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HQ 1.5/11 AIRFOIL (hq1511-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/11 AIRFOIL (hq1511-il)
Reynolds number: 200,000
Max Cl/Cd: 59.94 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1511-il-200000-n5.txt
Download as CSV file: xf-hq1511-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/11 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6675   0.06425   0.06052  -0.0446   1.0000   0.0118
 -11.000  -0.6959   0.05565   0.05174  -0.0516   1.0000   0.0115
 -10.750  -0.7214   0.04962   0.04552  -0.0551   1.0000   0.0115
 -10.500  -0.7428   0.04535   0.04104  -0.0558   1.0000   0.0114
 -10.250  -0.7622   0.04180   0.03723  -0.0539   1.0000   0.0114
 -10.000  -0.7717   0.03820   0.03327  -0.0522   1.0000   0.0115
  -9.750  -0.7736   0.03496   0.02964  -0.0505   1.0000   0.0116
  -9.500  -0.7694   0.03224   0.02657  -0.0487   1.0000   0.0117
  -9.250  -0.7616   0.02984   0.02385  -0.0469   1.0000   0.0118
  -9.000  -0.7512   0.02782   0.02155  -0.0450   1.0000   0.0119
  -8.750  -0.7390   0.02616   0.01965  -0.0432   1.0000   0.0121
  -8.500  -0.7261   0.02467   0.01796  -0.0413   1.0000   0.0123
  -8.250  -0.7131   0.02344   0.01657  -0.0393   1.0000   0.0125
  -8.000  -0.6946   0.02224   0.01527  -0.0385   0.9980   0.0130
  -7.750  -0.6636   0.02109   0.01397  -0.0400   0.9915   0.0135
  -7.500  -0.6319   0.02003   0.01278  -0.0415   0.9855   0.0143
  -7.250  -0.6004   0.01900   0.01159  -0.0428   0.9795   0.0156
  -7.000  -0.5686   0.01802   0.01051  -0.0442   0.9734   0.0172
  -6.750  -0.5366   0.01723   0.00965  -0.0456   0.9675   0.0203
  -6.500  -0.5054   0.01656   0.00893  -0.0467   0.9604   0.0253
  -6.250  -0.4722   0.01606   0.00840  -0.0481   0.9548   0.0321
  -6.000  -0.4422   0.01565   0.00797  -0.0489   0.9466   0.0390
  -5.750  -0.4101   0.01527   0.00748  -0.0500   0.9404   0.0447
  -5.500  -0.3817   0.01480   0.00700  -0.0504   0.9315   0.0502
  -5.250  -0.3520   0.01444   0.00655  -0.0509   0.9239   0.0561
  -5.000  -0.3240   0.01401   0.00613  -0.0512   0.9155   0.0643
  -4.750  -0.2962   0.01364   0.00570  -0.0513   0.9076   0.0738
  -4.500  -0.2685   0.01327   0.00529  -0.0514   0.8998   0.0841
  -4.250  -0.2422   0.01284   0.00489  -0.0512   0.8916   0.1000
  -4.000  -0.2162   0.01231   0.00451  -0.0511   0.8843   0.1349
  -3.750  -0.1915   0.01175   0.00421  -0.0509   0.8765   0.2097
  -3.500  -0.1663   0.01123   0.00391  -0.0506   0.8696   0.2744
  -3.250  -0.1429   0.01062   0.00370  -0.0501   0.8615   0.3739
  -3.000  -0.1183   0.01022   0.00356  -0.0495   0.8542   0.4617
  -2.750  -0.0937   0.00998   0.00353  -0.0487   0.8455   0.5279
  -2.500  -0.0680   0.00988   0.00352  -0.0480   0.8382   0.5811
  -2.250  -0.0422   0.00984   0.00353  -0.0474   0.8292   0.6177
  -2.000  -0.0160   0.00983   0.00352  -0.0467   0.8210   0.6483
  -1.750   0.0102   0.00983   0.00349  -0.0461   0.8115   0.6714
  -1.500   0.0370   0.00982   0.00344  -0.0456   0.8026   0.6852
  -1.250   0.0641   0.00980   0.00337  -0.0452   0.7948   0.6966
  -1.000   0.0909   0.00979   0.00335  -0.0449   0.7864   0.7093
  -0.750   0.1179   0.00979   0.00331  -0.0444   0.7789   0.7224
  -0.500   0.1448   0.00979   0.00328  -0.0441   0.7696   0.7339
  -0.250   0.1717   0.00978   0.00325  -0.0437   0.7616   0.7436
   0.000   0.1987   0.00977   0.00323  -0.0433   0.7527   0.7525
   0.250   0.2258   0.00977   0.00321  -0.0430   0.7433   0.7618
   0.500   0.2525   0.00976   0.00319  -0.0425   0.7335   0.7709
   0.750   0.2792   0.00976   0.00319  -0.0421   0.7225   0.7807
   1.000   0.3059   0.00976   0.00320  -0.0418   0.7123   0.7897
   1.250   0.3327   0.00977   0.00320  -0.0414   0.7025   0.7981
   1.500   0.3596   0.00979   0.00322  -0.0410   0.6912   0.8072
   1.750   0.3859   0.00979   0.00325  -0.0405   0.6787   0.8159
   2.000   0.4123   0.00981   0.00329  -0.0401   0.6661   0.8257
   2.250   0.4385   0.00983   0.00334  -0.0396   0.6531   0.8375
   2.500   0.4644   0.00984   0.00340  -0.0390   0.6395   0.8504
   2.750   0.4903   0.00986   0.00347  -0.0384   0.6243   0.8644
   3.000   0.5164   0.00989   0.00354  -0.0378   0.6070   0.8790
   3.250   0.5430   0.00994   0.00360  -0.0374   0.5869   0.8951
   3.500   0.5710   0.01002   0.00368  -0.0373   0.5605   0.9145
   3.750   0.6014   0.01018   0.00376  -0.0377   0.5220   0.9377
   4.000   0.6336   0.01057   0.00387  -0.0389   0.4630   0.9674
   4.250   0.6621   0.01106   0.00410  -0.0394   0.4112   1.0000
   4.500   0.6847   0.01147   0.00437  -0.0387   0.3682   1.0000
   4.750   0.7068   0.01195   0.00465  -0.0379   0.3266   1.0000
   5.000   0.7295   0.01242   0.00497  -0.0373   0.2988   1.0000
   5.500   0.7762   0.01327   0.00570  -0.0361   0.2599   1.0000
   5.750   0.7998   0.01367   0.00608  -0.0356   0.2429   1.0000
   6.000   0.8230   0.01412   0.00647  -0.0350   0.2234   1.0000
   6.250   0.8457   0.01459   0.00689  -0.0344   0.2016   1.0000
   6.500   0.8689   0.01502   0.00727  -0.0338   0.1707   1.0000
   6.750   0.8894   0.01570   0.00772  -0.0329   0.1322   1.0000
   7.000   0.9095   0.01644   0.00832  -0.0320   0.1071   1.0000
   7.250   0.9304   0.01711   0.00894  -0.0312   0.0892   1.0000
   7.500   0.9511   0.01778   0.00959  -0.0303   0.0743   1.0000
   7.750   0.9713   0.01848   0.01027  -0.0294   0.0614   1.0000
   8.000   0.9911   0.01921   0.01099  -0.0284   0.0511   1.0000
   8.250   1.0099   0.02000   0.01179  -0.0272   0.0438   1.0000
   8.500   1.0283   0.02079   0.01262  -0.0261   0.0382   1.0000
   8.750   1.0453   0.02166   0.01354  -0.0247   0.0343   1.0000
   9.000   1.0625   0.02248   0.01444  -0.0234   0.0312   1.0000
   9.250   1.0770   0.02347   0.01547  -0.0218   0.0290   1.0000
   9.500   1.0894   0.02458   0.01665  -0.0199   0.0274   1.0000
   9.750   1.1023   0.02549   0.01769  -0.0180   0.0259   1.0000
  10.000   1.1139   0.02648   0.01877  -0.0160   0.0243   1.0000
  10.250   1.1245   0.02753   0.01991  -0.0141   0.0231   1.0000
  10.500   1.1323   0.02881   0.02126  -0.0121   0.0221   1.0000
  10.750   1.1375   0.03045   0.02296  -0.0099   0.0213   1.0000
  11.000   1.1469   0.03180   0.02447  -0.0083   0.0206   1.0000
  11.250   1.1552   0.03330   0.02612  -0.0067   0.0199   1.0000
  11.500   1.1630   0.03485   0.02781  -0.0053   0.0191   1.0000
  11.750   1.1697   0.03649   0.02958  -0.0040   0.0184   1.0000
  12.000   1.1756   0.03819   0.03139  -0.0029   0.0176   1.0000
  12.250   1.1799   0.04007   0.03338  -0.0019   0.0170   1.0000
  12.500   1.1825   0.04226   0.03567  -0.0010   0.0166   1.0000
  12.750   1.1824   0.04500   0.03851  -0.0001   0.0161   1.0000
  13.000   1.1838   0.04754   0.04125   0.0004   0.0158   1.0000
  13.250   1.1834   0.05038   0.04430   0.0008   0.0156   1.0000
  13.500   1.1809   0.05355   0.04769   0.0008   0.0152   1.0000
  13.750   1.1764   0.05702   0.05138   0.0005   0.0149   1.0000
  14.000   1.1700   0.06090   0.05547  -0.0003   0.0146   1.0000
  14.250   1.1619   0.06519   0.05996  -0.0015   0.0143   1.0000
  14.500   1.1530   0.06977   0.06474  -0.0033   0.0140   1.0000
  14.750   1.1415   0.07507   0.07024  -0.0056   0.0139   1.0000
  15.000   1.1286   0.08097   0.07632  -0.0086   0.0137   1.0000
  15.250   1.1161   0.08718   0.08271  -0.0122   0.0135   1.0000
  15.500   1.0991   0.09469   0.09042  -0.0166   0.0135   1.0000
  15.750   1.0808   0.10296   0.09888  -0.0216   0.0134   1.0000
  16.000   1.0535   0.11387   0.11003  -0.0284   0.0137   1.0000
  16.250   1.0189   0.12742   0.12381  -0.0369   0.0141   1.0000
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