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HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il)
Reynolds number: 200,000
Max Cl/Cd: 79.55 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2590sm-il-200000.txt
Download as CSV file: xf-hq2590sm-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4170   0.09572   0.09207  -0.0319   1.0000   0.0435
  -9.000  -0.4172   0.09223   0.08862  -0.0336   1.0000   0.0451
  -8.750  -0.4242   0.08836   0.08482  -0.0376   1.0000   0.0471
  -8.500  -0.3536   0.07307   0.06984  -0.0394   1.0000   0.0506
  -8.250  -0.3507   0.07038   0.06718  -0.0383   1.0000   0.0521
  -8.000  -0.3553   0.06721   0.06406  -0.0380   1.0000   0.0534
  -7.750  -0.3663   0.06415   0.06107  -0.0373   1.0000   0.0545
  -7.500  -0.3867   0.06192   0.05895  -0.0350   1.0000   0.0546
  -7.250  -0.4955   0.06516   0.06167  -0.0470   1.0000   0.0489
  -7.000  -0.4940   0.06229   0.05893  -0.0442   1.0000   0.0499
  -6.750  -0.4934   0.06072   0.05743  -0.0414   1.0000   0.0512
  -6.500  -0.4938   0.05875   0.05546  -0.0396   1.0000   0.0527
  -6.250  -0.4735   0.05459   0.05111  -0.0439   0.9970   0.0570
  -6.000  -0.3882   0.03316   0.02954  -0.0565   0.9836   0.0648
  -5.750  -0.3664   0.02985   0.02607  -0.0587   0.9785   0.0690
  -5.500  -0.3401   0.02498   0.02067  -0.0629   0.9740   0.0772
  -5.250  -0.3103   0.02193   0.01757  -0.0652   0.9714   0.0822
  -5.000  -0.2841   0.01911   0.01449  -0.0673   0.9669   0.0938
  -4.750  -0.2572   0.01673   0.01185  -0.0690   0.9623   0.1072
  -4.500  -0.2409   0.02409   0.01731  -0.0672   0.9707   0.0475
  -4.250  -0.2109   0.02184   0.01473  -0.0679   0.9666   0.0472
  -4.000  -0.1791   0.02041   0.01299  -0.0687   0.9626   0.0489
  -3.750  -0.1457   0.01857   0.01097  -0.0698   0.9600   0.0497
  -3.500  -0.1110   0.01726   0.00963  -0.0713   0.9578   0.0516
  -3.250  -0.0740   0.01642   0.00878  -0.0732   0.9559   0.0552
  -3.000  -0.0489   0.01598   0.00828  -0.0727   0.9498   0.0599
  -2.750  -0.0168   0.01503   0.00738  -0.0738   0.9465   0.0659
  -2.500   0.0189   0.01439   0.00676  -0.0756   0.9439   0.0788
  -2.250   0.0560   0.01313   0.00605  -0.0781   0.9420   0.1955
  -2.000   0.0742   0.01183   0.00634  -0.0769   0.9364   0.6247
  -1.750   0.1083   0.01173   0.00637  -0.0775   0.9313   0.6999
  -1.500   0.1509   0.01149   0.00623  -0.0793   0.9274   0.7564
  -1.250   0.1771   0.01139   0.00617  -0.0781   0.9183   0.7887
  -1.000   0.2108   0.01119   0.00601  -0.0781   0.9133   0.8241
  -0.750   0.2318   0.01110   0.00597  -0.0758   0.9045   0.8529
  -0.500   0.2625   0.01091   0.00575  -0.0758   0.8995   0.8708
  -0.250   0.2877   0.01080   0.00564  -0.0749   0.8931   0.8868
   0.000   0.3139   0.01064   0.00549  -0.0741   0.8868   0.9044
   0.250   0.3460   0.01041   0.00525  -0.0744   0.8825   0.9232
   0.500   0.3767   0.01031   0.00517  -0.0748   0.8746   0.9468
   0.750   0.4222   0.01008   0.00493  -0.0781   0.8696   0.9700
   1.000   0.4615   0.01000   0.00484  -0.0807   0.8617   1.0000
   1.250   0.4917   0.00993   0.00471  -0.0812   0.8543   1.0000
   1.500   0.5187   0.00996   0.00472  -0.0812   0.8444   1.0000
   1.750   0.5477   0.00992   0.00466  -0.0812   0.8354   1.0000
   2.000   0.5762   0.00988   0.00459  -0.0811   0.8253   1.0000
   2.250   0.6030   0.00987   0.00458  -0.0806   0.8133   1.0000
   2.500   0.6301   0.00985   0.00454  -0.0801   0.8005   1.0000
   2.750   0.6570   0.00981   0.00451  -0.0795   0.7861   1.0000
   3.000   0.6836   0.00976   0.00445  -0.0788   0.7693   1.0000
   3.250   0.7096   0.00970   0.00437  -0.0779   0.7474   1.0000
   3.500   0.7341   0.00965   0.00427  -0.0767   0.7144   1.0000
   3.750   0.7580   0.00967   0.00419  -0.0754   0.6710   1.0000
   4.000   0.7812   0.00982   0.00415  -0.0740   0.6090   1.0000
   4.250   0.8019   0.01028   0.00421  -0.0723   0.5350   1.0000
   4.500   0.8227   0.01091   0.00453  -0.0710   0.4808   1.0000
   4.750   0.8447   0.01150   0.00491  -0.0700   0.4413   1.0000
   5.000   0.8676   0.01202   0.00530  -0.0692   0.4094   1.0000
   5.250   0.8908   0.01251   0.00570  -0.0684   0.3803   1.0000
   5.500   0.9131   0.01302   0.00611  -0.0675   0.3453   1.0000
   5.750   0.9349   0.01354   0.00650  -0.0666   0.3035   1.0000
   6.000   0.9559   0.01415   0.00693  -0.0657   0.2536   1.0000
   6.250   0.9748   0.01504   0.00748  -0.0645   0.1858   1.0000
   6.500   0.9923   0.01620   0.00830  -0.0631   0.1330   1.0000
   6.750   1.0106   0.01730   0.00921  -0.0618   0.1041   1.0000
   7.000   1.0290   0.01840   0.01023  -0.0605   0.0829   1.0000
   7.250   1.0466   0.01962   0.01140  -0.0589   0.0683   1.0000
   7.500   1.0636   0.02096   0.01272  -0.0573   0.0595   1.0000
   7.750   1.0824   0.02205   0.01382  -0.0561   0.0531   1.0000
   8.000   1.1009   0.02357   0.01540  -0.0547   0.0492   1.0000
   8.250   1.1218   0.02474   0.01668  -0.0537   0.0459   1.0000
   8.500   1.1416   0.02595   0.01789  -0.0527   0.0425   1.0000
   8.750   1.1626   0.02820   0.02022  -0.0519   0.0399   1.0000
   9.000   1.1842   0.02972   0.02197  -0.0510   0.0381   1.0000
   9.250   1.2044   0.03126   0.02370  -0.0499   0.0360   1.0000
   9.500   1.2225   0.03262   0.02517  -0.0488   0.0338   1.0000
   9.750   1.2412   0.03521   0.02783  -0.0481   0.0321   1.0000
  10.000   1.2549   0.03915   0.03216  -0.0467   0.0311   1.0000
  10.250   1.2649   0.04161   0.03501  -0.0446   0.0306   1.0000
  10.500   1.2705   0.04429   0.03809  -0.0421   0.0299   1.0000
  10.750   1.2717   0.04708   0.04128  -0.0393   0.0290   1.0000
  11.000   1.2681   0.04990   0.04443  -0.0362   0.0282   1.0000
  11.250   1.2586   0.05277   0.04758  -0.0327   0.0278   1.0000
  11.500   1.2428   0.05638   0.05148  -0.0294   0.0278   1.0000
  11.750   1.2239   0.06032   0.05571  -0.0269   0.0279   1.0000
  12.000   1.2023   0.06478   0.06044  -0.0255   0.0281   1.0000
  12.250   1.1787   0.06988   0.06578  -0.0254   0.0283   1.0000
  12.500   1.1538   0.07570   0.07182  -0.0266   0.0286   1.0000
  12.750   1.1276   0.08245   0.07877  -0.0295   0.0289   1.0000
  13.000   1.1013   0.09022   0.08669  -0.0339   0.0293   1.0000
  13.250   1.0735   0.09963   0.09626  -0.0404   0.0297   1.0000
  13.500   1.0464   0.11036   0.10708  -0.0477   0.0305   1.0000
  13.750   1.0244   0.12085   0.11760  -0.0538   0.0312   1.0000
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