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HQ 3.5/8 AIRFOIL (hq358-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/8 AIRFOIL (hq358-il)
Reynolds number: 1,000,000
Max Cl/Cd: 144.93 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq358-il-1000000.txt
Download as CSV file: xf-hq358-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/8 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3411   0.09776   0.09619  -0.0322   1.0000   0.0053
  -8.500  -0.3434   0.09522   0.09366  -0.0316   1.0000   0.0053
  -8.250  -0.3448   0.09266   0.09113  -0.0313   0.9997   0.0053
  -8.000  -0.3296   0.08828   0.08675  -0.0360   0.9981   0.0053
  -7.750  -0.3132   0.08403   0.08250  -0.0410   0.9955   0.0053
  -7.500  -0.2980   0.07949   0.07798  -0.0462   0.9913   0.0053
  -7.250  -0.2809   0.07491   0.07339  -0.0522   0.9864   0.0053
  -7.000  -0.2564   0.06935   0.06784  -0.0611   0.9832   0.0053
  -6.750  -0.2306   0.06359   0.06206  -0.0711   0.9785   0.0053
  -6.500  -0.1992   0.05691   0.05533  -0.0832   0.9734   0.0053
  -6.250  -0.1661   0.05043   0.04875  -0.0935   0.9691   0.0054
  -6.000  -0.1434   0.04527   0.04346  -0.0988   0.9589   0.0054
  -2.750   0.1759   0.00947   0.00460  -0.1064   0.8657   0.0096
  -2.500   0.2026   0.00824   0.00320  -0.1059   0.8566   0.0089
  -2.250   0.2297   0.00756   0.00236  -0.1055   0.8473   0.0088
  -2.000   0.2575   0.00713   0.00180  -0.1054   0.8385   0.0094
  -1.750   0.2855   0.00685   0.00139  -0.1052   0.8309   0.0113
  -1.500   0.3133   0.00669   0.00114  -0.1051   0.8226   0.0146
  -1.250   0.3412   0.00645   0.00101  -0.1051   0.8144   0.0546
  -1.000   0.3684   0.00595   0.00092  -0.1053   0.8056   0.2166
  -0.750   0.3949   0.00524   0.00086  -0.1056   0.7955   0.4775
  -0.500   0.4218   0.00498   0.00088  -0.1055   0.7855   0.5952
  -0.250   0.4484   0.00485   0.00093  -0.1052   0.7756   0.6807
   0.000   0.4754   0.00483   0.00095  -0.1049   0.7656   0.7152
   0.250   0.5025   0.00483   0.00096  -0.1047   0.7554   0.7408
   0.500   0.5293   0.00481   0.00099  -0.1044   0.7446   0.7728
   0.750   0.5561   0.00482   0.00101  -0.1041   0.7324   0.7956
   1.000   0.5830   0.00484   0.00103  -0.1039   0.7199   0.8107
   1.250   0.6096   0.00486   0.00106  -0.1036   0.7067   0.8287
   1.500   0.6356   0.00487   0.00108  -0.1032   0.6910   0.8526
   1.750   0.6586   0.00476   0.00111  -0.1020   0.6751   0.9151
   2.000   0.6907   0.00480   0.00113  -0.1029   0.6565   1.0000
   2.250   0.7174   0.00495   0.00119  -0.1027   0.6342   1.0000
   2.500   0.7436   0.00514   0.00129  -0.1025   0.6064   1.0000
   2.750   0.7691   0.00539   0.00138  -0.1021   0.5691   1.0000
   3.000   0.7939   0.00571   0.00152  -0.1016   0.5254   1.0000
   3.250   0.8184   0.00608   0.00168  -0.1011   0.4779   1.0000
   3.500   0.8426   0.00648   0.00187  -0.1005   0.4304   1.0000
   3.750   0.8671   0.00687   0.00208  -0.1001   0.3869   1.0000
   4.000   0.8908   0.00734   0.00234  -0.0995   0.3359   1.0000
   4.250   0.9152   0.00775   0.00257  -0.0990   0.2965   1.0000
   4.500   0.9390   0.00820   0.00283  -0.0985   0.2577   1.0000
   4.750   0.9637   0.00856   0.00306  -0.0981   0.2299   1.0000
   5.000   0.9879   0.00897   0.00330  -0.0977   0.1967   1.0000
   5.250   1.0119   0.00940   0.00360  -0.0972   0.1621   1.0000
   5.500   1.0322   0.01025   0.00408  -0.0961   0.0985   1.0000
   5.750   1.0491   0.01153   0.00489  -0.0946   0.0205   1.0000
   6.000   1.0713   0.01226   0.00558  -0.0935   0.0044   1.0000
   6.250   1.0955   0.01269   0.00609  -0.0929   0.0041   1.0000
   6.500   1.1189   0.01322   0.00671  -0.0921   0.0040   1.0000
   6.750   1.1415   0.01385   0.00746  -0.0912   0.0039   1.0000
   7.000   1.1630   0.01459   0.00835  -0.0901   0.0039   1.0000
   7.250   1.1829   0.01552   0.00941  -0.0887   0.0040   1.0000
   7.500   1.2007   0.01665   0.01068  -0.0869   0.0041   1.0000
   7.750   1.2183   0.01777   0.01191  -0.0852   0.0040   1.0000
   8.000   1.2367   0.01876   0.01300  -0.0838   0.0039   1.0000
   8.250   1.2551   0.01973   0.01407  -0.0823   0.0036   1.0000
   8.500   1.2697   0.02128   0.01576  -0.0802   0.0037   1.0000
   8.750   1.2853   0.02276   0.01737  -0.0784   0.0036   1.0000
   9.000   1.3000   0.02455   0.01932  -0.0764   0.0036   1.0000
   9.250   1.3147   0.02632   0.02124  -0.0746   0.0035   1.0000
   9.500   1.3283   0.02812   0.02324  -0.0726   0.0033   1.0000
   9.750   1.3411   0.02945   0.02470  -0.0707   0.0030   1.0000
  10.000   1.3504   0.03096   0.02634  -0.0683   0.0028   1.0000
  10.250   1.3547   0.03225   0.02773  -0.0653   0.0026   1.0000
  10.500   1.3543   0.03461   0.03030  -0.0617   0.0025   1.0000
  10.750   1.3202   0.04374   0.04022  -0.0542   0.0034   1.0000
  11.000   1.3085   0.04682   0.04351  -0.0507   0.0033   1.0000
  11.250   1.2944   0.05030   0.04720  -0.0479   0.0033   1.0000
  11.500   1.2799   0.05398   0.05107  -0.0459   0.0033   1.0000
  11.750   1.2644   0.05806   0.05533  -0.0448   0.0033   1.0000
  12.000   1.2472   0.06277   0.06022  -0.0446   0.0033   1.0000
  12.250   1.2286   0.06815   0.06578  -0.0455   0.0033   1.0000
  12.500   1.2094   0.07423   0.07202  -0.0475   0.0033   1.0000
  12.750   1.1896   0.08116   0.07911  -0.0508   0.0033   1.0000
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