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HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il)
Reynolds number: 100,000
Max Cl/Cd: 56.21 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2590sm-il-100000-n5.txt
Download as CSV file: xf-hq2590sm-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3488   0.08527   0.08051  -0.0387   1.0000   0.0402
  -9.000  -0.4225   0.09165   0.08656  -0.0368   1.0000   0.0373
  -8.750  -0.4208   0.08821   0.08316  -0.0368   1.0000   0.0356
  -8.500  -0.4237   0.08437   0.07940  -0.0378   1.0000   0.0343
  -8.250  -0.4305   0.08044   0.07556  -0.0390   1.0000   0.0332
  -8.000  -0.4425   0.07649   0.07172  -0.0402   1.0000   0.0323
  -7.500  -0.4763   0.06233   0.05740  -0.0507   1.0000   0.0287
  -7.250  -0.4812   0.05876   0.05372  -0.0502   1.0000   0.0287
  -7.000  -0.4863   0.05493   0.04983  -0.0495   1.0000   0.0292
  -6.750  -0.4826   0.05366   0.04864  -0.0478   1.0000   0.0304
  -6.500  -0.4700   0.05094   0.04577  -0.0489   0.9979   0.0318
  -6.250  -0.4437   0.04514   0.03951  -0.0539   0.9920   0.0319
  -6.000  -0.4157   0.03974   0.03357  -0.0577   0.9864   0.0316
  -5.750  -0.3850   0.03545   0.02871  -0.0607   0.9819   0.0319
  -5.500  -0.3561   0.03263   0.02546  -0.0625   0.9765   0.0336
  -5.250  -0.3240   0.02997   0.02227  -0.0644   0.9724   0.0358
  -5.000  -0.2902   0.02735   0.01911  -0.0661   0.9694   0.0367
  -4.750  -0.2619   0.02541   0.01672  -0.0665   0.9641   0.0375
  -4.500  -0.2297   0.02399   0.01489  -0.0674   0.9600   0.0389
  -4.250  -0.1975   0.02235   0.01323  -0.0689   0.9570   0.0421
  -4.000  -0.1669   0.02125   0.01200  -0.0696   0.9530   0.0443
  -3.750  -0.1381   0.02025   0.01088  -0.0698   0.9482   0.0464
  -3.500  -0.1065   0.01937   0.00990  -0.0706   0.9447   0.0491
  -3.250  -0.0732   0.01854   0.00906  -0.0720   0.9419   0.0543
  -3.000  -0.0455   0.01801   0.00850  -0.0722   0.9366   0.0612
  -2.750  -0.0154   0.01739   0.00784  -0.0729   0.9322   0.0698
  -2.500   0.0176   0.01683   0.00732  -0.0742   0.9290   0.0936
  -2.250   0.0509   0.01565   0.00679  -0.0762   0.9265   0.2259
  -2.000   0.0688   0.01454   0.00706  -0.0746   0.9202   0.5827
  -1.750   0.0943   0.01449   0.00724  -0.0735   0.9158   0.6855
  -1.500   0.1214   0.01447   0.00733  -0.0725   0.9125   0.7481
  -1.250   0.1386   0.01452   0.00747  -0.0695   0.9058   0.7981
  -1.000   0.1634   0.01448   0.00742  -0.0683   0.9010   0.8314
  -0.750   0.1952   0.01435   0.00720  -0.0686   0.8948   0.8492
  -0.500   0.2280   0.01412   0.00689  -0.0690   0.8853   0.8660
  -0.250   0.2590   0.01387   0.00657  -0.0690   0.8739   0.8846
   0.000   0.2931   0.01361   0.00627  -0.0697   0.8650   0.9044
   0.250   0.3284   0.01346   0.00609  -0.0709   0.8571   0.9290
   0.500   0.3708   0.01332   0.00592  -0.0737   0.8508   0.9620
   0.750   0.4050   0.01328   0.00583  -0.0751   0.8424   1.0000
   1.000   0.4343   0.01330   0.00580  -0.0755   0.8338   1.0000
   1.250   0.4653   0.01329   0.00574  -0.0760   0.8255   1.0000
   1.500   0.4925   0.01335   0.00578  -0.0759   0.8149   1.0000
   1.750   0.5214   0.01336   0.00579  -0.0760   0.8047   1.0000
   2.000   0.5513   0.01334   0.00575  -0.0761   0.7945   1.0000
   2.250   0.5786   0.01338   0.00579  -0.0758   0.7818   1.0000
   2.500   0.6059   0.01341   0.00584  -0.0754   0.7679   1.0000
   2.750   0.6333   0.01343   0.00589  -0.0750   0.7527   1.0000
   3.000   0.6602   0.01346   0.00594  -0.0745   0.7353   1.0000
   3.250   0.6861   0.01351   0.00603  -0.0738   0.7140   1.0000
   3.500   0.7122   0.01355   0.00611  -0.0731   0.6893   1.0000
   3.750   0.7372   0.01362   0.00619  -0.0722   0.6562   1.0000
   4.000   0.7621   0.01371   0.00618  -0.0711   0.6072   1.0000
   4.250   0.7858   0.01398   0.00609  -0.0696   0.5383   1.0000
   4.500   0.8069   0.01457   0.00630  -0.0681   0.4777   1.0000
   4.750   0.8283   0.01522   0.00668  -0.0670   0.4323   1.0000
   5.000   0.8507   0.01579   0.00712  -0.0661   0.3972   1.0000
   5.250   0.8735   0.01633   0.00759  -0.0653   0.3678   1.0000
   5.500   0.8962   0.01687   0.00811  -0.0645   0.3391   1.0000
   5.750   0.9185   0.01744   0.00863  -0.0636   0.3076   1.0000
   6.000   0.9403   0.01804   0.00917  -0.0627   0.2735   1.0000
   6.250   0.9611   0.01874   0.00975  -0.0618   0.2303   1.0000
   6.500   0.9796   0.01971   0.01045  -0.0606   0.1754   1.0000
   6.750   0.9976   0.02085   0.01130  -0.0595   0.1334   1.0000
   7.000   1.0163   0.02194   0.01225  -0.0584   0.1074   1.0000
   7.250   1.0348   0.02303   0.01327  -0.0573   0.0906   1.0000
   7.500   1.0529   0.02413   0.01436  -0.0561   0.0778   1.0000
   7.750   1.0709   0.02521   0.01558  -0.0548   0.0684   1.0000
   8.000   1.0871   0.02648   0.01692  -0.0532   0.0615   1.0000
   8.250   1.1033   0.02771   0.01821  -0.0518   0.0555   1.0000
   8.500   1.1189   0.02906   0.01965  -0.0503   0.0507   1.0000
   8.750   1.1355   0.03038   0.02112  -0.0489   0.0469   1.0000
   9.000   1.1511   0.03182   0.02266  -0.0474   0.0441   1.0000
   9.250   1.1662   0.03365   0.02452  -0.0461   0.0417   1.0000
   9.500   1.1837   0.03515   0.02630  -0.0449   0.0390   1.0000
   9.750   1.1993   0.03676   0.02810  -0.0435   0.0364   1.0000
  10.000   1.2139   0.03854   0.03003  -0.0422   0.0347   1.0000
  10.250   1.2256   0.04040   0.03196  -0.0408   0.0329   1.0000
  10.500   1.2358   0.04267   0.03449  -0.0390   0.0313   1.0000
  10.750   1.2429   0.04488   0.03709  -0.0370   0.0296   1.0000
  11.000   1.2475   0.04747   0.03999  -0.0349   0.0286   1.0000
  11.250   1.2483   0.05009   0.04290  -0.0327   0.0276   1.0000
  11.500   1.2463   0.05265   0.04570  -0.0307   0.0268   1.0000
  11.750   1.2434   0.05514   0.04837  -0.0290   0.0259   1.0000
  12.000   1.2397   0.05780   0.05117  -0.0277   0.0252   1.0000
  12.250   1.2335   0.06112   0.05461  -0.0268   0.0244   1.0000
  12.500   1.2199   0.06532   0.05908  -0.0263   0.0241   1.0000
  12.750   1.2031   0.07006   0.06414  -0.0265   0.0239   1.0000
  13.000   1.1845   0.07544   0.06980  -0.0278   0.0237   1.0000
  13.250   1.1641   0.08160   0.07622  -0.0302   0.0237   1.0000
  13.500   1.1430   0.08857   0.08343  -0.0338   0.0237   1.0000
  13.750   1.1211   0.09649   0.09154  -0.0386   0.0239   1.0000
  14.000   1.0984   0.10549   0.10071  -0.0445   0.0241   1.0000
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