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HQ 1.0/9 AIRFOIL (hq109-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.0/9 AIRFOIL (hq109-il)
Reynolds number: 1,000,000
Max Cl/Cd: 82.81 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq109-il-1000000.txt
Download as CSV file: xf-hq109-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.4899   0.15053   0.14902   0.0151   1.0000   0.0071
 -13.500  -0.4892   0.14788   0.14636   0.0133   1.0000   0.0078
  -8.250  -0.7299   0.02545   0.02207  -0.0341   1.0000   0.0059
  -7.750  -0.7016   0.02033   0.01630  -0.0310   1.0000   0.0059
  -7.500  -0.6831   0.01879   0.01454  -0.0296   1.0000   0.0057
  -7.250  -0.6655   0.01707   0.01261  -0.0280   1.0000   0.0057
  -7.000  -0.6473   0.01575   0.01111  -0.0264   1.0000   0.0057
  -6.750  -0.6265   0.01389   0.00904  -0.0255   0.9991   0.0058
  -6.500  -0.5943   0.01244   0.00742  -0.0269   0.9958   0.0063
  -6.250  -0.5609   0.01178   0.00670  -0.0284   0.9923   0.0071
  -6.000  -0.5279   0.01117   0.00602  -0.0298   0.9880   0.0078
  -5.750  -0.4935   0.01056   0.00534  -0.0314   0.9844   0.0084
  -5.500  -0.4599   0.01011   0.00483  -0.0327   0.9792   0.0089
  -5.250  -0.4281   0.00925   0.00382  -0.0337   0.9715   0.0105
  -5.000  -0.3970   0.00887   0.00342  -0.0345   0.9619   0.0132
  -4.750  -0.3681   0.00844   0.00294  -0.0347   0.9498   0.0184
  -4.500  -0.3413   0.00812   0.00264  -0.0345   0.9356   0.0318
  -4.250  -0.3151   0.00790   0.00242  -0.0341   0.9215   0.0427
  -4.000  -0.2890   0.00770   0.00222  -0.0337   0.9085   0.0547
  -3.500  -0.2370   0.00724   0.00182  -0.0330   0.8845   0.1014
  -3.250  -0.2118   0.00681   0.00163  -0.0327   0.8728   0.1719
  -3.000  -0.1858   0.00650   0.00147  -0.0324   0.8616   0.2267
  -2.750  -0.1601   0.00609   0.00129  -0.0322   0.8511   0.3063
  -2.500  -0.1350   0.00560   0.00113  -0.0319   0.8415   0.4187
  -2.250  -0.1090   0.00528   0.00104  -0.0316   0.8324   0.5006
  -2.000  -0.0820   0.00512   0.00099  -0.0315   0.8239   0.5498
  -1.750  -0.0548   0.00503   0.00095  -0.0313   0.8147   0.5844
  -1.500  -0.0277   0.00495   0.00091  -0.0310   0.8037   0.6195
  -1.250  -0.0003   0.00489   0.00088  -0.0309   0.7926   0.6444
  -1.000   0.0272   0.00486   0.00087  -0.0307   0.7825   0.6666
  -0.750   0.0546   0.00484   0.00086  -0.0305   0.7722   0.6880
  -0.500   0.0821   0.00484   0.00084  -0.0304   0.7605   0.7037
  -0.250   0.1098   0.00483   0.00083  -0.0302   0.7488   0.7183
   0.000   0.1375   0.00483   0.00084  -0.0301   0.7383   0.7317
   0.250   0.1652   0.00483   0.00084  -0.0300   0.7270   0.7436
   0.500   0.1928   0.00484   0.00085  -0.0299   0.7154   0.7555
   0.750   0.2204   0.00486   0.00087  -0.0298   0.7033   0.7671
   1.000   0.2479   0.00488   0.00089  -0.0296   0.6906   0.7798
   1.250   0.2753   0.00490   0.00091  -0.0295   0.6766   0.7926
   1.500   0.3027   0.00494   0.00095  -0.0293   0.6598   0.8042
   1.750   0.3299   0.00499   0.00098  -0.0291   0.6403   0.8154
   2.000   0.3569   0.00505   0.00102  -0.0289   0.6197   0.8270
   2.250   0.3835   0.00513   0.00107  -0.0286   0.5923   0.8398
   2.500   0.4092   0.00528   0.00114  -0.0281   0.5486   0.8539
   2.750   0.4348   0.00544   0.00123  -0.0276   0.5093   0.8702
   3.000   0.4595   0.00562   0.00133  -0.0270   0.4652   0.8911
   3.250   0.4829   0.00586   0.00147  -0.0260   0.4089   0.9219
   3.500   0.5133   0.00623   0.00166  -0.0268   0.3376   0.9653
   3.750   0.5519   0.00668   0.00187  -0.0295   0.2773   0.9947
   4.000   0.5795   0.00700   0.00205  -0.0297   0.2431   1.0000
   4.250   0.6047   0.00732   0.00223  -0.0294   0.2099   1.0000
   4.500   0.6302   0.00761   0.00242  -0.0291   0.1814   1.0000
   4.750   0.6555   0.00795   0.00264  -0.0287   0.1481   1.0000
   5.000   0.6798   0.00842   0.00291  -0.0283   0.1078   1.0000
   5.250   0.7043   0.00889   0.00322  -0.0279   0.0762   1.0000
   5.500   0.7295   0.00925   0.00350  -0.0275   0.0582   1.0000
   5.750   0.7548   0.00961   0.00379  -0.0272   0.0441   1.0000
   6.000   0.7798   0.01001   0.00413  -0.0268   0.0308   1.0000
   6.250   0.8047   0.01042   0.00449  -0.0264   0.0208   1.0000
   6.500   0.8287   0.01099   0.00502  -0.0258   0.0114   1.0000
   6.750   0.8534   0.01144   0.00548  -0.0253   0.0085   1.0000
   7.000   0.8767   0.01215   0.00628  -0.0246   0.0068   1.0000
   7.250   0.9012   0.01261   0.00680  -0.0241   0.0063   1.0000
   7.500   0.9252   0.01314   0.00740  -0.0235   0.0056   1.0000
   7.750   0.9486   0.01374   0.00806  -0.0229   0.0050   1.0000
   8.000   0.9694   0.01473   0.00916  -0.0218   0.0046   1.0000
   8.250   0.9889   0.01589   0.01046  -0.0206   0.0044   1.0000
   8.500   1.0051   0.01755   0.01232  -0.0189   0.0043   1.0000
   8.750   1.0226   0.01905   0.01398  -0.0175   0.0042   1.0000
   9.000   1.0393   0.02071   0.01581  -0.0160   0.0042   1.0000
   9.250   1.0547   0.02260   0.01790  -0.0144   0.0042   1.0000
   9.500   1.0666   0.02503   0.02058  -0.0126   0.0042   1.0000
   9.750   1.0781   0.02719   0.02299  -0.0108   0.0041   1.0000
  10.000   1.0951   0.02807   0.02403  -0.0096   0.0040   1.0000
  10.250   1.1050   0.02995   0.02611  -0.0078   0.0040   1.0000
  10.500   1.1076   0.03249   0.02890  -0.0053   0.0040   1.0000
  10.750   1.1005   0.03541   0.03210  -0.0018   0.0040   1.0000
  11.000   1.0811   0.03862   0.03555   0.0026   0.0040   1.0000
  11.250   1.0725   0.04095   0.03804   0.0049   0.0040   1.0000
  11.500   1.0563   0.04443   0.04172   0.0064   0.0040   1.0000
  11.750   1.0312   0.04967   0.04713   0.0064   0.0042   1.0000
  12.000   1.0140   0.05449   0.05211   0.0050   0.0042   1.0000
  12.250   1.0124   0.05770   0.05541   0.0034   0.0042   1.0000
  12.500   0.9878   0.06528   0.06317  -0.0013   0.0042   1.0000
  12.750   0.9729   0.07241   0.07043  -0.0064   0.0042   1.0000
  13.000   0.9632   0.07947   0.07759  -0.0115   0.0042   1.0000
  13.250   0.9505   0.08811   0.08634  -0.0175   0.0043   1.0000
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