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HQ 0/9 AIRFOIL (hq09-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 0/9 AIRFOIL (hq09-il)
Reynolds number: 1,000,000
Max Cl/Cd: 63.37 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq09-il-1000000-n5.txt
Download as CSV file: xf-hq09-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 0/9 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.9177   0.04166   0.03959  -0.0168   1.0000   0.0017
  -9.750  -0.9427   0.03392   0.03136  -0.0142   1.0000   0.0017
  -9.500  -0.9483   0.02845   0.02536  -0.0119   1.0000   0.0017
  -9.250  -0.9410   0.02484   0.02128  -0.0101   1.0000   0.0016
  -9.000  -0.9282   0.02202   0.01808  -0.0086   1.0000   0.0016
  -8.750  -0.9116   0.01982   0.01557  -0.0074   1.0000   0.0016
  -8.500  -0.8924   0.01813   0.01361  -0.0064   1.0000   0.0016
  -8.250  -0.8716   0.01675   0.01203  -0.0055   1.0000   0.0016
  -8.000  -0.8500   0.01551   0.01060  -0.0047   1.0000   0.0016
  -7.750  -0.8274   0.01451   0.00944  -0.0040   1.0000   0.0016
  -7.500  -0.8042   0.01365   0.00844  -0.0034   1.0000   0.0016
  -7.250  -0.7804   0.01289   0.00756  -0.0028   1.0000   0.0016
  -7.000  -0.7561   0.01224   0.00680  -0.0022   1.0000   0.0016
  -6.750  -0.7314   0.01168   0.00615  -0.0018   1.0000   0.0017
  -6.500  -0.7064   0.01119   0.00554  -0.0013   1.0000   0.0017
  -6.250  -0.6812   0.01075   0.00504  -0.0009   1.0000   0.0017
  -6.000  -0.6558   0.01036   0.00459  -0.0005   1.0000   0.0018
  -5.750  -0.6303   0.01001   0.00419  -0.0001   1.0000   0.0019
  -5.500  -0.6030   0.00970   0.00383  -0.0001   0.9971   0.0021
  -5.250  -0.5694   0.00938   0.00347  -0.0015   0.9812   0.0024
  -5.000  -0.5353   0.00895   0.00311  -0.0032   0.9655   0.0099
  -4.750  -0.5035   0.00876   0.00288  -0.0041   0.9455   0.0109
  -4.500  -0.4762   0.00862   0.00265  -0.0039   0.9216   0.0125
  -4.250  -0.4508   0.00848   0.00245  -0.0034   0.8971   0.0154
  -4.000  -0.4253   0.00834   0.00226  -0.0029   0.8755   0.0198
  -3.750  -0.3997   0.00815   0.00206  -0.0024   0.8575   0.0334
  -3.500  -0.3737   0.00791   0.00188  -0.0021   0.8416   0.0536
  -3.250  -0.3472   0.00775   0.00172  -0.0019   0.8266   0.0696
  -3.000  -0.3207   0.00756   0.00155  -0.0017   0.8110   0.0926
  -2.750  -0.2945   0.00731   0.00136  -0.0014   0.7945   0.1285
  -2.250  -0.2423   0.00667   0.00107  -0.0011   0.7671   0.2473
  -2.000  -0.2158   0.00638   0.00095  -0.0010   0.7560   0.3031
  -1.750  -0.1898   0.00601   0.00083  -0.0008   0.7457   0.3860
  -1.500  -0.1634   0.00572   0.00072  -0.0007   0.7365   0.4540
  -1.250  -0.1371   0.00544   0.00065  -0.0005   0.7265   0.5249
  -1.000  -0.1106   0.00520   0.00062  -0.0003   0.7164   0.5932
  -0.750  -0.0830   0.00515   0.00060  -0.0002   0.7062   0.6173
  -0.500  -0.0554   0.00515   0.00058  -0.0001   0.6908   0.6323
  -0.250  -0.0278   0.00515   0.00057   0.0000   0.6738   0.6469
   0.000   0.0000   0.00515   0.00057   0.0000   0.6603   0.6603
   0.250   0.0278   0.00515   0.00057   0.0000   0.6470   0.6739
   0.500   0.0554   0.00515   0.00058   0.0001   0.6322   0.6908
   0.750   0.0830   0.00515   0.00060   0.0002   0.6173   0.7062
   1.000   0.1107   0.00521   0.00062   0.0003   0.5932   0.7163
   1.250   0.1371   0.00543   0.00065   0.0005   0.5253   0.7266
   1.500   0.1634   0.00572   0.00072   0.0007   0.4539   0.7365
   1.750   0.1898   0.00601   0.00083   0.0008   0.3865   0.7458
   2.000   0.2158   0.00638   0.00095   0.0010   0.3033   0.7563
   2.250   0.2424   0.00667   0.00107   0.0011   0.2472   0.7671
   2.500   0.2689   0.00693   0.00120   0.0012   0.2038   0.7792
   2.750   0.2946   0.00731   0.00136   0.0014   0.1284   0.7943
   3.000   0.3208   0.00756   0.00155   0.0017   0.0926   0.8108
   3.250   0.3472   0.00775   0.00172   0.0019   0.0695   0.8266
   3.500   0.3737   0.00791   0.00188   0.0021   0.0537   0.8415
   3.750   0.3997   0.00814   0.00206   0.0024   0.0338   0.8577
   4.000   0.4254   0.00835   0.00226   0.0029   0.0194   0.8759
   4.250   0.4508   0.00848   0.00245   0.0034   0.0155   0.8975
   4.500   0.4763   0.00862   0.00265   0.0039   0.0124   0.9217
   4.750   0.5035   0.00876   0.00288   0.0041   0.0109   0.9454
   5.000   0.5352   0.00895   0.00311   0.0032   0.0096   0.9655
   5.250   0.5694   0.00939   0.00348   0.0015   0.0024   0.9812
   5.500   0.6030   0.00969   0.00382   0.0001   0.0021   0.9970
   5.750   0.6302   0.01001   0.00419   0.0001   0.0019   1.0000
   6.000   0.6557   0.01037   0.00460   0.0005   0.0018   1.0000
   6.250   0.6812   0.01075   0.00504   0.0009   0.0017   1.0000
   6.500   0.7064   0.01119   0.00555   0.0013   0.0017   1.0000
   6.750   0.7315   0.01169   0.00616   0.0018   0.0017   1.0000
   7.000   0.7562   0.01224   0.00680   0.0022   0.0016   1.0000
   7.250   0.7805   0.01290   0.00757   0.0027   0.0016   1.0000
   7.500   0.8043   0.01366   0.00844   0.0033   0.0016   1.0000
   7.750   0.8276   0.01450   0.00943   0.0040   0.0016   1.0000
   8.000   0.8503   0.01551   0.01059   0.0047   0.0016   1.0000
   8.250   0.8720   0.01670   0.01197   0.0055   0.0016   1.0000
   8.500   0.8924   0.01819   0.01368   0.0064   0.0016   1.0000
   8.750   0.9117   0.01987   0.01562   0.0074   0.0016   1.0000
   9.000   0.9283   0.02209   0.01816   0.0086   0.0016   1.0000
   9.250   0.9418   0.02477   0.02120   0.0100   0.0016   1.0000
   9.500   0.9482   0.02859   0.02552   0.0118   0.0017   1.0000
   9.750   0.9439   0.03382   0.03126   0.0140   0.0017   1.0000
  10.000   0.9165   0.04197   0.03992   0.0167   0.0017   1.0000
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