  -0.6666   0.08072   0.07857   0.0228   1.0001   0.0067
  -7.250  -0.6561   0.07407   0.07190   0.0152   1.0001   0.0067
  -7.000  -0.6423   0.06654   0.06430   0.0073   1.0001   0.0068
  -6.750  -0.6257   0.05833   0.05595  -0.0001   1.0001   0.0070
  -6.500  -0.6070   0.04952   0.04691  -0.0062   1.0001   0.0071
  -6.250  -0.5875   0.03763   0.03452  -0.0112   1.0001   0.0074
  -6.000  -0.5723   0.02058   0.01594  -0.0135   1.0001   0.0079
  -5.750  -0.5470   0.01834   0.01333  -0.0134   1.0001   0.0082
  -5.500  -0.5209   0.01683   0.01156  -0.0133   1.0001   0.0085
  -5.250  -0.4944   0.01548   0.00996  -0.0131   1.0001   0.0089
  -5.000  -0.4677   0.01427   0.00851  -0.0128   1.0001   0.0095
  -4.750  -0.4407   0.01323   0.00728  -0.0125   1.0001   0.0100
  -4.500  -0.4136   0.01242   0.00631  -0.0123   1.0001   0.0105
  -4.250  -0.3866   0.01158   0.00536  -0.0121   1.0001   0.0111
  -4.000  -0.3593   0.01117   0.00494  -0.0119   1.0001   0.0121
  -3.750  -0.3319   0.01076   0.00449  -0.0117   1.0001   0.0131
  -3.500  -0.3044   0.01024   0.00391  -0.0115   1.0001   0.0141
  -3.250  -0.2769   0.00976   0.00338  -0.0113   1.0001   0.0150
  -3.000  -0.2493   0.00931   0.00292  -0.0112   1.0001   0.0166
  -2.750  -0.2217   0.00903   0.00264  -0.0110   1.0001   0.0187
  -2.500  -0.1940   0.00872   0.00232  -0.0108   1.0001   0.0214
  -2.250  -0.1662   0.00844   0.00206  -0.0107   1.0001   0.0247
  -2.000  -0.1385   0.00821   0.00182  -0.0105   1.0001   0.0287
  -1.750  -0.1108   0.00799   0.00165  -0.0104   1.0001   0.0359
  -1.500  -0.0797   0.00778   0.00149  -0.0110   0.9803   0.0469
  -1.250  -0.0448   0.00763   0.00134  -0.0122   0.9015   0.0694
  -1.000  -0.0229   0.00770   0.00123  -0.0104   0.8077   0.1029
  -0.750   0.0017   0.00770   0.00113  -0.0096   0.7200   0.1724
  -0.500   0.0277   0.00750   0.00105  -0.0093   0.6444   0.2987
  -0.250   0.0539   0.00712   0.00100  -0.0093   0.5815   0.4794
   0.000   0.0793   0.00663   0.00099  -0.0089   0.5305   0.6769
   0.250   0.0982   0.00608   0.00100  -0.0064   0.4924   0.8867
   0.500   0.1336   0.00612   0.00097  -0.0078   0.4516   0.9999
   0.750   0.1612   0.00629   0.00097  -0.0076   0.4206   0.9999
   1.250   0.2167   0.00660   0.00101  -0.0074   0.3651   0.9999
   1.500   0.2445   0.00676   0.00104  -0.0073   0.3386   0.9999
   1.750   0.2722   0.00693   0.00110  -0.0072   0.3122   0.9999
   2.000   0.2999   0.00712   0.00116  -0.0071   0.2844   0.9999
   2.250   0.3276   0.00732   0.00123  -0.0070   0.2560   0.9999
   2.500   0.3553   0.00754   0.00132  -0.0069   0.2266   0.9999
   2.750   0.3829   0.00777   0.00145  -0.0068   0.1997   0.9999
   3.000   0.4104   0.00802   0.00158  -0.0068   0.1713   0.9999
   3.250   0.4379   0.00829   0.00173  -0.0067   0.1454   0.9999
   3.500   0.4654   0.00858   0.00190  -0.0066   0.1210   0.9999
   3.750   0.4929   0.00886   0.00211  -0.0065   0.1005   0.9999
   4.000   0.5203   0.00915   0.00232  -0.0065   0.0841   0.9999
   4.250   0.5477   0.00945   0.00255  -0.0064   0.0698   0.9999
   4.500   0.5750   0.00975   0.00282  -0.0063   0.0584   0.9999
   4.750   0.6024   0.01002   0.00308  -0.0062   0.0512   0.9999
   5.000   0.6297   0.01033   0.00338  -0.0060   0.0450   0.9999
   5.250   0.6569   0.01063   0.00369  -0.0059   0.0402   0.9999
   5.500   0.6840   0.01101   0.00408  -0.0058   0.0353   0.9999
   5.750   0.7111   0.01132   0.00444  -0.0056   0.0329   0.9999
   6.000   0.7381   0.01168   0.00483  -0.0055   0.0304   0.9999
   6.250   0.7648   0.01214   0.00531  -0.0053   0.0279   0.9999
   6.500   0.7914   0.01263   0.00588  -0.0051   0.0263   0.9999
   6.750   0.8181   0.01302   0.00634  -0.0050   0.0250   0.9999
   7.000   0.8446   0.01345   0.00683  -0.0048   0.0236   0.9999
   7.250   0.8709   0.01393   0.00737  -0.0046   0.0223   0.9999
   7.500   0.8968   0.01452   0.00803  -0.0044   0.0211   0.9999
   7.750   0.9218   0.01539   0.00899  -0.0042   0.0197   0.9999
   8.000   0.9478   0.01586   0.00957  -0.0040   0.0190   0.9999
   8.250   0.9733   0.01647   0.01028  -0.0037   0.0182   0.9999
   8.500   0.9985   0.01713   0.01106  -0.0035   0.0174   0.9999
   8.750   1.0235   0.01779   0.01183  -0.0032   0.0166   0.9999
   9.000   1.0485   0.01842   0.01254  -0.0030   0.0157   0.9999
   9.250   1.0719   0.01942   0.01363  -0.0028   0.0148   0.9999
   9.500   1.0954   0.02040   0.01476  -0.0025   0.0142   0.9999
   9.750   1.1189   0.02131   0.01585  -0.0021   0.0137   0.9999
  10.000   1.1417   0.02233   0.01706  -0.0018   0.0131   0.9999
  10.250   1.1641   0.02338   0.01828  -0.0015   0.0125   0.9999
  10.500   1.1865   0.02432   0.01936  -0.0012   0.0119   0.9999
  10.750   1.2089   0.02517   0.02032  -0.0010   0.0114   0.9999
  11.000   1.2297   0.02631   0.02157  -0.0007   0.0108   0.9999
  11.250   1.2468   0.02817   0.02364  -0.0004   0.0103   0.9999
  11.500   1.2643   0.02983   0.02555   0.0000   0.0100   0.9999
  11.750   1.2796   0.03178   0.02778   0.0003   0.0097   0.9999
  12.000   1.2925   0.03399   0.03024   0.0005   0.0094   0.9999
  12.250   1.3025   0.03644   0.03294   0.0006   0.0090   0.9999
  12.500   1.3092   0.03917   0.03590   0.0004   0.0088   0.9999
  12.750   1.3111   0.04236   0.03933  -0.0003   0.0086   0.9999
  13.000   1.2965   0.04785   0.04507  -0.0042   0.0085   0.9999
  13.250   1.2447   0.06728   0.06488  -0.0239   0.0089   0.9999
  13.500   1.1810   0.08528   0.08302  -0.0356   0.0094   0.9999
  13.750   1.1173   0.10295   0.10077  -0.0456   0.0099   0.9999
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