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HQ 3.5/9 AIRFOIL (hq359-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/9 AIRFOIL (hq359-il)
Reynolds number: 500,000
Max Cl/Cd: 101.08 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq359-il-500000-n5.txt
Download as CSV file: xf-hq359-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/9 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3366   0.10684   0.10452  -0.0357   1.0000   0.0068
  -9.500  -0.3348   0.10369   0.10140  -0.0362   1.0000   0.0068
  -9.000  -0.3346   0.09768   0.09547  -0.0365   1.0000   0.0068
  -8.500  -0.3190   0.08984   0.08765  -0.0413   0.9937   0.0055
  -8.250  -0.3085   0.08517   0.08299  -0.0456   0.9885   0.0050
  -8.000  -0.2979   0.08006   0.07789  -0.0506   0.9826   0.0046
  -7.750  -0.2851   0.07497   0.07281  -0.0565   0.9762   0.0046
  -7.500  -0.2692   0.07012   0.06797  -0.0632   0.9691   0.0047
  -7.250  -0.2482   0.06464   0.06248  -0.0724   0.9615   0.0054
  -7.000  -0.2270   0.05749   0.05529  -0.0847   0.9501   0.0052
  -6.750  -0.2071   0.05104   0.04871  -0.0937   0.9384   0.0058
  -6.500  -0.1895   0.04535   0.04285  -0.0992   0.9275   0.0061
  -6.250  -0.1705   0.04035   0.03763  -0.1025   0.9184   0.0065
  -6.000  -0.1518   0.03565   0.03269  -0.1046   0.9093   0.0066
  -5.750  -0.1328   0.03071   0.02742  -0.1061   0.9015   0.0063
  -5.500  -0.1114   0.02577   0.02206  -0.1070   0.8944   0.0061
  -5.250  -0.0886   0.02050   0.01624  -0.1072   0.8878   0.0059
  -5.000  -0.0638   0.01680   0.01196  -0.1070   0.8816   0.0060
  -4.750  -0.0375   0.01473   0.00949  -0.1068   0.8763   0.0062
  -4.500  -0.0109   0.01347   0.00796  -0.1066   0.8703   0.0066
  -4.250   0.0163   0.01272   0.00698  -0.1064   0.8652   0.0069
  -4.000   0.0423   0.01130   0.00534  -0.1061   0.8593   0.0076
  -3.750   0.0692   0.01082   0.00481  -0.1061   0.8538   0.0089
  -3.500   0.0964   0.01028   0.00416  -0.1060   0.8484   0.0093
  -3.250   0.1238   0.00976   0.00354  -0.1058   0.8423   0.0095
  -3.000   0.1514   0.00937   0.00303  -0.1057   0.8370   0.0099
  -2.750   0.1791   0.00906   0.00262  -0.1057   0.8306   0.0105
  -2.500   0.2069   0.00884   0.00229  -0.1056   0.8245   0.0113
  -2.250   0.2347   0.00862   0.00203  -0.1055   0.8171   0.0150
  -2.000   0.2622   0.00844   0.00185  -0.1054   0.8083   0.0308
  -1.500   0.3165   0.00814   0.00156  -0.1051   0.7835   0.0756
  -1.250   0.3437   0.00793   0.00145  -0.1051   0.7721   0.1276
  -1.000   0.3697   0.00694   0.00136  -0.1055   0.7624   0.4466
  -0.750   0.3963   0.00671   0.00136  -0.1054   0.7524   0.5530
  -0.500   0.4228   0.00662   0.00139  -0.1050   0.7412   0.6199
  -0.250   0.4495   0.00658   0.00142  -0.1047   0.7300   0.6650
   0.000   0.4759   0.00657   0.00146  -0.1043   0.7184   0.7060
   0.250   0.5027   0.00661   0.00146  -0.1040   0.7044   0.7244
   0.500   0.5295   0.00666   0.00146  -0.1037   0.6891   0.7336
   0.750   0.5565   0.00672   0.00148  -0.1035   0.6762   0.7431
   1.250   0.6099   0.00687   0.00155  -0.1030   0.6474   0.7634
   1.500   0.6363   0.00696   0.00159  -0.1027   0.6305   0.7745
   1.750   0.6624   0.00705   0.00165  -0.1023   0.6120   0.7866
   2.000   0.6879   0.00718   0.00173  -0.1018   0.5891   0.8001
   2.250   0.7128   0.00732   0.00183  -0.1012   0.5627   0.8157
   2.500   0.7371   0.00749   0.00193  -0.1005   0.5339   0.8348
   2.750   0.7598   0.00766   0.00206  -0.0995   0.4990   0.8625
   3.000   0.7874   0.00779   0.00218  -0.0995   0.4616   1.0000
   3.250   0.8117   0.00815   0.00237  -0.0990   0.4257   1.0000
   3.500   0.8360   0.00853   0.00260  -0.0985   0.3892   1.0000
   3.750   0.8602   0.00892   0.00283  -0.0980   0.3544   1.0000
   4.000   0.8844   0.00930   0.00306  -0.0975   0.3204   1.0000
   4.250   0.9088   0.00967   0.00331  -0.0971   0.2948   1.0000
   4.500   0.9336   0.01000   0.00358  -0.0967   0.2763   1.0000
   4.750   0.9585   0.01031   0.00384  -0.0963   0.2614   1.0000
   5.000   0.9823   0.01071   0.00414  -0.0958   0.2368   1.0000
   5.250   1.0057   0.01115   0.00443  -0.0952   0.2088   1.0000
   5.500   1.0299   0.01150   0.00472  -0.0947   0.1905   1.0000
   5.750   1.0532   0.01194   0.00506  -0.0941   0.1619   1.0000
   6.000   1.0728   0.01274   0.00555  -0.0931   0.1112   1.0000
   6.250   1.0925   0.01354   0.00611  -0.0920   0.0711   1.0000
   6.500   1.1073   0.01487   0.00705  -0.0901   0.0138   1.0000
   6.750   1.1284   0.01553   0.00767  -0.0891   0.0052   1.0000
   7.000   1.1507   0.01603   0.00823  -0.0883   0.0042   1.0000
   7.250   1.1726   0.01657   0.00886  -0.0874   0.0036   1.0000
   7.500   1.1940   0.01713   0.00956  -0.0864   0.0034   1.0000
   7.750   1.2148   0.01774   0.01027  -0.0853   0.0032   1.0000
   8.000   1.2344   0.01844   0.01108  -0.0841   0.0031   1.0000
   8.250   1.2530   0.01922   0.01197  -0.0827   0.0030   1.0000
   8.500   1.2702   0.02007   0.01294  -0.0812   0.0029   1.0000
   8.750   1.2859   0.02099   0.01397  -0.0794   0.0028   1.0000
   9.000   1.3004   0.02191   0.01499  -0.0775   0.0026   1.0000
   9.250   1.3123   0.02284   0.01601  -0.0752   0.0024   1.0000
   9.500   1.3221   0.02389   0.01715  -0.0726   0.0022   1.0000
   9.750   1.3292   0.02514   0.01855  -0.0698   0.0021   1.0000
  10.000   1.3324   0.02670   0.02024  -0.0666   0.0020   1.0000
  10.250   1.3336   0.02851   0.02219  -0.0635   0.0019   1.0000
  10.500   1.3324   0.03067   0.02451  -0.0603   0.0018   1.0000
  10.750   1.3371   0.03238   0.02636  -0.0580   0.0018   1.0000
  11.000   1.3422   0.03409   0.02821  -0.0560   0.0018   1.0000
  11.250   1.3476   0.03580   0.03007  -0.0542   0.0017   1.0000
  11.500   1.3505   0.03784   0.03226  -0.0524   0.0017   1.0000
  11.750   1.3534   0.03995   0.03454  -0.0509   0.0016   1.0000
  12.000   1.3525   0.04256   0.03732  -0.0493   0.0016   1.0000
  12.250   1.3519   0.04523   0.04016  -0.0481   0.0015   1.0000
  12.500   1.3489   0.04829   0.04341  -0.0471   0.0015   1.0000
  12.750   1.3448   0.05163   0.04694  -0.0465   0.0014   1.0000
  13.000   1.3381   0.05547   0.05097  -0.0463   0.0014   1.0000
  13.250   1.3303   0.05964   0.05534  -0.0465   0.0014   1.0000
  13.500   1.3203   0.06440   0.06029  -0.0473   0.0014   1.0000
  13.750   1.3093   0.06960   0.06568  -0.0486   0.0013   1.0000
  14.000   1.2975   0.07531   0.07159  -0.0506   0.0013   1.0000
  14.250   1.2844   0.08165   0.07812  -0.0533   0.0013   1.0000
  14.500   1.2703   0.08863   0.08528  -0.0567   0.0013   1.0000
  14.750   1.2559   0.09613   0.09296  -0.0607   0.0013   1.0000
  15.000   1.2413   0.10408   0.10109  -0.0651   0.0013   1.0000
  15.250   1.2259   0.11256   0.10973  -0.0700   0.0013   1.0000
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