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HQ 3.0/10 AIRFOIL (hq3010-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/10 AIRFOIL (hq3010-il)
Reynolds number: 50,000
Max Cl/Cd: 37.72 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3010-il-50000.txt
Download as CSV file: xf-hq3010-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/10 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3622   0.10577   0.09911  -0.0283   1.0000   0.2230
  -8.500  -0.3754   0.10482   0.09830  -0.0285   1.0000   0.2326
  -8.250  -0.3734   0.10202   0.09558  -0.0272   1.0000   0.2466
  -8.000  -0.3698   0.09914   0.09278  -0.0257   1.0000   0.2604
  -7.750  -0.3702   0.09661   0.09035  -0.0240   1.0000   0.2746
  -7.500  -0.3721   0.09429   0.08813  -0.0221   1.0000   0.2889
  -7.250  -0.3778   0.09230   0.08626  -0.0197   1.0000   0.3034
  -7.000  -0.3842   0.09044   0.08449  -0.0168   1.0000   0.3179
  -6.750  -0.3662   0.08652   0.08058  -0.0143   1.0000   0.3397
  -6.500  -0.3766   0.08518   0.07937  -0.0105   1.0000   0.3580
  -6.250  -0.3964   0.08455   0.07890  -0.0059   1.0000   0.3741
  -6.000  -0.3851   0.08160   0.07598  -0.0026   1.0000   0.4003
  -5.750  -0.3821   0.07929   0.07375   0.0012   1.0000   0.4269
  -5.500  -0.3845   0.07755   0.07209   0.0058   1.0000   0.4565
  -4.500  -0.3842   0.04803   0.04086  -0.0462   1.0000   0.1474
  -4.250  -0.3582   0.04331   0.03567  -0.0475   1.0000   0.1296
  -4.000  -0.3278   0.03945   0.03093  -0.0491   1.0000   0.1184
  -3.750  -0.3008   0.03672   0.02756  -0.0497   1.0000   0.1194
  -3.500  -0.2749   0.03396   0.02450  -0.0498   1.0000   0.1224
  -3.250  -0.2480   0.03169   0.02186  -0.0496   1.0000   0.1248
  -3.000  -0.2216   0.02994   0.01966  -0.0492   1.0000   0.1355
  -2.750  -0.1968   0.02826   0.01784  -0.0485   1.0000   0.1499
  -2.500  -0.1737   0.02687   0.01647  -0.0475   1.0000   0.1736
  -2.250  -0.1506   0.02564   0.01522  -0.0464   1.0000   0.2038
  -2.000  -0.1246   0.02437   0.01412  -0.0460   1.0000   0.2471
  -1.750  -0.1116   0.02178   0.01425  -0.0412   1.0000   0.7041
  -1.500  -0.1170   0.02104   0.01397  -0.0307   1.0000   0.9277
  -1.250  -0.0918   0.02099   0.01338  -0.0317   1.0000   1.0000
  -1.000  -0.0665   0.02131   0.01323  -0.0327   1.0000   1.0000
  -0.750  -0.0419   0.02169   0.01319  -0.0336   1.0000   1.0000
  -0.500  -0.0179   0.02212   0.01328  -0.0344   1.0000   1.0000
  -0.250   0.0053   0.02261   0.01347  -0.0350   1.0000   1.0000
   0.000   0.0279   0.02313   0.01373  -0.0356   1.0000   1.0000
   0.250   0.0499   0.02371   0.01405  -0.0360   1.0000   1.0000
   0.500   0.0713   0.02433   0.01447  -0.0363   1.0000   1.0000
   0.750   0.0922   0.02499   0.01496  -0.0367   1.0000   1.0000
   1.000   0.1126   0.02571   0.01552  -0.0370   1.0000   1.0000
   1.250   0.1325   0.02647   0.01614  -0.0372   1.0000   1.0000
   1.500   0.1610   0.02753   0.01708  -0.0393   0.9957   1.0000
   1.750   0.2105   0.02914   0.01856  -0.0450   0.9806   1.0000
   2.000   0.2546   0.03049   0.01982  -0.0497   0.9643   1.0000
   2.250   0.2985   0.03177   0.02105  -0.0541   0.9469   1.0000
   2.500   0.3461   0.03305   0.02231  -0.0588   0.9288   1.0000
   2.750   0.3864   0.03409   0.02336  -0.0621   0.9094   1.0000
   3.000   0.4276   0.03505   0.02434  -0.0652   0.8897   1.0000
   3.250   0.4754   0.03596   0.02531  -0.0691   0.8708   1.0000
   3.500   0.5064   0.03671   0.02614  -0.0703   0.8498   1.0000
   3.750   0.5541   0.03727   0.02682  -0.0735   0.8303   1.0000
   4.000   0.5861   0.03782   0.02746  -0.0743   0.8082   1.0000
   4.250   0.6391   0.03777   0.02763  -0.0773   0.7881   1.0000
   4.500   0.6719   0.03794   0.02795  -0.0775   0.7643   1.0000
   4.750   0.7200   0.03739   0.02761  -0.0789   0.7422   1.0000
   5.000   0.7750   0.03611   0.02664  -0.0804   0.7201   1.0000
   5.250   0.8171   0.03506   0.02583  -0.0800   0.6960   1.0000
   5.500   0.8706   0.03304   0.02409  -0.0801   0.6730   1.0000
   5.750   0.9202   0.03103   0.02236  -0.0795   0.6462   1.0000
   6.000   0.9565   0.02984   0.02133  -0.0778   0.6134   1.0000
   6.250   1.0003   0.02824   0.01978  -0.0766   0.5779   1.0000
   6.500   1.0285   0.02793   0.01946  -0.0745   0.5379   1.0000
   6.750   1.0550   0.02804   0.01953  -0.0725   0.4971   1.0000
   7.000   1.0787   0.02860   0.01998  -0.0706   0.4570   1.0000
   7.250   1.1010   0.02949   0.02072  -0.0688   0.4188   1.0000
   7.500   1.1235   0.03052   0.02154  -0.0671   0.3819   1.0000
   7.750   1.1400   0.03185   0.02287  -0.0650   0.3470   1.0000
   8.000   1.1595   0.03315   0.02403  -0.0632   0.3124   1.0000
   8.250   1.1748   0.03480   0.02566  -0.0611   0.2796   1.0000
   8.500   1.1904   0.03668   0.02753  -0.0591   0.2489   1.0000
   8.750   1.2052   0.03861   0.02943  -0.0571   0.2207   1.0000
   9.000   1.2248   0.04109   0.03187  -0.0558   0.1978   1.0000
   9.250   1.2370   0.04343   0.03442  -0.0536   0.1784   1.0000
   9.500   1.2527   0.04611   0.03724  -0.0520   0.1625   1.0000
   9.750   1.2635   0.04954   0.04102  -0.0499   0.1511   1.0000
  10.000   1.2702   0.05239   0.04412  -0.0476   0.1384   1.0000
  10.250   1.2768   0.05614   0.04812  -0.0454   0.1290   1.0000
  10.500   1.2822   0.05944   0.05160  -0.0432   0.1175   1.0000
  10.750   1.2659   0.06295   0.05565  -0.0394   0.1126   1.0000
  11.000   1.2614   0.06537   0.05814  -0.0368   0.1019   1.0000
  11.250   1.2613   0.06776   0.06046  -0.0346   0.0914   1.0000
  11.500   1.2394   0.07165   0.06470  -0.0314   0.0908   1.0000
  11.750   1.2159   0.07597   0.06930  -0.0292   0.0906   1.0000
  12.000   1.1924   0.08081   0.07438  -0.0282   0.0909   1.0000
  12.250   1.1688   0.08625   0.08001  -0.0283   0.0915   1.0000
  12.500   1.1470   0.09226   0.08616  -0.0294   0.0922   1.0000
  12.750   1.1255   0.09885   0.09287  -0.0315   0.0928   1.0000
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