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HQ 2.5/11 AIRFOIL (hq2511-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/11 AIRFOIL (hq2511-il)
Reynolds number: 100,000
Max Cl/Cd: 56.75 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2511-il-100000.txt
Download as CSV file: xf-hq2511-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/11 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3922   0.10117   0.09625  -0.0370   1.0000   0.0965
  -9.250  -0.4194   0.09816   0.09342  -0.0435   1.0000   0.0992
  -9.000  -0.4455   0.09462   0.09004  -0.0484   1.0000   0.0995
  -8.750  -0.4009   0.09038   0.08570  -0.0405   1.0000   0.1030
  -8.500  -0.3974   0.08756   0.08293  -0.0398   1.0000   0.1062
  -8.250  -0.4058   0.08456   0.08003  -0.0404   1.0000   0.1096
  -8.000  -0.4304   0.08188   0.07750  -0.0413   1.0000   0.1120
  -7.750  -0.4720   0.07896   0.07472  -0.0436   1.0000   0.1131
  -7.500  -0.5126   0.07719   0.07288  -0.0439   1.0000   0.1139
  -7.250  -0.5075   0.07291   0.06876  -0.0410   1.0000   0.1157
  -7.000  -0.5004   0.07080   0.06672  -0.0372   1.0000   0.1181
  -6.750  -0.5066   0.06845   0.06440  -0.0353   1.0000   0.1206
  -6.500  -0.5350   0.06498   0.06057  -0.0386   1.0000   0.1295
  -6.250  -0.5257   0.06182   0.05759  -0.0357   1.0000   0.1317
  -6.000  -0.5226   0.04877   0.04317  -0.0411   1.0000   0.0723
  -5.750  -0.5072   0.04229   0.03627  -0.0405   1.0000   0.0557
  -5.500  -0.4923   0.03848   0.03209  -0.0401   1.0000   0.0535
  -5.250  -0.4738   0.03535   0.02849  -0.0398   1.0000   0.0536
  -5.000  -0.4529   0.03271   0.02532  -0.0394   1.0000   0.0551
  -4.750  -0.4302   0.03038   0.02244  -0.0388   1.0000   0.0567
  -4.500  -0.4066   0.02817   0.01971  -0.0381   1.0000   0.0585
  -4.250  -0.3782   0.02588   0.01734  -0.0388   0.9983   0.0647
  -4.000  -0.3410   0.02407   0.01524  -0.0406   0.9945   0.0821
  -3.750  -0.3073   0.02307   0.01422  -0.0425   0.9897   0.1038
  -3.500  -0.2718   0.02236   0.01352  -0.0447   0.9852   0.1234
  -3.250  -0.2381   0.02152   0.01272  -0.0460   0.9804   0.1357
  -3.000  -0.2048   0.02093   0.01218  -0.0474   0.9750   0.1556
  -2.750  -0.1667   0.02026   0.01178  -0.0498   0.9705   0.1940
  -2.500  -0.1470   0.01825   0.01193  -0.0486   0.9641   0.6045
  -2.250  -0.1146   0.01883   0.01258  -0.0480   0.9566   0.7160
  -2.000  -0.0920   0.01908   0.01281  -0.0461   0.9468   0.7624
  -1.750  -0.0653   0.01934   0.01304  -0.0449   0.9394   0.8005
  -1.500  -0.0452   0.01947   0.01314  -0.0425   0.9315   0.8387
  -1.250  -0.0249   0.01956   0.01321  -0.0400   0.9249   0.8770
  -1.000  -0.0025   0.01956   0.01323  -0.0377   0.9176   0.9251
  -0.750   0.0751   0.01984   0.01337  -0.0466   0.9155   0.9707
  -0.500   0.1536   0.02002   0.01335  -0.0567   0.9133   0.9868
  -0.250   0.1865   0.02007   0.01331  -0.0594   0.9041   1.0000
   0.000   0.2102   0.02012   0.01326  -0.0600   0.8956   1.0000
   0.250   0.2379   0.02019   0.01325  -0.0612   0.8869   1.0000
   0.500   0.2634   0.02037   0.01334  -0.0618   0.8771   1.0000
   0.750   0.3099   0.02039   0.01329  -0.0657   0.8711   1.0000
   1.000   0.3403   0.02050   0.01334  -0.0667   0.8600   1.0000
   1.250   0.3888   0.02026   0.01306  -0.0702   0.8514   1.0000
   1.500   0.4342   0.01990   0.01267  -0.0728   0.8420   1.0000
   1.750   0.4656   0.01984   0.01258  -0.0733   0.8302   1.0000
   2.000   0.5022   0.01967   0.01241  -0.0745   0.8210   1.0000
   2.250   0.5412   0.01933   0.01208  -0.0758   0.8122   1.0000
   2.500   0.5704   0.01923   0.01199  -0.0756   0.7999   1.0000
   2.750   0.6014   0.01905   0.01183  -0.0756   0.7883   1.0000
   3.000   0.6357   0.01871   0.01153  -0.0759   0.7779   1.0000
   3.250   0.6696   0.01833   0.01117  -0.0760   0.7672   1.0000
   3.500   0.6986   0.01808   0.01095  -0.0754   0.7532   1.0000
   3.750   0.7286   0.01769   0.01061  -0.0747   0.7383   1.0000
   4.000   0.7579   0.01727   0.01021  -0.0738   0.7215   1.0000
   4.250   0.7832   0.01702   0.00999  -0.0725   0.7009   1.0000
   4.500   0.8119   0.01665   0.00964  -0.0715   0.6809   1.0000
   4.750   0.8373   0.01646   0.00948  -0.0703   0.6573   1.0000
   5.000   0.8634   0.01628   0.00930  -0.0691   0.6320   1.0000
   5.250   0.8874   0.01622   0.00925  -0.0677   0.6016   1.0000
   5.500   0.9104   0.01625   0.00924  -0.0662   0.5660   1.0000
   5.750   0.9324   0.01643   0.00930  -0.0646   0.5253   1.0000
   6.000   0.9532   0.01685   0.00951  -0.0630   0.4823   1.0000
   6.250   0.9730   0.01753   0.00996  -0.0614   0.4406   1.0000
   6.500   0.9920   0.01834   0.01054  -0.0598   0.4009   1.0000
   6.750   1.0100   0.01912   0.01120  -0.0581   0.3625   1.0000
   7.000   1.0284   0.02002   0.01190  -0.0566   0.3303   1.0000
   7.250   1.0481   0.02109   0.01280  -0.0554   0.3025   1.0000
   7.500   1.0685   0.02221   0.01384  -0.0544   0.2781   1.0000
   7.750   1.0870   0.02315   0.01465  -0.0532   0.2558   1.0000
   8.000   1.1027   0.02384   0.01542  -0.0515   0.2339   1.0000
   8.250   1.1188   0.02454   0.01613  -0.0500   0.2155   1.0000
   8.500   1.1332   0.02524   0.01681  -0.0483   0.1978   1.0000
   8.750   1.1458   0.02585   0.01762  -0.0463   0.1787   1.0000
   9.000   1.1559   0.02655   0.01840  -0.0440   0.1582   1.0000
   9.250   1.1589   0.02758   0.01938  -0.0409   0.1287   1.0000
   9.500   1.1555   0.02954   0.02112  -0.0371   0.0904   1.0000
   9.750   1.1572   0.03164   0.02310  -0.0340   0.0733   1.0000
  10.000   1.1618   0.03357   0.02495  -0.0315   0.0648   1.0000
  10.250   1.1720   0.03530   0.02681  -0.0296   0.0583   1.0000
  10.500   1.1791   0.03737   0.02877  -0.0278   0.0536   1.0000
  10.750   1.1945   0.03934   0.03099  -0.0264   0.0506   1.0000
  11.000   1.2112   0.04153   0.03333  -0.0252   0.0480   1.0000
  11.250   1.2284   0.04388   0.03580  -0.0243   0.0461   1.0000
  11.500   1.2499   0.04695   0.03891  -0.0240   0.0440   1.0000
  11.750   1.2603   0.05034   0.04259  -0.0228   0.0428   1.0000
  12.000   1.2592   0.05315   0.04576  -0.0206   0.0419   1.0000
  12.250   1.2547   0.05632   0.04928  -0.0187   0.0412   1.0000
  12.500   1.2476   0.05994   0.05323  -0.0171   0.0410   1.0000
  12.750   1.2360   0.06397   0.05758  -0.0159   0.0409   1.0000
  13.000   1.2212   0.06834   0.06226  -0.0152   0.0410   1.0000
  13.250   1.2031   0.07317   0.06738  -0.0152   0.0411   1.0000
  13.500   1.1828   0.07856   0.07303  -0.0161   0.0414   1.0000
  13.750   1.1609   0.08449   0.07920  -0.0179   0.0416   1.0000
  14.000   1.1374   0.09112   0.08604  -0.0207   0.0419   1.0000
  14.250   1.1127   0.09853   0.09364  -0.0246   0.0422   1.0000
  14.500   1.0877   0.10679   0.10207  -0.0295   0.0426   1.0000
  14.750   1.0642   0.11570   0.11110  -0.0350   0.0431   1.0000
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