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HQ 2.5/10 AIRFOIL (hq2510-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/10 AIRFOIL (hq2510-il)
Reynolds number: 50,000
Max Cl/Cd: 36.97 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2510-il-50000.txt
Download as CSV file: xf-hq2510-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/10 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3214   0.11382   0.10741  -0.0266   1.0000   0.2125
  -9.750  -0.3066   0.10923   0.10283  -0.0259   1.0000   0.2212
  -9.500  -0.3295   0.10843   0.10216  -0.0274   1.0000   0.2274
  -9.250  -0.3161   0.10405   0.09776  -0.0264   1.0000   0.2406
  -9.000  -0.3100   0.10047   0.09423  -0.0257   1.0000   0.2541
  -8.750  -0.3074   0.09727   0.09109  -0.0249   1.0000   0.2681
  -8.500  -0.3093   0.09442   0.08832  -0.0242   1.0000   0.2827
  -8.250  -0.3102   0.09153   0.08551  -0.0231   1.0000   0.2971
  -8.000  -0.3129   0.08876   0.08284  -0.0219   1.0000   0.3114
  -7.750  -0.2982   0.08437   0.07848  -0.0203   1.0000   0.3279
  -7.500  -0.2915   0.08098   0.07514  -0.0186   1.0000   0.3444
  -7.250  -0.2897   0.07803   0.07227  -0.0168   1.0000   0.3609
  -7.000  -0.2930   0.07550   0.06984  -0.0147   1.0000   0.3780
  -6.750  -0.3721   0.08337   0.07732  -0.0101   1.0000   0.3936
  -6.500  -0.3612   0.08000   0.07400  -0.0078   1.0000   0.4153
  -6.250  -0.3855   0.07989   0.07409  -0.0030   1.0000   0.4373
  -6.000  -0.3598   0.07549   0.06967  -0.0017   1.0000   0.4610
  -5.750  -0.3556   0.07312   0.06738   0.0017   1.0000   0.4885
  -5.250  -0.4499   0.05210   0.04548  -0.0411   1.0000   0.1559
  -5.000  -0.4318   0.04693   0.03989  -0.0422   1.0000   0.1378
  -4.750  -0.4104   0.04240   0.03463  -0.0433   1.0000   0.1251
  -4.500  -0.3852   0.03845   0.02964  -0.0439   1.0000   0.1165
  -4.250  -0.3615   0.03553   0.02614  -0.0435   1.0000   0.1157
  -4.000  -0.3405   0.03298   0.02358  -0.0429   1.0000   0.1243
  -3.750  -0.3148   0.03064   0.02065  -0.0424   1.0000   0.1313
  -3.500  -0.2899   0.02880   0.01848  -0.0417   1.0000   0.1438
  -3.250  -0.2664   0.02694   0.01667  -0.0408   1.0000   0.1617
  -3.000  -0.2433   0.02552   0.01523  -0.0397   1.0000   0.1880
  -2.750  -0.2205   0.02419   0.01393  -0.0383   1.0000   0.2151
  -2.500  -0.1962   0.02260   0.01271  -0.0378   1.0000   0.2803
  -2.250  -0.1947   0.02042   0.01312  -0.0299   1.0000   0.7162
  -2.000  -0.2044   0.02024   0.01318  -0.0192   1.0000   0.8507
  -1.750  -0.1546   0.01997   0.01253  -0.0216   1.0000   1.0000
  -1.500  -0.1371   0.01993   0.01210  -0.0219   1.0000   1.0000
  -1.250  -0.1155   0.02005   0.01184  -0.0227   1.0000   1.0000
  -1.000  -0.0927   0.02027   0.01168  -0.0235   1.0000   1.0000
  -0.750  -0.0697   0.02057   0.01166  -0.0242   1.0000   1.0000
  -0.500  -0.0470   0.02093   0.01174  -0.0248   1.0000   1.0000
  -0.250  -0.0247   0.02134   0.01189  -0.0253   1.0000   1.0000
   0.000  -0.0028   0.02180   0.01210  -0.0257   1.0000   1.0000
   0.250   0.0187   0.02230   0.01240  -0.0260   1.0000   1.0000
   0.500   0.0397   0.02285   0.01278  -0.0263   1.0000   1.0000
   0.750   0.0604   0.02344   0.01322  -0.0265   1.0000   1.0000
   1.000   0.0806   0.02408   0.01373  -0.0268   1.0000   1.0000
   1.250   0.1003   0.02477   0.01429  -0.0270   1.0000   1.0000
   1.500   0.1197   0.02551   0.01493  -0.0272   1.0000   1.0000
   1.750   0.1596   0.02680   0.01614  -0.0314   0.9894   1.0000
   2.000   0.2081   0.02827   0.01754  -0.0370   0.9734   1.0000
   2.250   0.2588   0.02970   0.01894  -0.0426   0.9560   1.0000
   2.500   0.3025   0.03081   0.02004  -0.0468   0.9361   1.0000
   2.750   0.3518   0.03189   0.02118  -0.0516   0.9157   1.0000
   3.000   0.3935   0.03278   0.02211  -0.0548   0.8948   1.0000
   3.250   0.4394   0.03358   0.02299  -0.0584   0.8744   1.0000
   3.500   0.4788   0.03427   0.02382  -0.0608   0.8530   1.0000
   3.750   0.5269   0.03472   0.02441  -0.0639   0.8318   1.0000
   4.000   0.5642   0.03509   0.02493  -0.0653   0.8084   1.0000
   4.250   0.6132   0.03501   0.02504  -0.0676   0.7854   1.0000
   4.500   0.6698   0.03428   0.02463  -0.0701   0.7621   1.0000
   4.750   0.7146   0.03355   0.02414  -0.0706   0.7367   1.0000
   5.000   0.7608   0.03235   0.02325  -0.0705   0.7106   1.0000
   5.250   0.8082   0.03072   0.02190  -0.0700   0.6830   1.0000
   5.500   0.8557   0.02880   0.02020  -0.0689   0.6523   1.0000
   5.750   0.8910   0.02761   0.01914  -0.0668   0.6149   1.0000
   6.000   0.9243   0.02667   0.01829  -0.0646   0.5735   1.0000
   6.250   0.9534   0.02631   0.01785  -0.0624   0.5294   1.0000
   6.500   0.9796   0.02650   0.01785  -0.0603   0.4850   1.0000
   6.750   1.0031   0.02721   0.01836  -0.0584   0.4424   1.0000
   7.000   1.0239   0.02835   0.01939  -0.0566   0.4032   1.0000
   7.250   1.0447   0.02967   0.02071  -0.0550   0.3676   1.0000
   7.500   1.0657   0.03112   0.02211  -0.0535   0.3354   1.0000
   7.750   1.0873   0.03281   0.02378  -0.0522   0.3069   1.0000
   8.000   1.1070   0.03459   0.02561  -0.0507   0.2800   1.0000
   8.250   1.1259   0.03659   0.02771  -0.0492   0.2550   1.0000
   8.500   1.1428   0.03851   0.02970  -0.0474   0.2293   1.0000
   8.750   1.1556   0.04031   0.03157  -0.0451   0.2009   1.0000
   9.000   1.1617   0.04127   0.03224  -0.0421   0.1640   1.0000
   9.250   1.1589   0.04280   0.03374  -0.0382   0.1307   1.0000
   9.500   1.1604   0.04517   0.03614  -0.0351   0.1055   1.0000
   9.750   1.1675   0.04792   0.03891  -0.0328   0.0896   1.0000
  10.000   1.1750   0.05186   0.04321  -0.0307   0.0817   1.0000
  10.250   1.1846   0.05557   0.04716  -0.0290   0.0766   1.0000
  10.500   1.1915   0.06014   0.05190  -0.0275   0.0736   1.0000
  10.750   1.1812   0.06422   0.05649  -0.0247   0.0728   1.0000
  11.000   1.1664   0.06817   0.06081  -0.0219   0.0724   1.0000
  11.250   1.1481   0.07218   0.06512  -0.0195   0.0724   1.0000
  11.500   1.1297   0.07656   0.06973  -0.0182   0.0727   1.0000
  11.750   1.1086   0.08139   0.07478  -0.0179   0.0730   1.0000
  12.000   1.0886   0.08672   0.08027  -0.0186   0.0734   1.0000
  12.250   1.0699   0.09254   0.08622  -0.0201   0.0739   1.0000
  12.500   0.9627   0.11355   0.10752  -0.0379   0.0913   1.0000
  12.750   0.9596   0.11893   0.11288  -0.0398   0.0883   1.0000
  13.000   0.9547   0.12545   0.11939  -0.0423   0.0871   1.0000
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