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HQ 1.0/9 AIRFOIL (hq109-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.0/9 AIRFOIL (hq109-il)
Reynolds number: 500,000
Max Cl/Cd: 66.11 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq109-il-500000-n5.txt
Download as CSV file: xf-hq109-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/9 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5910   0.10026   0.09798  -0.0069   1.0000   0.0047
 -10.500  -0.5974   0.09413   0.09190  -0.0099   1.0000   0.0046
 -10.000  -0.7846   0.04367   0.04114  -0.0389   1.0000   0.0033
  -9.750  -0.7892   0.04031   0.03758  -0.0386   1.0000   0.0034
  -9.500  -0.7951   0.03587   0.03280  -0.0378   1.0000   0.0035
  -9.250  -0.7921   0.03232   0.02892  -0.0368   1.0000   0.0035
  -9.000  -0.7756   0.03117   0.02766  -0.0363   1.0000   0.0037
  -8.750  -0.7596   0.02971   0.02603  -0.0357   1.0000   0.0039
  -8.500  -0.7467   0.02722   0.02323  -0.0346   1.0000   0.0041
  -8.250  -0.7326   0.02472   0.02038  -0.0335   1.0000   0.0043
  -8.000  -0.7168   0.02243   0.01776  -0.0322   1.0000   0.0044
  -7.750  -0.6995   0.02041   0.01543  -0.0309   1.0000   0.0045
  -7.500  -0.6810   0.01878   0.01355  -0.0297   1.0000   0.0047
  -7.250  -0.6617   0.01745   0.01201  -0.0284   1.0000   0.0049
  -7.000  -0.6419   0.01632   0.01071  -0.0271   1.0000   0.0052
  -6.750  -0.6127   0.01529   0.00949  -0.0278   0.9953   0.0055
  -6.500  -0.5822   0.01421   0.00824  -0.0288   0.9892   0.0059
  -6.250  -0.5508   0.01314   0.00705  -0.0300   0.9833   0.0068
  -6.000  -0.5193   0.01253   0.00636  -0.0311   0.9760   0.0076
  -5.750  -0.4871   0.01203   0.00580  -0.0323   0.9686   0.0089
  -5.500  -0.4551   0.01158   0.00528  -0.0333   0.9599   0.0100
  -5.250  -0.4250   0.01093   0.00453  -0.0340   0.9491   0.0124
  -5.000  -0.3952   0.01054   0.00406  -0.0345   0.9374   0.0152
  -4.750  -0.3668   0.01015   0.00368  -0.0346   0.9248   0.0228
  -4.500  -0.3394   0.00986   0.00336  -0.0346   0.9126   0.0324
  -4.250  -0.3125   0.00963   0.00309  -0.0344   0.9012   0.0403
  -3.750  -0.2599   0.00914   0.00259  -0.0338   0.8789   0.0691
  -3.500  -0.2339   0.00883   0.00236  -0.0335   0.8685   0.0998
  -3.250  -0.2077   0.00854   0.00215  -0.0333   0.8589   0.1354
  -3.000  -0.1815   0.00827   0.00197  -0.0331   0.8493   0.1768
  -2.750  -0.1550   0.00803   0.00181  -0.0329   0.8395   0.2151
  -2.500  -0.1290   0.00769   0.00161  -0.0327   0.8295   0.2734
  -2.250  -0.1045   0.00710   0.00144  -0.0324   0.8192   0.4010
  -2.000  -0.0790   0.00675   0.00134  -0.0320   0.8084   0.4876
  -1.750  -0.0523   0.00659   0.00128  -0.0318   0.7983   0.5334
  -1.500  -0.0260   0.00642   0.00124  -0.0314   0.7896   0.5900
  -1.250   0.0008   0.00633   0.00123  -0.0311   0.7813   0.6285
  -1.000   0.0280   0.00629   0.00121  -0.0309   0.7706   0.6527
  -0.750   0.0550   0.00626   0.00118  -0.0306   0.7574   0.6723
  -0.500   0.0821   0.00626   0.00116  -0.0303   0.7441   0.6887
  -0.250   0.1094   0.00626   0.00115  -0.0301   0.7324   0.7029
   0.000   0.1367   0.00626   0.00114  -0.0299   0.7187   0.7166
   0.250   0.1638   0.00628   0.00114  -0.0297   0.7037   0.7307
   0.500   0.1910   0.00629   0.00116  -0.0294   0.6909   0.7449
   0.750   0.2182   0.00631   0.00118  -0.0292   0.6776   0.7572
   1.000   0.2455   0.00635   0.00119  -0.0290   0.6617   0.7674
   1.250   0.2726   0.00640   0.00122  -0.0288   0.6452   0.7776
   1.750   0.3265   0.00651   0.00132  -0.0283   0.6076   0.7988
   2.000   0.3529   0.00661   0.00137  -0.0280   0.5806   0.8104
   2.250   0.3788   0.00675   0.00143  -0.0275   0.5455   0.8227
   2.500   0.4043   0.00693   0.00154  -0.0270   0.5053   0.8359
   2.750   0.4289   0.00720   0.00166  -0.0264   0.4523   0.8500
   3.000   0.4526   0.00755   0.00182  -0.0257   0.3893   0.8661
   3.250   0.4765   0.00787   0.00199  -0.0250   0.3315   0.8863
   3.750   0.5326   0.00845   0.00242  -0.0253   0.2528   0.9482
   4.000   0.5697   0.00876   0.00264  -0.0276   0.2202   0.9861
   4.250   0.5983   0.00905   0.00286  -0.0280   0.1968   1.0000
   4.500   0.6231   0.00944   0.00310  -0.0277   0.1606   1.0000
   4.750   0.6475   0.00989   0.00340  -0.0273   0.1220   1.0000
   5.000   0.6724   0.01029   0.00370  -0.0269   0.0968   1.0000
   5.250   0.6970   0.01073   0.00404  -0.0265   0.0729   1.0000
   5.500   0.7215   0.01120   0.00440  -0.0261   0.0525   1.0000
   5.750   0.7463   0.01161   0.00476  -0.0257   0.0390   1.0000
   6.000   0.7712   0.01201   0.00514  -0.0254   0.0297   1.0000
   6.250   0.7958   0.01246   0.00559  -0.0249   0.0209   1.0000
   6.500   0.8201   0.01294   0.00605  -0.0245   0.0144   1.0000
   6.750   0.8441   0.01346   0.00657  -0.0240   0.0092   1.0000
   7.000   0.8678   0.01403   0.00718  -0.0234   0.0067   1.0000
   7.250   0.8915   0.01459   0.00781  -0.0228   0.0055   1.0000
   7.500   0.9143   0.01530   0.00858  -0.0221   0.0047   1.0000
   7.750   0.9363   0.01611   0.00951  -0.0213   0.0042   1.0000
   8.000   0.9583   0.01687   0.01039  -0.0205   0.0040   1.0000
   8.250   0.9795   0.01774   0.01141  -0.0196   0.0038   1.0000
   8.500   0.9999   0.01869   0.01250  -0.0186   0.0037   1.0000
   8.750   1.0193   0.01976   0.01370  -0.0175   0.0035   1.0000
   9.000   1.0376   0.02095   0.01505  -0.0163   0.0034   1.0000
   9.250   1.0551   0.02223   0.01650  -0.0151   0.0033   1.0000
   9.500   1.0712   0.02367   0.01812  -0.0137   0.0033   1.0000
   9.750   1.0866   0.02512   0.01976  -0.0123   0.0032   1.0000
  10.000   1.1007   0.02663   0.02145  -0.0108   0.0031   1.0000
  10.250   1.1142   0.02802   0.02301  -0.0093   0.0029   1.0000
  10.500   1.1265   0.02936   0.02450  -0.0078   0.0028   1.0000
  10.750   1.1376   0.03061   0.02587  -0.0063   0.0026   1.0000
  11.000   1.1407   0.03232   0.02780  -0.0037   0.0026   1.0000
  11.250   1.1380   0.03429   0.02996  -0.0008   0.0025   1.0000
  11.500   1.1318   0.03670   0.03258   0.0017   0.0025   1.0000
  11.750   1.1236   0.03944   0.03553   0.0035   0.0024   1.0000
  12.000   1.1103   0.04303   0.03935   0.0045   0.0023   1.0000
  12.250   1.0987   0.04685   0.04337   0.0044   0.0024   1.0000
  12.500   1.0867   0.05117   0.04788   0.0033   0.0024   1.0000
  12.750   1.0682   0.05704   0.05396   0.0006   0.0023   1.0000
  13.000   1.0533   0.06324   0.06033  -0.0030   0.0024   1.0000
  13.250   1.0396   0.07013   0.06737  -0.0076   0.0024   1.0000
  13.500   1.0215   0.07894   0.07635  -0.0137   0.0024   1.0000
  13.750   1.0041   0.08840   0.08595  -0.0198   0.0024   1.0000
  14.000   0.9678   0.10302   0.10078  -0.0282   0.0026   1.0000
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