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HQ 2.0/8 AIRFOIL (hq208-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.0/8 AIRFOIL (hq208-il)
Reynolds number: 50,000
Max Cl/Cd: 37.81 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq208-il-50000.txt
Download as CSV file: xf-hq208-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/8 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4458   0.09402   0.08753  -0.0107   1.0000   0.2645
  -7.500  -0.4434   0.09127   0.08485  -0.0100   1.0000   0.2824
  -7.250  -0.4546   0.08956   0.08329  -0.0095   1.0000   0.2994
  -7.000  -0.4421   0.08615   0.07985  -0.0072   1.0000   0.3257
  -6.750  -0.4244   0.08250   0.07622  -0.0041   1.0000   0.3612
  -6.500  -0.4204   0.08005   0.07384  -0.0015   1.0000   0.3924
  -6.250  -0.4245   0.07825   0.07216   0.0016   1.0000   0.4222
  -6.000  -0.3980   0.07393   0.06783   0.0038   1.0000   0.4569
  -4.750  -0.3850   0.04303   0.03517  -0.0440   1.0000   0.1351
  -4.500  -0.3617   0.03904   0.03061  -0.0441   1.0000   0.1211
  -4.250  -0.3387   0.03541   0.02648  -0.0437   1.0000   0.1126
  -4.000  -0.3134   0.03263   0.02302  -0.0430   1.0000   0.1075
  -3.750  -0.2890   0.03000   0.01997  -0.0421   1.0000   0.1066
  -3.500  -0.2635   0.02789   0.01731  -0.0409   1.0000   0.1089
  -3.250  -0.2404   0.02598   0.01529  -0.0400   1.0000   0.1218
  -3.000  -0.2164   0.02409   0.01333  -0.0385   1.0000   0.1344
  -2.750  -0.1931   0.02242   0.01168  -0.0370   1.0000   0.1635
  -2.500  -0.1690   0.02032   0.00999  -0.0359   1.0000   0.2308
  -2.250  -0.1392   0.01665   0.00940  -0.0274   1.0000   1.0000
  -2.000  -0.1282   0.01648   0.00877  -0.0259   1.0000   1.0000
  -1.750  -0.1099   0.01644   0.00827  -0.0255   1.0000   1.0000
  -1.500  -0.0889   0.01649   0.00789  -0.0254   1.0000   1.0000
  -1.250  -0.0671   0.01659   0.00763  -0.0253   1.0000   1.0000
  -1.000  -0.0449   0.01675   0.00746  -0.0253   1.0000   1.0000
  -0.750  -0.0228   0.01694   0.00732  -0.0252   1.0000   1.0000
  -0.500  -0.0009   0.01718   0.00731  -0.0251   1.0000   1.0000
  -0.250   0.0209   0.01745   0.00736  -0.0249   1.0000   1.0000
   0.000   0.0424   0.01776   0.00748  -0.0248   1.0000   1.0000
   0.250   0.0637   0.01810   0.00767  -0.0246   1.0000   1.0000
   0.500   0.0847   0.01848   0.00788  -0.0245   1.0000   1.0000
   0.750   0.1055   0.01890   0.00818  -0.0243   1.0000   1.0000
   1.000   0.1260   0.01936   0.00855  -0.0242   1.0000   1.0000
   1.250   0.1461   0.01986   0.00898  -0.0241   1.0000   1.0000
   1.500   0.1660   0.02041   0.00948  -0.0240   1.0000   1.0000
   1.750   0.1854   0.02101   0.01004  -0.0239   1.0000   1.0000
   2.000   0.2046   0.02165   0.01067  -0.0239   1.0000   1.0000
   2.250   0.2232   0.02236   0.01137  -0.0240   1.0000   1.0000
   2.500   0.2414   0.02314   0.01216  -0.0240   1.0000   1.0000
   2.750   0.2879   0.02446   0.01358  -0.0296   0.9852   1.0000
   3.000   0.3555   0.02588   0.01520  -0.0383   0.9577   1.0000
   3.250   0.4133   0.02689   0.01641  -0.0448   0.9317   1.0000
   3.500   0.4694   0.02763   0.01740  -0.0503   0.9049   1.0000
   3.750   0.5266   0.02807   0.01822  -0.0553   0.8767   1.0000
   4.000   0.5915   0.02799   0.01855  -0.0605   0.8470   1.0000
   4.250   0.6447   0.02759   0.01856  -0.0630   0.8130   1.0000
   4.500   0.7040   0.02631   0.01784  -0.0645   0.7777   1.0000
   4.750   0.7461   0.02503   0.01692  -0.0627   0.7346   1.0000
   5.000   0.7847   0.02338   0.01551  -0.0593   0.6840   1.0000
   5.250   0.8100   0.02232   0.01446  -0.0546   0.6188   1.0000
   5.500   0.8296   0.02194   0.01395  -0.0500   0.5421   1.0000
   5.750   0.8456   0.02243   0.01402  -0.0460   0.4583   1.0000
   6.000   0.8578   0.02381   0.01479  -0.0424   0.3632   1.0000
   6.250   0.8708   0.02641   0.01650  -0.0393   0.2639   1.0000
   6.500   0.8919   0.02899   0.01873  -0.0377   0.2054   1.0000
   6.750   0.9149   0.03112   0.02080  -0.0365   0.1726   1.0000
   7.000   0.9430   0.03396   0.02366  -0.0358   0.1538   1.0000
   7.250   0.9640   0.03638   0.02636  -0.0344   0.1341   1.0000
   7.500   0.9860   0.03995   0.03032  -0.0330   0.1216   1.0000
   7.750   1.0030   0.04385   0.03475  -0.0313   0.1102   1.0000
   8.000   1.0155   0.04745   0.03868  -0.0296   0.0982   1.0000
   8.250   1.0278   0.05122   0.04260  -0.0282   0.0883   1.0000
   8.500   1.0308   0.05575   0.04783  -0.0260   0.0860   1.0000
   8.750   1.0311   0.06080   0.05340  -0.0242   0.0861   1.0000
   9.000   1.0273   0.06597   0.05897  -0.0228   0.0869   1.0000
   9.250   1.0214   0.07117   0.06447  -0.0216   0.0880   1.0000
   9.500   1.0184   0.07658   0.07004  -0.0210   0.0892   1.0000
   9.750   0.9835   0.08118   0.07504  -0.0204   0.0925   1.0000
  10.000   0.9446   0.08710   0.08109  -0.0224   0.0962   1.0000
  10.250   0.9237   0.09383   0.08784  -0.0258   0.0993   1.0000
  10.500   0.9171   0.10016   0.09416  -0.0282   0.1016   1.0000
  10.750   0.8600   0.12034   0.11407  -0.0480   0.1514   1.0000
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