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HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) (hq17-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) (hq17-il)
Reynolds number: 50,000
Max Cl/Cd: 18.33 at α=12.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq17-il-50000-n5.txt
Download as CSV file: xf-hq17-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURE
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2397   0.12826   0.12169  -0.0768   0.9511   0.1174
 -10.250  -0.2457   0.12589   0.11937  -0.0792   0.9467   0.1219
 -10.000  -0.2596   0.12363   0.11719  -0.0841   0.9428   0.1234
  -9.750  -0.2270   0.11851   0.11199  -0.0822   0.9417   0.1299
  -9.500  -0.2322   0.11628   0.10980  -0.0814   0.9365   0.1314
  -9.250  -0.2321   0.11315   0.10670  -0.0829   0.9326   0.1327
  -9.000  -0.2738   0.10265   0.09622  -0.0942   0.9251   0.0662
  -8.750  -0.2583   0.09992   0.09348  -0.0917   0.9217   0.0644
  -8.500  -0.2556   0.09607   0.08963  -0.0933   0.9178   0.0624
  -8.250  -0.2668   0.09270   0.08630  -0.0939   0.9120   0.0609
  -8.000  -0.2832   0.08967   0.08329  -0.0938   0.9057   0.0597
  -7.750  -0.3013   0.08642   0.08004  -0.0935   0.8999   0.0583
  -7.500  -0.3223   0.08345   0.07704  -0.0917   0.8930   0.0571
  -7.000  -0.3656   0.07572   0.06873  -0.0888   0.8804   0.0528
  -6.750  -0.3604   0.07216   0.06498  -0.0885   0.8767   0.0523
  -6.500  -0.3581   0.06897   0.06158  -0.0874   0.8727   0.0520
  -6.250  -0.3600   0.06636   0.05877  -0.0851   0.8676   0.0517
  -6.000  -0.3513   0.06306   0.05513  -0.0845   0.8641   0.0516
  -5.750  -0.3353   0.05972   0.05120  -0.0849   0.8614   0.0525
  -5.500  -0.3335   0.05747   0.04870  -0.0823   0.8563   0.0535
  -5.250  -0.3187   0.05537   0.04649  -0.0819   0.8526   0.0555
  -5.000  -0.2967   0.05284   0.04353  -0.0821   0.8498   0.0562
  -4.750  -0.2731   0.05047   0.04066  -0.0822   0.8474   0.0565
  -4.500  -0.2621   0.04902   0.03888  -0.0801   0.8429   0.0569
  -4.250  -0.2399   0.04742   0.03690  -0.0796   0.8396   0.0577
  -4.000  -0.2125   0.04593   0.03502  -0.0797   0.8370   0.0592
  -3.750  -0.1820   0.04480   0.03352  -0.0803   0.8348   0.0628
  -3.500  -0.1711   0.04428   0.03273  -0.0777   0.8300   0.0653
  -3.250  -0.1488   0.04345   0.03175  -0.0767   0.8266   0.0675
  -3.000  -0.1227   0.04276   0.03097  -0.0763   0.8239   0.0701
  -2.750  -0.0936   0.04222   0.03025  -0.0762   0.8217   0.0736
  -2.500  -0.0849   0.04207   0.02996  -0.0733   0.8165   0.0767
  -2.250  -0.0642   0.04174   0.02951  -0.0724   0.8128   0.0824
  -2.000  -0.0387   0.04140   0.02910  -0.0723   0.8099   0.0953
  -1.750  -0.0178   0.04103   0.02880  -0.0718   0.8064   0.1132
  -1.500  -0.0045   0.04048   0.02857  -0.0702   0.8016   0.1648
  -1.250  -0.0102   0.03855   0.02940  -0.0628   0.7982   0.6496
  -1.000   0.1456   0.04095   0.03126  -0.0797   0.8010   1.0000
  -0.750   0.1593   0.04111   0.03117  -0.0781   0.7969   1.0000
  -0.500   0.1680   0.04132   0.03119  -0.0758   0.7925   1.0000
  -0.250   0.1659   0.04154   0.03128  -0.0717   0.7861   1.0000
   0.000   0.1840   0.04169   0.03122  -0.0707   0.7823   1.0000
   0.250   0.1807   0.04192   0.03134  -0.0665   0.7756   1.0000
   0.500   0.1940   0.04210   0.03134  -0.0647   0.7709   1.0000
   0.750   0.2077   0.04234   0.03143  -0.0631   0.7667   1.0000
   1.000   0.2083   0.04269   0.03168  -0.0596   0.7605   1.0000
   1.250   0.2287   0.04303   0.03186  -0.0591   0.7568   1.0000
   1.500   0.2397   0.04349   0.03220  -0.0574   0.7515   1.0000
   1.750   0.2543   0.04399   0.03257  -0.0562   0.7462   1.0000
   2.000   0.2800   0.04446   0.03291  -0.0566   0.7429   1.0000
   2.250   0.2909   0.04517   0.03355  -0.0552   0.7374   1.0000
   2.500   0.3099   0.04579   0.03408  -0.0549   0.7325   1.0000
   2.750   0.3390   0.04629   0.03448  -0.0558   0.7292   1.0000
   3.000   0.3484   0.04712   0.03526  -0.0543   0.7223   1.0000
   3.250   0.3740   0.04771   0.03578  -0.0548   0.7180   1.0000
   3.500   0.3934   0.04837   0.03640  -0.0545   0.7119   1.0000
   3.750   0.4155   0.04897   0.03696  -0.0545   0.7058   1.0000
   4.000   0.4484   0.04939   0.03734  -0.0558   0.7023   1.0000
   4.250   0.4564   0.05037   0.03832  -0.0543   0.6936   1.0000
   4.500   0.4877   0.05081   0.03875  -0.0554   0.6896   1.0000
   4.750   0.4992   0.05170   0.03965  -0.0542   0.6807   1.0000
   5.000   0.5317   0.05201   0.03997  -0.0553   0.6763   1.0000
   5.250   0.5434   0.05295   0.04094  -0.0543   0.6671   1.0000
   5.500   0.5752   0.05331   0.04135  -0.0553   0.6631   1.0000
   5.750   0.5845   0.05449   0.04258  -0.0542   0.6540   1.0000
   6.000   0.6145   0.05494   0.04309  -0.0550   0.6497   1.0000
   6.250   0.6240   0.05616   0.04437  -0.0539   0.6403   1.0000
   6.500   0.6548   0.05651   0.04483  -0.0547   0.6358   1.0000
   6.750   0.6651   0.05767   0.04607  -0.0537   0.6256   1.0000
   7.250   0.7137   0.05841   0.04700  -0.0538   0.6096   1.0000
   7.500   0.7292   0.05915   0.04784  -0.0530   0.5987   1.0000
   7.750   0.7644   0.05883   0.04770  -0.0537   0.5934   1.0000
   8.000   0.7746   0.06000   0.04899  -0.0527   0.5815   1.0000
   8.250   0.7900   0.06092   0.05003  -0.0521   0.5711   1.0000
   8.500   0.8201   0.06086   0.05014  -0.0523   0.5648   1.0000
   8.750   0.8310   0.06206   0.05153  -0.0514   0.5527   1.0000
   9.000   0.8458   0.06304   0.05266  -0.0508   0.5418   1.0000
   9.250   0.8775   0.06266   0.05248  -0.0510   0.5355   1.0000
   9.500   0.8893   0.06381   0.05380  -0.0501   0.5230   1.0000
   9.750   0.9044   0.06457   0.05474  -0.0493   0.5105   1.0000
  10.000   0.9233   0.06483   0.05524  -0.0485   0.4981   1.0000
  10.500   0.9824   0.06255   0.05343  -0.0469   0.4771   1.0000
  10.750   1.0016   0.06242   0.05351  -0.0458   0.4632   1.0000
  11.250   1.0360   0.06240   0.05395  -0.0433   0.4299   1.0000
  11.500   1.0491   0.06280   0.05455  -0.0419   0.4093   1.0000
  11.750   1.0790   0.06118   0.05310  -0.0406   0.3902   1.0000
  12.000   1.0952   0.06161   0.05369  -0.0395   0.3691   1.0000
  12.250   1.1181   0.06122   0.05343  -0.0383   0.3472   1.0000
  12.500   1.1328   0.06179   0.05406  -0.0370   0.3206   1.0000
  12.750   1.1388   0.06342   0.05571  -0.0357   0.2909   1.0000
  13.000   1.1441   0.06510   0.05731  -0.0344   0.2608   1.0000
  13.250   1.1445   0.06755   0.05966  -0.0332   0.2327   1.0000
  13.500   1.1413   0.07063   0.06268  -0.0324   0.2049   1.0000
  13.750   1.1358   0.07414   0.06608  -0.0319   0.1781   1.0000
  14.000   1.1297   0.07785   0.06964  -0.0317   0.1547   1.0000
  14.250   1.1225   0.08182   0.07344  -0.0317   0.1343   1.0000
  14.500   1.1168   0.08591   0.07751  -0.0320   0.1132   1.0000
  14.750   1.1118   0.08998   0.08157  -0.0325   0.0972   1.0000
  15.000   1.1057   0.09432   0.08584  -0.0332   0.0834   1.0000
  15.250   1.0984   0.09896   0.09044  -0.0341   0.0698   1.0000
  15.500   1.0931   0.10341   0.09487  -0.0351   0.0597   1.0000
  15.750   1.0893   0.10775   0.09930  -0.0360   0.0502   1.0000
  16.000   1.0873   0.11183   0.10345  -0.0369   0.0442   1.0000
  16.250   1.0868   0.11574   0.10748  -0.0379   0.0395   1.0000
  16.500   1.0847   0.11989   0.11163  -0.0393   0.0360   1.0000
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