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HQ 3.5/9 AIRFOIL (hq359-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/9 AIRFOIL (hq359-il)
Reynolds number: 200,000
Max Cl/Cd: 82.16 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq359-il-200000-n5.txt
Download as CSV file: xf-hq359-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3366   0.10008   0.09668  -0.0395   1.0000   0.0191
  -8.500  -0.3401   0.09762   0.09429  -0.0389   1.0000   0.0191
  -8.250  -0.3469   0.09551   0.09224  -0.0376   1.0000   0.0192
  -8.000  -0.3460   0.09252   0.08930  -0.0388   0.9980   0.0192
  -7.750  -0.3423   0.08620   0.08303  -0.0407   0.9943   0.0204
  -7.500  -0.3279   0.08276   0.07959  -0.0432   0.9895   0.0213
  -7.250  -0.3138   0.07842   0.07526  -0.0483   0.9831   0.0218
  -7.000  -0.2953   0.07359   0.07044  -0.0552   0.9762   0.0223
  -6.750  -0.2749   0.06806   0.06489  -0.0640   0.9696   0.0225
  -6.250  -0.2220   0.05406   0.05063  -0.0850   0.9566   0.0171
  -6.000  -0.1991   0.04821   0.04459  -0.0912   0.9500   0.0150
  -5.500  -0.1419   0.03542   0.03100  -0.0998   0.9377   0.0115
  -5.250  -0.1130   0.03063   0.02578  -0.1029   0.9337   0.0113
  -5.000  -0.0883   0.02675   0.02144  -0.1038   0.9271   0.0112
  -4.750  -0.0587   0.02331   0.01746  -0.1049   0.9226   0.0113
  -4.500  -0.0273   0.02029   0.01383  -0.1060   0.9194   0.0121
  -4.250  -0.0025   0.01922   0.01260  -0.1060   0.9128   0.0141
  -4.000   0.0275   0.01759   0.01066  -0.1063   0.9086   0.0148
  -3.750   0.0574   0.01609   0.00889  -0.1065   0.9047   0.0151
  -3.500   0.0836   0.01501   0.00766  -0.1061   0.8984   0.0157
  -3.250   0.1127   0.01407   0.00659  -0.1062   0.8940   0.0166
  -3.000   0.1404   0.01337   0.00577  -0.1061   0.8885   0.0180
  -2.750   0.1682   0.01276   0.00503  -0.1061   0.8828   0.0209
  -2.500   0.1980   0.01232   0.00456  -0.1064   0.8785   0.0328
  -2.250   0.2245   0.01199   0.00424  -0.1062   0.8716   0.0562
  -2.000   0.2533   0.01166   0.00394  -0.1064   0.8664   0.0856
  -1.750   0.2800   0.01096   0.00371  -0.1067   0.8602   0.2243
  -1.500   0.3046   0.00998   0.00369  -0.1066   0.8539   0.5317
  -1.250   0.3300   0.00980   0.00373  -0.1057   0.8472   0.6335
  -1.000   0.3548   0.00969   0.00374  -0.1047   0.8397   0.7015
  -0.750   0.3794   0.00962   0.00372  -0.1036   0.8311   0.7441
  -0.500   0.4047   0.00952   0.00360  -0.1025   0.8221   0.7773
  -0.250   0.4310   0.00944   0.00346  -0.1019   0.8111   0.7939
   0.000   0.4570   0.00937   0.00335  -0.1013   0.7996   0.8069
   0.250   0.4832   0.00932   0.00325  -0.1008   0.7891   0.8212
   0.500   0.5093   0.00925   0.00316  -0.1002   0.7786   0.8377
   0.750   0.5356   0.00917   0.00306  -0.0996   0.7677   0.8579
   1.000   0.5621   0.00908   0.00297  -0.0990   0.7553   0.8879
   1.250   0.5972   0.00896   0.00288  -0.1004   0.7426   1.0000
   1.500   0.6250   0.00904   0.00289  -0.1004   0.7305   1.0000
   1.750   0.6526   0.00913   0.00291  -0.1003   0.7177   1.0000
   2.000   0.6799   0.00923   0.00294  -0.1002   0.7040   1.0000
   2.250   0.7071   0.00934   0.00301  -0.1001   0.6895   1.0000
   2.750   0.7603   0.00960   0.00315  -0.0995   0.6545   1.0000
   3.000   0.7863   0.00977   0.00324  -0.0991   0.6338   1.0000
   3.250   0.8120   0.00996   0.00336  -0.0987   0.6098   1.0000
   3.500   0.8369   0.01019   0.00353  -0.0981   0.5814   1.0000
   3.750   0.8610   0.01048   0.00369  -0.0973   0.5485   1.0000
   4.000   0.8841   0.01084   0.00389  -0.0965   0.5098   1.0000
   4.250   0.9062   0.01128   0.00415  -0.0955   0.4686   1.0000
   4.500   0.9278   0.01179   0.00450  -0.0944   0.4274   1.0000
   4.750   0.9494   0.01231   0.00487  -0.0934   0.3896   1.0000
   5.000   0.9711   0.01282   0.00526  -0.0925   0.3565   1.0000
   5.250   0.9931   0.01333   0.00567  -0.0917   0.3275   1.0000
   5.500   1.0153   0.01384   0.00610  -0.0908   0.3034   1.0000
   5.750   1.0374   0.01435   0.00659  -0.0900   0.2835   1.0000
   6.000   1.0595   0.01485   0.00707  -0.0892   0.2652   1.0000
   6.250   1.0806   0.01542   0.00757  -0.0883   0.2416   1.0000
   6.500   1.1017   0.01599   0.00807  -0.0874   0.2157   1.0000
   6.750   1.1227   0.01656   0.00855  -0.0865   0.1846   1.0000
   7.000   1.1433   0.01717   0.00909  -0.0855   0.1560   1.0000
   7.250   1.1598   0.01819   0.00982  -0.0841   0.1081   1.0000
   7.500   1.1711   0.01979   0.01100  -0.0821   0.0481   1.0000
   7.750   1.1833   0.02130   0.01227  -0.0800   0.0148   1.0000
   8.000   1.1996   0.02234   0.01337  -0.0783   0.0088   1.0000
   8.250   1.2159   0.02333   0.01448  -0.0767   0.0073   1.0000
   8.500   1.2302   0.02447   0.01579  -0.0747   0.0065   1.0000
   8.750   1.2427   0.02558   0.01708  -0.0725   0.0061   1.0000
   9.000   1.2535   0.02675   0.01843  -0.0701   0.0059   1.0000
   9.250   1.2621   0.02805   0.01991  -0.0675   0.0057   1.0000
   9.500   1.2688   0.02950   0.02153  -0.0648   0.0055   1.0000
   9.750   1.2742   0.03107   0.02327  -0.0622   0.0054   1.0000
  10.000   1.2784   0.03281   0.02518  -0.0596   0.0053   1.0000
  10.250   1.2819   0.03471   0.02723  -0.0572   0.0053   1.0000
  10.500   1.2853   0.03673   0.02948  -0.0550   0.0052   1.0000
  10.750   1.2877   0.03898   0.03191  -0.0529   0.0051   1.0000
  11.000   1.2903   0.04134   0.03445  -0.0510   0.0051   1.0000
  11.250   1.2923   0.04390   0.03719  -0.0493   0.0050   1.0000
  11.500   1.2935   0.04665   0.04015  -0.0477   0.0050   1.0000
  11.750   1.2937   0.04952   0.04322  -0.0464   0.0048   1.0000
  12.000   1.2923   0.05261   0.04653  -0.0454   0.0048   1.0000
  12.250   1.2898   0.05574   0.04986  -0.0447   0.0046   1.0000
  12.500   1.2854   0.05921   0.05352  -0.0444   0.0044   1.0000
  12.750   1.2798   0.06284   0.05730  -0.0446   0.0042   1.0000
  13.000   1.2719   0.06714   0.06181  -0.0451   0.0041   1.0000
  13.250   1.2619   0.07193   0.06678  -0.0462   0.0040   1.0000
  13.500   1.2507   0.07726   0.07232  -0.0478   0.0039   1.0000
  13.750   1.2383   0.08309   0.07837  -0.0500   0.0039   1.0000
  14.000   1.2244   0.08958   0.08506  -0.0529   0.0038   1.0000
  14.250   1.2110   0.09643   0.09212  -0.0564   0.0038   1.0000
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