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HQ 3.0/9 AIRFOIL (hq309-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/9 AIRFOIL (hq309-il)
Reynolds number: 200,000
Max Cl/Cd: 78.36 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq309-il-200000-n5.txt
Download as CSV file: xf-hq309-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3728   0.08962   0.08624  -0.0389   1.0000   0.0205
  -8.250  -0.3705   0.08730   0.08396  -0.0376   1.0000   0.0214
  -8.000  -0.3747   0.08453   0.08126  -0.0374   1.0000   0.0215
  -7.500  -0.2959   0.06229   0.05929  -0.0438   0.9894   0.0169
  -7.000  -0.3609   0.06798   0.06484  -0.0519   0.9858   0.0172
  -6.750  -0.3409   0.06057   0.05734  -0.0624   0.9775   0.0153
  -6.250  -0.2891   0.04394   0.04008  -0.0793   0.9635   0.0116
  -6.000  -0.2609   0.03798   0.03374  -0.0844   0.9596   0.0113
  -5.750  -0.2385   0.03308   0.02844  -0.0864   0.9518   0.0111
  -5.500  -0.2090   0.02819   0.02300  -0.0889   0.9474   0.0110
  -5.250  -0.1821   0.02436   0.01860  -0.0897   0.9415   0.0111
  -5.000  -0.1530   0.02139   0.01508  -0.0904   0.9365   0.0115
  -4.750  -0.1213   0.01913   0.01236  -0.0913   0.9330   0.0124
  -4.500  -0.0949   0.01800   0.01109  -0.0915   0.9268   0.0144
  -4.250  -0.0650   0.01660   0.00946  -0.0918   0.9221   0.0153
  -4.000  -0.0344   0.01534   0.00799  -0.0923   0.9183   0.0161
  -3.750  -0.0082   0.01442   0.00694  -0.0919   0.9115   0.0172
  -3.500   0.0216   0.01362   0.00601  -0.0922   0.9068   0.0190
  -3.250   0.0492   0.01296   0.00529  -0.0922   0.9008   0.0238
  -3.000   0.0777   0.01247   0.00478  -0.0923   0.8949   0.0375
  -2.750   0.1070   0.01212   0.00434  -0.0926   0.8898   0.0555
  -2.500   0.1339   0.01177   0.00407  -0.0925   0.8828   0.0828
  -2.250   0.1628   0.01127   0.00373  -0.0929   0.8778   0.1362
  -2.000   0.1878   0.01045   0.00350  -0.0929   0.8702   0.3161
  -1.750   0.2135   0.00979   0.00346  -0.0927   0.8645   0.5226
  -1.500   0.2386   0.00963   0.00346  -0.0919   0.8567   0.6046
  -1.250   0.2647   0.00950   0.00347  -0.0911   0.8503   0.6753
  -1.000   0.2879   0.00943   0.00353  -0.0897   0.8412   0.7341
  -0.750   0.3130   0.00936   0.00349  -0.0886   0.8332   0.7686
  -0.500   0.3397   0.00932   0.00338  -0.0882   0.8248   0.7819
  -0.250   0.3665   0.00929   0.00331  -0.0878   0.8163   0.7941
   0.000   0.3939   0.00924   0.00321  -0.0875   0.8089   0.8067
   0.250   0.4199   0.00920   0.00317  -0.0870   0.7996   0.8205
   0.500   0.4460   0.00915   0.00310  -0.0864   0.7892   0.8358
   0.750   0.4719   0.00907   0.00301  -0.0857   0.7766   0.8536
   1.000   0.4982   0.00900   0.00293  -0.0850   0.7638   0.8763
   1.250   0.5277   0.00891   0.00288  -0.0851   0.7527   0.9115
   1.500   0.5639   0.00887   0.00282  -0.0868   0.7406   1.0000
   1.750   0.5913   0.00895   0.00283  -0.0867   0.7267   1.0000
   2.000   0.6183   0.00904   0.00285  -0.0865   0.7104   1.0000
   2.250   0.6451   0.00914   0.00291  -0.0862   0.6930   1.0000
   2.500   0.6718   0.00926   0.00296  -0.0860   0.6754   1.0000
   2.750   0.6983   0.00940   0.00303  -0.0856   0.6571   1.0000
   3.000   0.7245   0.00955   0.00313  -0.0853   0.6361   1.0000
   3.250   0.7503   0.00973   0.00328  -0.0848   0.6127   1.0000
   3.500   0.7755   0.00994   0.00341  -0.0843   0.5847   1.0000
   3.750   0.8001   0.01021   0.00356  -0.0836   0.5526   1.0000
   4.000   0.8238   0.01054   0.00375  -0.0829   0.5158   1.0000
   4.250   0.8469   0.01093   0.00399  -0.0820   0.4773   1.0000
   4.500   0.8694   0.01138   0.00431  -0.0811   0.4381   1.0000
   4.750   0.8919   0.01185   0.00465  -0.0803   0.4006   1.0000
   5.000   0.9142   0.01235   0.00502  -0.0794   0.3644   1.0000
   5.250   0.9362   0.01287   0.00542  -0.0786   0.3287   1.0000
   5.500   0.9581   0.01343   0.00585  -0.0777   0.2953   1.0000
   5.750   0.9797   0.01401   0.00635  -0.0769   0.2634   1.0000
   6.000   1.0012   0.01460   0.00684  -0.0760   0.2328   1.0000
   6.250   1.0220   0.01526   0.00735  -0.0751   0.1962   1.0000
   6.500   1.0411   0.01609   0.00791  -0.0741   0.1522   1.0000
   6.750   1.0601   0.01696   0.00852  -0.0730   0.1100   1.0000
   7.000   1.0802   0.01771   0.00916  -0.0721   0.0837   1.0000
   7.250   1.1004   0.01845   0.00984  -0.0711   0.0633   1.0000
   7.500   1.1204   0.01921   0.01065  -0.0700   0.0489   1.0000
   7.750   1.1383   0.02018   0.01155  -0.0687   0.0310   1.0000
   8.000   1.1546   0.02129   0.01257  -0.0673   0.0148   1.0000
   8.250   1.1717   0.02230   0.01360  -0.0658   0.0087   1.0000
   8.500   1.1888   0.02329   0.01470  -0.0643   0.0069   1.0000
   8.750   1.2048   0.02433   0.01587  -0.0627   0.0062   1.0000
   9.000   1.2186   0.02554   0.01724  -0.0608   0.0057   1.0000
   9.250   1.2312   0.02669   0.01858  -0.0588   0.0055   1.0000
   9.500   1.2411   0.02794   0.02001  -0.0563   0.0054   1.0000
   9.750   1.2489   0.02932   0.02157  -0.0538   0.0052   1.0000
  10.000   1.2552   0.03083   0.02333  -0.0512   0.0051   1.0000
  10.250   1.2600   0.03251   0.02518  -0.0487   0.0050   1.0000
  10.500   1.2642   0.03429   0.02715  -0.0463   0.0050   1.0000
  10.750   1.2669   0.03630   0.02934  -0.0441   0.0049   1.0000
  11.000   1.2688   0.03849   0.03172  -0.0420   0.0049   1.0000
  11.250   1.2698   0.04089   0.03432  -0.0401   0.0048   1.0000
  11.500   1.2698   0.04347   0.03711  -0.0385   0.0048   1.0000
  11.750   1.2688   0.04627   0.04012  -0.0371   0.0047   1.0000
  12.000   1.2655   0.04947   0.04355  -0.0359   0.0047   1.0000
  12.250   1.2612   0.05285   0.04716  -0.0351   0.0047   1.0000
  12.500   1.2544   0.05672   0.05127  -0.0347   0.0047   1.0000
  12.750   1.2461   0.06093   0.05572  -0.0348   0.0047   1.0000
  13.000   1.2357   0.06565   0.06068  -0.0355   0.0047   1.0000
  13.250   1.2243   0.07074   0.06600  -0.0369   0.0046   1.0000
  13.500   1.2111   0.07648   0.07197  -0.0390   0.0047   1.0000
  13.750   1.1963   0.08292   0.07863  -0.0419   0.0047   1.0000
  14.000   1.1809   0.08996   0.08588  -0.0456   0.0047   1.0000
  14.250   1.1649   0.09774   0.09386  -0.0500   0.0047   1.0000
  14.500   1.1480   0.10626   0.10257  -0.0551   0.0047   1.0000
  14.750   1.1306   0.11550   0.11199  -0.0608   0.0048   1.0000
  15.000   1.1134   0.12519   0.12184  -0.0669   0.0049   1.0000
  15.250   1.0959   0.13551   0.13229  -0.0732   0.0049   1.0000
  15.500   1.0781   0.14640   0.14330  -0.0797   0.0050   1.0000
  15.750   1.0595   0.15825   0.15523  -0.0866   0.0051   1.0000
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