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HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il)
Reynolds number: 100,000
Max Cl/Cd: 58.39 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2590sm-il-100000.txt
Download as CSV file: xf-hq2590sm-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/9.0 smoothed by Eppler                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4212   0.09199   0.08708  -0.0333   1.0000   0.1003
  -8.250  -0.4429   0.08964   0.08489  -0.0369   1.0000   0.1022
  -8.000  -0.4674   0.08617   0.08152  -0.0439   1.0000   0.1028
  -7.750  -0.4394   0.08260   0.07798  -0.0343   1.0000   0.1069
  -7.500  -0.4394   0.07997   0.07542  -0.0334   1.0000   0.1107
  -7.250  -0.4509   0.07654   0.07208  -0.0366   1.0000   0.1145
  -7.000  -0.4841   0.07355   0.06890  -0.0445   1.0000   0.1175
  -6.750  -0.4728   0.06925   0.06484  -0.0398   1.0000   0.1202
  -6.500  -0.4686   0.06722   0.06287  -0.0364   1.0000   0.1247
  -6.250  -0.4841   0.06371   0.05901  -0.0420   1.0000   0.1331
  -6.000  -0.4739   0.06120   0.05679  -0.0363   1.0000   0.1382
  -5.750  -0.4735   0.05774   0.05317  -0.0382   1.0000   0.1497
  -5.500  -0.4676   0.05499   0.05027  -0.0386   1.0000   0.1637
  -5.250  -0.4588   0.05231   0.04753  -0.0383   1.0000   0.1785
  -5.000  -0.4485   0.04961   0.04482  -0.0374   1.0000   0.1938
  -4.750  -0.4373   0.04716   0.04241  -0.0360   1.0000   0.2105
  -4.250  -0.3474   0.03361   0.02602  -0.0453   1.0000   0.0890
  -4.000  -0.3231   0.03029   0.02253  -0.0455   1.0000   0.0866
  -3.750  -0.2961   0.02757   0.01947  -0.0456   1.0000   0.0822
  -3.500  -0.2683   0.02544   0.01683  -0.0453   1.0000   0.0790
  -3.250  -0.2426   0.02393   0.01499  -0.0448   1.0000   0.0789
  -3.000  -0.2187   0.02295   0.01388  -0.0443   1.0000   0.0834
  -2.750  -0.1940   0.02197   0.01269  -0.0436   1.0000   0.0866
  -2.500  -0.1697   0.02102   0.01161  -0.0428   1.0000   0.0894
  -2.250  -0.1461   0.02001   0.01074  -0.0424   1.0000   0.0961
  -2.000  -0.1226   0.01932   0.01012  -0.0418   1.0000   0.1078
  -1.750  -0.0983   0.01865   0.00954  -0.0415   1.0000   0.1251
  -1.500  -0.0718   0.01601   0.00927  -0.0417   1.0000   0.6213
  -1.250  -0.0667   0.01598   0.00970  -0.0355   1.0000   0.7904
  -1.000  -0.0613   0.01588   0.00978  -0.0299   1.0000   0.8794
  -0.750  -0.0098   0.01590   0.00970  -0.0350   0.9898   1.0000
  -0.500   0.0434   0.01644   0.00994  -0.0408   0.9794   1.0000
  -0.250   0.0976   0.01697   0.01023  -0.0467   0.9698   1.0000
   0.000   0.1371   0.01723   0.01033  -0.0497   0.9599   1.0000
   0.250   0.1793   0.01758   0.01052  -0.0530   0.9512   1.0000
   0.500   0.2242   0.01790   0.01073  -0.0567   0.9428   1.0000
   0.750   0.2600   0.01814   0.01089  -0.0587   0.9329   1.0000
   1.000   0.3051   0.01838   0.01107  -0.0622   0.9246   1.0000
   1.250   0.3450   0.01854   0.01120  -0.0647   0.9145   1.0000
   1.500   0.3825   0.01866   0.01132  -0.0666   0.9035   1.0000
   1.750   0.4266   0.01868   0.01135  -0.0695   0.8936   1.0000
   2.000   0.4758   0.01851   0.01123  -0.0730   0.8839   1.0000
   2.250   0.5157   0.01839   0.01117  -0.0749   0.8716   1.0000
   2.500   0.5568   0.01813   0.01099  -0.0766   0.8592   1.0000
   2.750   0.5976   0.01777   0.01072  -0.0780   0.8464   1.0000
   3.000   0.6365   0.01732   0.01039  -0.0788   0.8322   1.0000
   3.250   0.6729   0.01683   0.00999  -0.0790   0.8159   1.0000
   3.500   0.7082   0.01625   0.00950  -0.0788   0.7977   1.0000
   3.750   0.7387   0.01575   0.00911  -0.0777   0.7746   1.0000
   4.000   0.7678   0.01521   0.00861  -0.0762   0.7455   1.0000
   4.250   0.7950   0.01472   0.00810  -0.0743   0.7078   1.0000
   4.500   0.8182   0.01450   0.00786  -0.0722   0.6573   1.0000
   4.750   0.8416   0.01449   0.00767  -0.0703   0.5993   1.0000
   5.000   0.8647   0.01481   0.00768  -0.0687   0.5439   1.0000
   5.250   0.8870   0.01543   0.00802  -0.0673   0.4973   1.0000
   5.500   0.9087   0.01614   0.00855  -0.0660   0.4566   1.0000
   5.750   0.9296   0.01688   0.00913  -0.0647   0.4170   1.0000
   6.000   0.9494   0.01759   0.00975  -0.0632   0.3748   1.0000
   6.250   0.9664   0.01836   0.01036  -0.0614   0.3209   1.0000
   6.500   0.9800   0.01938   0.01104  -0.0592   0.2468   1.0000
   6.750   0.9930   0.02088   0.01203  -0.0571   0.1828   1.0000
   7.000   1.0083   0.02248   0.01332  -0.0554   0.1447   1.0000
   7.250   1.0249   0.02419   0.01487  -0.0537   0.1194   1.0000
   7.500   1.0434   0.02620   0.01664  -0.0525   0.1021   1.0000
   7.750   1.0651   0.02805   0.01842  -0.0516   0.0890   1.0000
   8.000   1.0900   0.03001   0.02060  -0.0509   0.0812   1.0000
   8.250   1.1169   0.03273   0.02320  -0.0509   0.0749   1.0000
   8.500   1.1380   0.03445   0.02532  -0.0497   0.0696   1.0000
   8.750   1.1608   0.03687   0.02794  -0.0489   0.0662   1.0000
   9.000   1.1835   0.04073   0.03188  -0.0488   0.0632   1.0000
   9.250   1.1952   0.04321   0.03497  -0.0465   0.0610   1.0000
   9.500   1.2049   0.04624   0.03855  -0.0442   0.0592   1.0000
   9.750   1.2110   0.05006   0.04287  -0.0419   0.0586   1.0000
  10.000   1.2117   0.05421   0.04750  -0.0393   0.0585   1.0000
  10.250   1.2068   0.05844   0.05218  -0.0366   0.0586   1.0000
  10.500   1.1966   0.06261   0.05673  -0.0338   0.0586   1.0000
  10.750   1.1806   0.06665   0.06108  -0.0308   0.0588   1.0000
  11.000   1.1597   0.07063   0.06530  -0.0281   0.0592   1.0000
  11.250   1.1369   0.07499   0.06987  -0.0265   0.0596   1.0000
  11.500   1.1141   0.08003   0.07508  -0.0264   0.0604   1.0000
  11.750   1.0918   0.08570   0.08090  -0.0276   0.0611   1.0000
  12.000   1.0716   0.09210   0.08739  -0.0297   0.0618   1.0000
  12.250   1.0572   0.09906   0.09441  -0.0322   0.0626   1.0000
  12.500   0.8142   0.13003   0.12585  -0.0508   0.0877   1.0000
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