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HQ 1.5/9 AIRFOIL (hq159-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.5/9 AIRFOIL (hq159-il)
Reynolds number: 500,000
Max Cl/Cd: 88.43 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq159-il-500000.txt
Download as CSV file: xf-hq159-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/9 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5062   0.08296   0.08076  -0.0250   1.0000   0.0174
  -8.750  -0.5097   0.07800   0.07583  -0.0281   1.0000   0.0178
  -8.500  -0.5153   0.07281   0.07068  -0.0318   1.0000   0.0177
  -8.250  -0.5311   0.06626   0.06416  -0.0384   1.0000   0.0174
  -8.000  -0.5410   0.06061   0.05843  -0.0422   1.0000   0.0173
  -7.750  -0.5456   0.05544   0.05315  -0.0441   1.0000   0.0179
  -6.500  -0.5438   0.02661   0.02256  -0.0382   0.9976   0.0120
  -6.250  -0.5142   0.02097   0.01620  -0.0399   0.9940   0.0114
  -6.000  -0.4827   0.01840   0.01325  -0.0410   0.9901   0.0119
  -5.750  -0.4494   0.01644   0.01100  -0.0423   0.9866   0.0123
  -5.500  -0.4129   0.01584   0.01026  -0.0442   0.9839   0.0132
  -5.250  -0.3802   0.01356   0.00773  -0.0455   0.9811   0.0140
  -5.000  -0.3491   0.01207   0.00609  -0.0464   0.9759   0.0153
  -4.750  -0.3141   0.01130   0.00526  -0.0480   0.9722   0.0173
  -4.500  -0.2783   0.01072   0.00461  -0.0497   0.9689   0.0202
  -4.250  -0.2484   0.01004   0.00390  -0.0502   0.9612   0.0296
  -4.000  -0.2160   0.00946   0.00337  -0.0512   0.9557   0.0507
  -3.750  -0.1876   0.00915   0.00305  -0.0514   0.9467   0.0662
  -3.500  -0.1590   0.00874   0.00275  -0.0516   0.9391   0.0972
  -3.250  -0.1340   0.00806   0.00246  -0.0514   0.9294   0.1965
  -3.000  -0.1103   0.00728   0.00218  -0.0509   0.9196   0.3413
  -2.750  -0.0866   0.00664   0.00203  -0.0503   0.9106   0.4925
  -2.500  -0.0614   0.00640   0.00196  -0.0497   0.9013   0.5668
  -2.250  -0.0354   0.00629   0.00191  -0.0491   0.8913   0.6088
  -2.000  -0.0090   0.00624   0.00186  -0.0486   0.8820   0.6389
  -1.750   0.0173   0.00619   0.00182  -0.0480   0.8730   0.6670
  -1.500   0.0438   0.00616   0.00180  -0.0476   0.8637   0.6932
  -1.250   0.0704   0.00615   0.00178  -0.0471   0.8547   0.7136
  -1.000   0.0964   0.00614   0.00177  -0.0464   0.8445   0.7375
  -0.750   0.1227   0.00612   0.00175  -0.0458   0.8330   0.7552
  -0.500   0.1493   0.00610   0.00173  -0.0454   0.8221   0.7697
  -0.250   0.1759   0.00610   0.00171  -0.0449   0.8119   0.7841
   0.000   0.2025   0.00609   0.00169  -0.0444   0.8015   0.7990
   0.250   0.2289   0.00607   0.00168  -0.0439   0.7901   0.8133
   0.500   0.2556   0.00605   0.00166  -0.0435   0.7786   0.8254
   0.750   0.2824   0.00603   0.00166  -0.0432   0.7680   0.8373
   1.000   0.3090   0.00602   0.00165  -0.0427   0.7573   0.8501
   1.250   0.3353   0.00600   0.00165  -0.0422   0.7462   0.8644
   1.500   0.3613   0.00597   0.00166  -0.0417   0.7341   0.8812
   1.750   0.3871   0.00593   0.00167  -0.0410   0.7212   0.9022
   2.000   0.4153   0.00590   0.00169  -0.0408   0.7073   0.9310
   2.250   0.4532   0.00592   0.00171  -0.0429   0.6912   0.9652
   2.500   0.4947   0.00597   0.00175  -0.0460   0.6695   0.9997
   2.750   0.5202   0.00609   0.00179  -0.0455   0.6457   1.0000
   3.000   0.5456   0.00624   0.00185  -0.0451   0.6169   1.0000
   3.250   0.5704   0.00645   0.00192  -0.0445   0.5775   1.0000
   3.500   0.5944   0.00677   0.00204  -0.0437   0.5244   1.0000
   3.750   0.6176   0.00720   0.00221  -0.0430   0.4606   1.0000
   4.000   0.6409   0.00768   0.00243  -0.0423   0.3984   1.0000
   4.250   0.6646   0.00816   0.00268  -0.0417   0.3408   1.0000
   4.500   0.6884   0.00865   0.00297  -0.0412   0.2925   1.0000
   4.750   0.7126   0.00911   0.00326  -0.0407   0.2542   1.0000
   5.000   0.7371   0.00952   0.00355  -0.0403   0.2214   1.0000
   5.250   0.7619   0.00992   0.00383  -0.0399   0.1880   1.0000
   5.500   0.7857   0.01043   0.00416  -0.0394   0.1456   1.0000
   5.750   0.8080   0.01114   0.00461  -0.0387   0.0973   1.0000
   6.000   0.8309   0.01179   0.00512  -0.0381   0.0680   1.0000
   6.250   0.8544   0.01235   0.00561  -0.0375   0.0529   1.0000
   6.500   0.8787   0.01279   0.00606  -0.0370   0.0446   1.0000
   6.750   0.9027   0.01326   0.00652  -0.0365   0.0369   1.0000
   7.000   0.9269   0.01370   0.00695  -0.0361   0.0306   1.0000
   7.250   0.9512   0.01412   0.00742  -0.0356   0.0244   1.0000
   7.500   0.9706   0.01525   0.00851  -0.0343   0.0120   1.0000
   7.750   0.9931   0.01592   0.00928  -0.0334   0.0102   1.0000
   8.000   1.0144   0.01673   0.01017  -0.0325   0.0092   1.0000
   8.250   1.0344   0.01768   0.01122  -0.0313   0.0085   1.0000
   8.500   1.0518   0.01894   0.01261  -0.0298   0.0080   1.0000
   8.750   1.0657   0.02071   0.01455  -0.0278   0.0077   1.0000
   9.000   1.0778   0.02293   0.01700  -0.0257   0.0073   1.0000
   9.250   1.0974   0.02381   0.01801  -0.0247   0.0071   1.0000
   9.500   1.1151   0.02494   0.01929  -0.0234   0.0068   1.0000
   9.750   1.1297   0.02656   0.02114  -0.0218   0.0066   1.0000
  10.000   1.1420   0.02843   0.02322  -0.0200   0.0064   1.0000
  10.250   1.1513   0.03057   0.02561  -0.0179   0.0063   1.0000
  10.500   1.1568   0.03292   0.02823  -0.0155   0.0062   1.0000
  10.750   1.1565   0.03524   0.03080  -0.0124   0.0061   1.0000
  11.000   1.1528   0.03745   0.03323  -0.0092   0.0060   1.0000
  11.250   1.1407   0.04066   0.03671  -0.0060   0.0061   1.0000
  11.500   1.1295   0.04372   0.04001  -0.0038   0.0060   1.0000
  11.750   1.1180   0.04699   0.04349  -0.0025   0.0058   1.0000
  12.000   1.0964   0.05197   0.04873  -0.0023   0.0060   1.0000
  12.250   1.0802   0.05668   0.05363  -0.0033   0.0059   1.0000
  12.500   1.0613   0.06243   0.05959  -0.0057   0.0059   1.0000
  12.750   1.0420   0.06910   0.06643  -0.0095   0.0059   1.0000
  13.000   1.0190   0.07763   0.07514  -0.0151   0.0060   1.0000
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