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HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) (hq17-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) (hq17-il)
Reynolds number: 200,000
Max Cl/Cd: 68.87 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq17-il-200000.txt
Download as CSV file: xf-hq17-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.0502   0.09666   0.09292  -0.1387   0.9441   0.0469
 -10.750  -0.0482   0.09258   0.08884  -0.1440   0.9400   0.0473
 -10.500  -0.0499   0.08897   0.08524  -0.1467   0.9342   0.0474
 -10.250  -0.0311   0.08505   0.08132  -0.1430   0.9332   0.0499
 -10.000  -0.0189   0.08229   0.07853  -0.1444   0.9303   0.0515
  -9.750  -0.0118   0.07918   0.07540  -0.1465   0.9270   0.0536
  -9.500  -0.0167   0.07644   0.07268  -0.1471   0.9208   0.0556
  -9.250  -0.0220   0.07221   0.06848  -0.1510   0.9157   0.0578
  -9.000  -0.0440   0.06814   0.06443  -0.1540   0.9067   0.0587
  -8.750  -0.0689   0.06498   0.06119  -0.1547   0.8989   0.0592
  -6.750  -0.1523   0.04994   0.04531  -0.1316   0.8517   0.0757
  -6.500  -0.1338   0.04806   0.04354  -0.1314   0.8494   0.0797
  -6.250  -0.1257   0.04567   0.04063  -0.1304   0.8469   0.0896
  -6.000  -0.1017   0.04316   0.03819  -0.1310   0.8456   0.0940
  -5.750  -0.1222   0.04353   0.03854  -0.1234   0.8352   0.0956
  -5.500  -0.1025   0.04120   0.03596  -0.1235   0.8335   0.1068
  -5.250  -0.1268   0.04180   0.03656  -0.1152   0.8235   0.1077
  -5.000  -0.0996   0.03399   0.02738  -0.1123   0.8213   0.0566
  -4.750  -0.0666   0.03080   0.02342  -0.1122   0.8202   0.0488
  -4.500  -0.0587   0.03055   0.02301  -0.1087   0.8147   0.0481
  -4.250  -0.0049   0.02831   0.02047  -0.1129   0.8169   0.0479
  -3.500   0.0009   0.02771   0.01976  -0.1003   0.7976   0.0513
  -3.250   0.0252   0.02707   0.01909  -0.0998   0.7948   0.0524
  -3.000   0.0562   0.02632   0.01831  -0.1003   0.7932   0.0541
  -2.750   0.0897   0.02560   0.01754  -0.1013   0.7920   0.0568
  -2.500   0.1010   0.02570   0.01761  -0.0988   0.7871   0.0589
  -2.250   0.1060   0.02598   0.01787  -0.0954   0.7807   0.0623
  -2.000   0.1380   0.02547   0.01735  -0.0963   0.7791   0.0725
  -1.750   0.1674   0.02372   0.01668  -0.0974   0.7780   0.3110
  -1.500   0.1464   0.02367   0.01812  -0.0894   0.7692   0.6629
  -1.250   0.1601   0.02425   0.01891  -0.0847   0.7661   0.7956
  -1.000   0.1802   0.02462   0.01923  -0.0812   0.7643   0.8353
  -0.750   0.1707   0.02576   0.02036  -0.0749   0.7558   0.8512
  -0.500   0.1780   0.02596   0.02054  -0.0699   0.7525   0.8765
  -0.250   0.1848   0.02565   0.02021  -0.0641   0.7505   0.9048
   0.000   0.1816   0.02565   0.02021  -0.0574   0.7463   0.9306
   0.250   0.2265   0.02481   0.01928  -0.0585   0.7481   0.9551
   0.500   0.2334   0.02623   0.02068  -0.0573   0.7379   0.9670
   0.750   0.3138   0.02663   0.02096  -0.0677   0.7380   0.9759
   1.000   0.3590   0.02662   0.02086  -0.0713   0.7369   0.9789
   1.250   0.3981   0.02650   0.02066  -0.0738   0.7359   0.9813
   1.500   0.4417   0.02634   0.02044  -0.0770   0.7352   0.9827
   1.750   0.4858   0.02614   0.02018  -0.0803   0.7347   0.9840
   2.000   0.4876   0.02801   0.02207  -0.0790   0.7237   0.9916
   2.250   0.5270   0.02780   0.02183  -0.0813   0.7226   0.9939
   2.500   0.5682   0.02749   0.02149  -0.0839   0.7218   0.9961
   2.750   0.6114   0.02704   0.02103  -0.0867   0.7212   0.9979
   3.000   0.6541   0.02652   0.02049  -0.0894   0.7201   0.9995
   3.250   0.7028   0.02562   0.01959  -0.0927   0.7206   0.9998
   3.500   0.6399   0.02722   0.02119  -0.0785   0.7054   1.0000
   3.750   0.6870   0.02622   0.02018  -0.0812   0.7062   1.0000
   5.000   0.7562   0.02814   0.02218  -0.0731   0.6751   1.0000
   5.250   0.8051   0.02678   0.02087  -0.0757   0.6762   1.0000
   5.500   0.8515   0.02555   0.01969  -0.0781   0.6767   1.0000
   5.750   0.8998   0.02438   0.01858  -0.0810   0.6772   1.0000
   6.000   0.9570   0.02272   0.01699  -0.0850   0.6775   1.0000
   6.250   0.9616   0.02329   0.01761  -0.0818   0.6671   1.0000
   6.500   1.0270   0.02110   0.01549  -0.0868   0.6666   1.0000
   6.750   1.0875   0.01970   0.01419  -0.0918   0.6652   1.0000
   7.000   1.0828   0.02047   0.01503  -0.0870   0.6544   1.0000
   7.250   1.1400   0.01917   0.01382  -0.0915   0.6517   1.0000
   7.500   1.1412   0.01979   0.01451  -0.0876   0.6413   1.0000
   7.750   1.1945   0.01842   0.01322  -0.0912   0.6346   1.0000
   8.000   1.2101   0.01825   0.01310  -0.0892   0.6221   1.0000
   8.250   1.2277   0.01806   0.01296  -0.0875   0.6080   1.0000
   8.500   1.2445   0.01807   0.01299  -0.0857   0.5922   1.0000
   8.750   1.2499   0.01862   0.01358  -0.0826   0.5738   1.0000
   9.000   1.2597   0.01901   0.01397  -0.0800   0.5505   1.0000
   9.250   1.2624   0.01976   0.01467  -0.0766   0.5206   1.0000
   9.500   1.2675   0.02056   0.01531  -0.0736   0.4840   1.0000
   9.750   1.2721   0.02154   0.01609  -0.0707   0.4486   1.0000
  10.250   1.2657   0.02463   0.01880  -0.0637   0.3719   1.0000
  10.500   1.2561   0.02673   0.02065  -0.0598   0.3333   1.0000
  10.750   1.2535   0.02861   0.02240  -0.0570   0.2982   1.0000
  11.000   1.2413   0.03123   0.02471  -0.0535   0.2546   1.0000
  11.250   1.2396   0.03331   0.02668  -0.0513   0.2259   1.0000
  11.500   1.2369   0.03558   0.02879  -0.0491   0.1910   1.0000
  11.750   1.2337   0.03799   0.03100  -0.0471   0.1572   1.0000
  12.000   1.2311   0.04046   0.03330  -0.0453   0.1285   1.0000
  12.250   1.2310   0.04281   0.03550  -0.0438   0.1003   1.0000
  12.500   1.2305   0.04526   0.03781  -0.0424   0.0785   1.0000
  12.750   1.2258   0.04822   0.04061  -0.0407   0.0510   1.0000
  13.000   1.2183   0.05157   0.04373  -0.0391   0.0289   1.0000
  13.250   1.2176   0.05439   0.04659  -0.0379   0.0239   1.0000
  13.500   1.2132   0.05768   0.04996  -0.0367   0.0213   1.0000
  13.750   1.2141   0.06050   0.05292  -0.0359   0.0201   1.0000
  14.000   1.2151   0.06335   0.05589  -0.0353   0.0188   1.0000
  14.250   1.2166   0.06619   0.05886  -0.0348   0.0178   1.0000
  14.500   1.2173   0.06915   0.06191  -0.0344   0.0169   1.0000
  14.750   1.2182   0.07215   0.06500  -0.0340   0.0165   1.0000
  15.000   1.2136   0.07572   0.06861  -0.0333   0.0151   1.0000
  15.250   1.2198   0.07814   0.07115  -0.0330   0.0149   1.0000
  15.500   1.2263   0.08057   0.07371  -0.0327   0.0145   1.0000
  15.750   1.2336   0.08290   0.07617  -0.0324   0.0142   1.0000
  16.000   1.2412   0.08524   0.07865  -0.0321   0.0138   1.0000
  16.250   1.2491   0.08757   0.08113  -0.0318   0.0137   1.0000
  16.500   1.2560   0.09012   0.08385  -0.0315   0.0135   1.0000
  16.750   1.2609   0.09305   0.08696  -0.0315   0.0133   1.0000
  17.000   1.2638   0.09629   0.09041  -0.0316   0.0133   1.0000
  17.250   1.2637   0.10003   0.09440  -0.0320   0.0132   1.0000
  17.500   1.2604   0.10424   0.09885  -0.0327   0.0132   1.0000
  17.750   1.2537   0.10906   0.10392  -0.0338   0.0133   1.0000
  18.000   1.2448   0.11430   0.10940  -0.0354   0.0134   1.0000
  18.250   1.2336   0.12001   0.11536  -0.0374   0.0135   1.0000
  18.500   1.2202   0.12626   0.12186  -0.0401   0.0136   1.0000
  18.750   1.2053   0.13297   0.12880  -0.0433   0.0137   1.0000
  19.000   1.1897   0.14004   0.13607  -0.0470   0.0139   1.0000
  19.250   1.1725   0.14777   0.14401  -0.0514   0.0141   1.0000
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