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HQ 2.0/9 AIRFOIL (hq209-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.0/9 AIRFOIL (hq209-il)
Reynolds number: 100,000
Max Cl/Cd: 53.34 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq209-il-100000-n5.txt
Download as CSV file: xf-hq209-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/9 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4545   0.10500   0.09993  -0.0221   1.0000   0.0298
  -9.500  -0.4526   0.10085   0.09582  -0.0235   1.0000   0.0277
  -9.250  -0.4530   0.09628   0.09131  -0.0256   1.0000   0.0259
  -8.750  -0.4590   0.08455   0.07971  -0.0338   1.0000   0.0217
  -8.500  -0.4614   0.08025   0.07548  -0.0355   1.0000   0.0213
  -8.250  -0.4657   0.07580   0.07110  -0.0379   1.0000   0.0210
  -8.000  -0.4738   0.07082   0.06619  -0.0416   1.0000   0.0208
  -7.750  -0.4790   0.06603   0.06138  -0.0446   1.0000   0.0205
  -7.500  -0.4838   0.06142   0.05673  -0.0463   1.0000   0.0203
  -7.250  -0.4864   0.05731   0.05253  -0.0471   1.0000   0.0200
  -7.000  -0.4880   0.05302   0.04809  -0.0472   1.0000   0.0198
  -6.750  -0.4872   0.04903   0.04391  -0.0468   1.0000   0.0197
  -6.500  -0.4845   0.04508   0.03970  -0.0459   1.0000   0.0195
  -6.250  -0.4792   0.04133   0.03563  -0.0447   1.0000   0.0195
  -6.000  -0.4708   0.03769   0.03160  -0.0434   1.0000   0.0195
  -5.750  -0.4591   0.03435   0.02781  -0.0421   1.0000   0.0196
  -5.500  -0.4441   0.03118   0.02414  -0.0409   1.0000   0.0201
  -5.250  -0.4135   0.02849   0.02079  -0.0420   0.9961   0.0222
  -5.000  -0.3829   0.02583   0.01776  -0.0438   0.9915   0.0244
  -4.750  -0.3499   0.02368   0.01525  -0.0450   0.9870   0.0258
  -4.500  -0.3170   0.02185   0.01314  -0.0460   0.9828   0.0280
  -4.250  -0.2852   0.02033   0.01139  -0.0467   0.9776   0.0308
  -4.000  -0.2516   0.01913   0.01012  -0.0482   0.9733   0.0372
  -3.750  -0.2208   0.01811   0.00899  -0.0489   0.9674   0.0469
  -3.500  -0.1880   0.01725   0.00810  -0.0503   0.9621   0.0669
  -3.250  -0.1540   0.01646   0.00734  -0.0519   0.9574   0.0979
  -3.000  -0.1242   0.01556   0.00676  -0.0529   0.9508   0.1611
  -2.750  -0.0928   0.01419   0.00632  -0.0546   0.9464   0.3762
  -2.500  -0.0670   0.01361   0.00643  -0.0540   0.9396   0.5801
  -2.250  -0.0371   0.01351   0.00641  -0.0539   0.9338   0.6642
  -2.000  -0.0094   0.01348   0.00641  -0.0532   0.9271   0.7185
  -1.750   0.0184   0.01345   0.00639  -0.0525   0.9206   0.7664
  -1.500   0.0445   0.01339   0.00634  -0.0514   0.9139   0.8075
  -1.250   0.0718   0.01329   0.00620  -0.0506   0.9071   0.8394
  -1.000   0.1021   0.01319   0.00604  -0.0507   0.9005   0.8610
  -0.750   0.1338   0.01310   0.00588  -0.0513   0.8935   0.8777
  -0.500   0.1678   0.01301   0.00573  -0.0523   0.8868   0.8959
  -0.250   0.2046   0.01292   0.00559  -0.0539   0.8796   0.9159
   0.000   0.2456   0.01284   0.00546  -0.0565   0.8727   0.9380
   0.250   0.2882   0.01275   0.00533  -0.0596   0.8653   0.9645
   0.500   0.3282   0.01270   0.00523  -0.0623   0.8566   1.0000
   0.750   0.3557   0.01270   0.00515  -0.0622   0.8460   1.0000
   1.000   0.3827   0.01268   0.00507  -0.0619   0.8333   1.0000
   1.250   0.4084   0.01266   0.00500  -0.0613   0.8180   1.0000
   1.500   0.4339   0.01265   0.00495  -0.0606   0.8015   1.0000
   1.750   0.4600   0.01265   0.00492  -0.0600   0.7862   1.0000
   2.000   0.4863   0.01269   0.00494  -0.0595   0.7723   1.0000
   2.250   0.5128   0.01275   0.00499  -0.0591   0.7583   1.0000
   2.500   0.5392   0.01280   0.00509  -0.0586   0.7433   1.0000
   2.750   0.5656   0.01286   0.00516  -0.0581   0.7275   1.0000
   3.000   0.5920   0.01293   0.00523  -0.0575   0.7100   1.0000
   3.250   0.6176   0.01303   0.00536  -0.0569   0.6901   1.0000
   3.500   0.6436   0.01312   0.00550  -0.0562   0.6686   1.0000
   3.750   0.6690   0.01325   0.00564  -0.0555   0.6434   1.0000
   4.000   0.6940   0.01341   0.00579  -0.0546   0.6136   1.0000
   4.250   0.7184   0.01362   0.00597  -0.0537   0.5775   1.0000
   4.500   0.7420   0.01391   0.00615  -0.0526   0.5332   1.0000
   4.750   0.7641   0.01434   0.00643  -0.0513   0.4783   1.0000
   5.000   0.7848   0.01495   0.00676  -0.0500   0.4171   1.0000
   5.250   0.8046   0.01568   0.00721  -0.0487   0.3568   1.0000
   5.500   0.8247   0.01646   0.00773  -0.0475   0.3044   1.0000
   5.750   0.8454   0.01720   0.00832  -0.0466   0.2659   1.0000
   6.000   0.8672   0.01788   0.00901  -0.0458   0.2347   1.0000
   6.250   0.8886   0.01860   0.00968  -0.0449   0.2000   1.0000
   6.500   0.9090   0.01943   0.01038  -0.0440   0.1536   1.0000
   6.750   0.9279   0.02050   0.01124  -0.0430   0.1141   1.0000
   7.000   0.9464   0.02166   0.01229  -0.0418   0.0925   1.0000
   7.250   0.9652   0.02278   0.01341  -0.0406   0.0780   1.0000
   7.500   0.9839   0.02386   0.01451  -0.0396   0.0654   1.0000
   7.750   1.0019   0.02499   0.01565  -0.0385   0.0555   1.0000
   8.000   1.0210   0.02601   0.01698  -0.0373   0.0484   1.0000
   8.250   1.0366   0.02742   0.01849  -0.0359   0.0421   1.0000
   8.500   1.0537   0.02856   0.01969  -0.0349   0.0317   1.0000
   8.750   1.0702   0.02983   0.02115  -0.0335   0.0234   1.0000
   9.000   1.0826   0.03159   0.02309  -0.0317   0.0188   1.0000
   9.250   1.0941   0.03342   0.02510  -0.0299   0.0163   1.0000
   9.500   1.1042   0.03529   0.02712  -0.0281   0.0150   1.0000
   9.750   1.1089   0.03786   0.02983  -0.0258   0.0139   1.0000
  10.000   1.1164   0.04027   0.03256  -0.0237   0.0133   1.0000
  10.250   1.1213   0.04298   0.03559  -0.0215   0.0128   1.0000
  10.500   1.1230   0.04586   0.03878  -0.0193   0.0125   1.0000
  10.750   1.1208   0.04898   0.04222  -0.0172   0.0122   1.0000
  11.000   1.1141   0.05246   0.04604  -0.0154   0.0120   1.0000
  11.250   1.1043   0.05622   0.05009  -0.0142   0.0119   1.0000
  11.500   1.0911   0.06048   0.05465  -0.0138   0.0118   1.0000
  11.750   1.0763   0.06514   0.05958  -0.0143   0.0118   1.0000
  12.000   1.0590   0.07055   0.06523  -0.0159   0.0118   1.0000
  12.250   1.0408   0.07663   0.07154  -0.0188   0.0118   1.0000
  12.500   1.0213   0.08372   0.07883  -0.0229   0.0120   1.0000
  12.750   1.0010   0.09192   0.08720  -0.0284   0.0122   1.0000
  13.000   0.9799   0.10148   0.09690  -0.0349   0.0124   1.0000
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