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HQ 2.5/9 B AIRFOIL (hq259b-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/9 B AIRFOIL (hq259b-il)
Reynolds number: 100,000
Max Cl/Cd: 56.2 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq259b-il-100000-n5.txt
Download as CSV file: xf-hq259b-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/9 B AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4363   0.12013   0.11480  -0.0276   1.0000   0.0502
 -10.500  -0.4405   0.11699   0.11173  -0.0312   1.0000   0.0508
 -10.250  -0.4411   0.11348   0.10828  -0.0337   1.0000   0.0509
 -10.000  -0.4409   0.10971   0.10455  -0.0359   1.0000   0.0510
  -9.750  -0.4405   0.10589   0.10079  -0.0378   1.0000   0.0511
  -9.500  -0.4410   0.10189   0.09684  -0.0398   1.0000   0.0511
  -9.250  -0.4418   0.09787   0.09287  -0.0417   1.0000   0.0511
  -9.000  -0.4226   0.09161   0.08652  -0.0368   1.0000   0.0373
  -8.750  -0.4207   0.08819   0.08315  -0.0368   1.0000   0.0356
  -8.500  -0.4235   0.08441   0.07944  -0.0378   1.0000   0.0343
  -8.250  -0.4303   0.08048   0.07560  -0.0390   1.0000   0.0332
  -8.000  -0.4424   0.07649   0.07173  -0.0402   1.0000   0.0323
  -7.500  -0.4755   0.06247   0.05757  -0.0504   1.0000   0.0286
  -6.750  -0.4827   0.05365   0.04862  -0.0478   1.0000   0.0304
  -6.500  -0.4700   0.05078   0.04559  -0.0490   0.9978   0.0317
  -6.250  -0.4437   0.04514   0.03951  -0.0539   0.9920   0.0319
  -6.000  -0.4156   0.03972   0.03354  -0.0577   0.9863   0.0316
  -5.750  -0.3850   0.03547   0.02873  -0.0607   0.9819   0.0320
  -5.500  -0.3561   0.03262   0.02545  -0.0625   0.9765   0.0336
  -5.250  -0.3240   0.02997   0.02227  -0.0644   0.9723   0.0359
  -5.000  -0.2903   0.02735   0.01911  -0.0661   0.9694   0.0367
  -4.750  -0.2619   0.02541   0.01671  -0.0665   0.9641   0.0375
  -4.500  -0.2297   0.02398   0.01489  -0.0674   0.9600   0.0389
  -4.250  -0.1975   0.02236   0.01324  -0.0689   0.9570   0.0421
  -4.000  -0.1669   0.02125   0.01200  -0.0696   0.9529   0.0443
  -3.750  -0.1382   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   0.00907  -0.0720   0.9419   0.0543
  -3.000  -0.0455   0.01801   0.00850  -0.0722   0.9366   0.0612
  -2.750  -0.0154   0.01740   0.00784  -0.0729   0.9322   0.0697
  -2.500   0.0176   0.01683   0.00732  -0.0742   0.9290   0.0937
  -2.250   0.0509   0.01565   0.00679  -0.0762   0.9265   0.2262
  -2.000   0.0688   0.01454   0.00706  -0.0746   0.9202   0.5828
  -1.750   0.0943   0.01449   0.00724  -0.0735   0.9158   0.6854
  -1.500   0.1214   0.01447   0.00733  -0.0725   0.9125   0.7483
  -1.250   0.1385   0.01452   0.00747  -0.0695   0.9058   0.7981
  -1.000   0.1634   0.01448   0.00742  -0.0683   0.9010   0.8315
  -0.750   0.1952   0.01435   0.00720  -0.0686   0.8948   0.8492
  -0.500   0.2279   0.01412   0.00689  -0.0690   0.8853   0.8660
   0.000   0.2931   0.01362   0.00627  -0.0697   0.8650   0.9044
   0.250   0.3283   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   0.00581  -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   0.8048   1.0000
   2.000   0.5513   0.01334   0.00575  -0.0761   0.7946   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   0.7680   1.0000
   2.750   0.6333   0.01342   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   0.6563   1.0000
   4.000   0.7621   0.01371   0.00618  -0.0711   0.6071   1.0000
   4.250   0.7857   0.01398   0.00609  -0.0696   0.5384   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   0.3393   1.0000
   5.750   0.9185   0.01744   0.00863  -0.0636   0.3077   1.0000
   6.000   0.9403   0.01804   0.00917  -0.0627   0.2736   1.0000
   6.250   0.9611   0.01873   0.00975  -0.0618   0.2305   1.0000
   6.500   0.9796   0.01971   0.01045  -0.0606   0.1755   1.0000
   6.750   0.9976   0.02085   0.01130  -0.0595   0.1333   1.0000
   7.000   1.0163   0.02194   0.01225  -0.0584   0.1075   1.0000
   7.250   1.0347   0.02303   0.01327  -0.0573   0.0907   1.0000
   7.500   1.0528   0.02413   0.01436  -0.0561   0.0778   1.0000
   7.750   1.0709   0.02521   0.01558  -0.0548   0.0683   1.0000
   8.000   1.0871   0.02648   0.01692  -0.0532   0.0615   1.0000
   8.250   1.1033   0.02771   0.01822  -0.0518   0.0555   1.0000
   8.500   1.1188   0.02906   0.01965  -0.0503   0.0507   1.0000
   8.750   1.1355   0.03038   0.02111  -0.0489   0.0469   1.0000
   9.000   1.1510   0.03182   0.02266  -0.0474   0.0441   1.0000
   9.250   1.1661   0.03366   0.02452  -0.0461   0.0417   1.0000
   9.500   1.1836   0.03515   0.02629  -0.0448   0.0390   1.0000
   9.750   1.1993   0.03676   0.02810  -0.0435   0.0364   1.0000
  10.000   1.2138   0.03853   0.03003  -0.0422   0.0347   1.0000
  10.250   1.2255   0.04040   0.03195  -0.0407   0.0329   1.0000
  10.500   1.2356   0.04266   0.03449  -0.0390   0.0312   1.0000
  10.750   1.2428   0.04488   0.03708  -0.0370   0.0297   1.0000
  11.000   1.2474   0.04746   0.03998  -0.0349   0.0286   1.0000
  11.250   1.2482   0.05010   0.04290  -0.0327   0.0276   1.0000
  11.500   1.2463   0.05263   0.04568  -0.0306   0.0268   1.0000
  11.750   1.2432   0.05514   0.04837  -0.0290   0.0259   1.0000
  12.000   1.2396   0.05778   0.05115  -0.0277   0.0252   1.0000
  12.250   1.2334   0.06110   0.05459  -0.0268   0.0245   1.0000
  12.500   1.2197   0.06531   0.05907  -0.0262   0.0241   1.0000
  12.750   1.2030   0.07002   0.06410  -0.0265   0.0239   1.0000
  13.000   1.1844   0.07541   0.06977  -0.0278   0.0237   1.0000
  13.250   1.1641   0.08157   0.07619  -0.0302   0.0237   1.0000
  13.500   1.1427   0.08858   0.08343  -0.0338   0.0237   1.0000
  13.750   1.1210   0.09646   0.09151  -0.0385   0.0239   1.0000
  14.000   1.0986   0.10538   0.10059  -0.0444   0.0241   1.0000
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