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HQ 3.0/9 AIRFOIL (hq309-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/9 AIRFOIL (hq309-il)
Reynolds number: 500,000
Max Cl/Cd: 96.32 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq309-il-500000-n5.txt
Download as CSV file: xf-hq309-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/9 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3811   0.08630   0.08411  -0.0364   1.0000   0.0042
  -8.500  -0.3847   0.08281   0.08067  -0.0370   1.0000   0.0042
  -8.250  -0.3894   0.08022   0.07813  -0.0367   1.0000   0.0043
  -8.000  -0.3799   0.07438   0.07231  -0.0432   0.9915   0.0043
  -7.750  -0.3672   0.06888   0.06682  -0.0509   0.9825   0.0044
  -7.500  -0.3452   0.06232   0.06022  -0.0629   0.9751   0.0046
  -7.250  -0.3232   0.05361   0.05139  -0.0767   0.9651   0.0046
  -7.000  -0.3031   0.04594   0.04350  -0.0854   0.9550   0.0047
  -6.750  -0.2821   0.04040   0.03773  -0.0902   0.9458   0.0049
  -6.500  -0.2631   0.03581   0.03288  -0.0924   0.9352   0.0053
  -6.250  -0.2439   0.03072   0.02744  -0.0938   0.9256   0.0057
  -6.000  -0.2246   0.02475   0.02096  -0.0942   0.9169   0.0059
  -5.750  -0.2044   0.01933   0.01486  -0.0939   0.9084   0.0058
  -5.500  -0.1804   0.01651   0.01154  -0.0936   0.9018   0.0059
  -5.250  -0.1551   0.01473   0.00940  -0.0932   0.8950   0.0061
  -5.000  -0.1290   0.01346   0.00787  -0.0929   0.8891   0.0065
  -4.750  -0.1028   0.01259   0.00681  -0.0925   0.8824   0.0068
  -4.500  -0.0760   0.01196   0.00604  -0.0923   0.8767   0.0072
  -4.250  -0.0505   0.01083   0.00475  -0.0920   0.8700   0.0080
  -4.000  -0.0236   0.01044   0.00426  -0.0919   0.8642   0.0093
  -3.750   0.0034   0.01000   0.00374  -0.0917   0.8577   0.0099
  -3.500   0.0307   0.00960   0.00322  -0.0915   0.8516   0.0105
  -3.250   0.0581   0.00928   0.00281  -0.0914   0.8452   0.0113
  -3.000   0.0857   0.00901   0.00244  -0.0913   0.8388   0.0133
  -2.750   0.1132   0.00874   0.00220  -0.0912   0.8324   0.0244
  -2.500   0.1408   0.00858   0.00203  -0.0912   0.8254   0.0379
  -2.250   0.1683   0.00842   0.00188  -0.0911   0.8177   0.0545
  -2.000   0.1956   0.00827   0.00173  -0.0910   0.8089   0.0725
  -1.750   0.2227   0.00794   0.00158  -0.0910   0.7992   0.1391
  -1.500   0.2496   0.00748   0.00144  -0.0911   0.7908   0.2600
  -1.250   0.2759   0.00691   0.00134  -0.0912   0.7827   0.4333
  -1.000   0.3029   0.00669   0.00133  -0.0911   0.7745   0.5176
  -0.750   0.3299   0.00658   0.00132  -0.0909   0.7660   0.5774
  -0.500   0.3563   0.00649   0.00135  -0.0906   0.7544   0.6391
  -0.250   0.3822   0.00644   0.00139  -0.0900   0.7405   0.6937
   0.000   0.4089   0.00645   0.00140  -0.0896   0.7269   0.7160
   0.250   0.4363   0.00648   0.00139  -0.0895   0.7152   0.7256
   0.500   0.4636   0.00651   0.00140  -0.0893   0.7036   0.7350
   0.750   0.4906   0.00656   0.00141  -0.0891   0.6897   0.7445
   1.000   0.5172   0.00664   0.00142  -0.0888   0.6720   0.7547
   1.250   0.5438   0.00672   0.00146  -0.0885   0.6538   0.7654
   1.500   0.5704   0.00680   0.00150  -0.0882   0.6368   0.7765
   1.750   0.5966   0.00689   0.00156  -0.0878   0.6182   0.7883
   2.000   0.6226   0.00698   0.00162  -0.0874   0.5978   0.8011
   2.250   0.6481   0.00711   0.00172  -0.0869   0.5736   0.8154
   2.500   0.6729   0.00726   0.00181  -0.0863   0.5452   0.8325
   2.750   0.6968   0.00742   0.00192  -0.0855   0.5132   0.8539
   3.000   0.7189   0.00757   0.00205  -0.0843   0.4788   0.8937
   3.250   0.7503   0.00779   0.00221  -0.0852   0.4404   1.0000
   3.500   0.7752   0.00813   0.00240  -0.0848   0.4083   1.0000
   3.750   0.8001   0.00847   0.00260  -0.0844   0.3755   1.0000
   4.000   0.8249   0.00881   0.00282  -0.0840   0.3439   1.0000
   4.250   0.8494   0.00919   0.00306  -0.0835   0.3120   1.0000
   4.500   0.8740   0.00956   0.00334  -0.0831   0.2842   1.0000
   5.000   0.9218   0.01043   0.00392  -0.0821   0.2199   1.0000
   5.250   0.9436   0.01107   0.00429  -0.0814   0.1707   1.0000
   5.500   0.9661   0.01165   0.00466  -0.0807   0.1338   1.0000
   5.750   0.9885   0.01223   0.00508  -0.0800   0.0999   1.0000
   6.000   1.0102   0.01288   0.00554  -0.0792   0.0673   1.0000
   6.250   1.0319   0.01353   0.00604  -0.0784   0.0409   1.0000
   6.500   1.0532   0.01421   0.00659  -0.0775   0.0206   1.0000
   6.750   1.0737   0.01500   0.00727  -0.0765   0.0053   1.0000
   7.000   1.0963   0.01553   0.00783  -0.0757   0.0042   1.0000
   7.250   1.1188   0.01604   0.00843  -0.0749   0.0035   1.0000
   7.500   1.1410   0.01658   0.00908  -0.0741   0.0033   1.0000
   7.750   1.1626   0.01717   0.00978  -0.0731   0.0031   1.0000
   8.000   1.1836   0.01779   0.01050  -0.0722   0.0030   1.0000
   8.250   1.2038   0.01848   0.01130  -0.0710   0.0029   1.0000
   8.500   1.2227   0.01928   0.01221  -0.0697   0.0028   1.0000
   8.750   1.2407   0.02012   0.01316  -0.0683   0.0028   1.0000
   9.000   1.2572   0.02104   0.01421  -0.0667   0.0027   1.0000
   9.250   1.2727   0.02200   0.01528  -0.0650   0.0026   1.0000
   9.500   1.2864   0.02303   0.01642  -0.0631   0.0025   1.0000
   9.750   1.2974   0.02406   0.01760  -0.0607   0.0023   1.0000
  10.000   1.3068   0.02514   0.01878  -0.0582   0.0021   1.0000
  10.250   1.3134   0.02643   0.02018  -0.0555   0.0020   1.0000
  10.500   1.3182   0.02788   0.02175  -0.0527   0.0019   1.0000
  10.750   1.3200   0.02963   0.02364  -0.0499   0.0018   1.0000
  11.000   1.3190   0.03173   0.02590  -0.0470   0.0018   1.0000
  11.250   1.3176   0.03400   0.02833  -0.0444   0.0017   1.0000
  11.500   1.3168   0.03632   0.03082  -0.0423   0.0017   1.0000
  11.750   1.3133   0.03905   0.03372  -0.0402   0.0017   1.0000
  12.000   1.3137   0.04142   0.03627  -0.0388   0.0017   1.0000
  12.250   1.3150   0.04371   0.03872  -0.0378   0.0016   1.0000
  12.500   1.3120   0.04667   0.04187  -0.0369   0.0016   1.0000
  12.750   1.3096   0.04966   0.04502  -0.0364   0.0016   1.0000
  13.000   1.3045   0.05319   0.04874  -0.0363   0.0016   1.0000
  13.250   1.2993   0.05692   0.05265  -0.0366   0.0015   1.0000
  13.500   1.2887   0.06165   0.05757  -0.0376   0.0015   1.0000
  13.750   1.2779   0.06676   0.06286  -0.0391   0.0015   1.0000
  14.000   1.2667   0.07231   0.06860  -0.0413   0.0015   1.0000
  14.250   1.2538   0.07861   0.07507  -0.0442   0.0015   1.0000
  14.500   1.2404   0.08549   0.08213  -0.0478   0.0015   1.0000
  14.750   1.2254   0.09316   0.08997  -0.0521   0.0015   1.0000
  15.000   1.2098   0.10136   0.09833  -0.0567   0.0015   1.0000
  15.250   1.1942   0.10999   0.10711  -0.0618   0.0015   1.0000
  15.500   1.1790   0.11881   0.11608  -0.0669   0.0015   1.0000
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