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HQ 2.0/8 AIRFOIL (hq208-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.0/8 AIRFOIL (hq208-il)
Reynolds number: 200,000
Max Cl/Cd: 74.61 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq208-il-200000.txt
Download as CSV file: xf-hq208-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/8 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3766   0.09623   0.09289  -0.0218   1.0000   0.0334
  -9.250  -0.3738   0.09250   0.08918  -0.0226   1.0000   0.0343
  -9.000  -0.4635   0.09607   0.09258  -0.0247   1.0000   0.0316
  -8.750  -0.4575   0.09283   0.08936  -0.0244   1.0000   0.0324
  -8.500  -0.4532   0.08964   0.08618  -0.0249   1.0000   0.0332
  -8.250  -0.4507   0.08629   0.08288  -0.0259   1.0000   0.0342
  -8.000  -0.4501   0.08289   0.07953  -0.0272   1.0000   0.0352
  -7.750  -0.4518   0.07950   0.07618  -0.0287   1.0000   0.0359
  -7.500  -0.4561   0.07601   0.07276  -0.0305   1.0000   0.0364
  -7.250  -0.4567   0.07152   0.06831  -0.0349   1.0000   0.0371
  -7.000  -0.4557   0.06702   0.06381  -0.0388   1.0000   0.0379
  -6.750  -0.4539   0.06258   0.05932  -0.0416   1.0000   0.0392
  -6.500  -0.4489   0.05844   0.05496  -0.0446   1.0000   0.0416
  -6.250  -0.4439   0.05648   0.05263  -0.0448   1.0000   0.0426
  -6.000  -0.4440   0.05200   0.04795  -0.0440   1.0000   0.0431
  -5.750  -0.4419   0.04682   0.04288  -0.0430   1.0000   0.0444
  -5.500  -0.4347   0.04415   0.04022  -0.0415   1.0000   0.0459
  -5.250  -0.4249   0.04166   0.03763  -0.0404   1.0000   0.0479
  -5.000  -0.4117   0.03902   0.03475  -0.0396   1.0000   0.0518
  -4.750  -0.3962   0.03567   0.03089  -0.0393   1.0000   0.0576
  -4.500  -0.3807   0.03308   0.02823  -0.0386   1.0000   0.0601
  -4.250  -0.3495   0.03032   0.02510  -0.0407   0.9974   0.0723
  -4.000  -0.3069   0.02398   0.01781  -0.0408   0.9953   0.0385
  -3.750  -0.2670   0.02143   0.01452  -0.0414   0.9923   0.0306
  -3.500  -0.2324   0.01871   0.01147  -0.0426   0.9891   0.0298
  -3.250  -0.1959   0.01707   0.00959  -0.0440   0.9856   0.0303
  -3.000  -0.1605   0.01493   0.00740  -0.0455   0.9830   0.0336
  -2.750  -0.1256   0.01406   0.00652  -0.0471   0.9782   0.0453
  -2.500  -0.0899   0.01278   0.00535  -0.0488   0.9734   0.0953
  -2.000  -0.0310   0.01034   0.00531  -0.0503   0.9635   0.7122
  -1.750   0.0035   0.01027   0.00526  -0.0513   0.9579   0.7625
  -1.500   0.0372   0.01019   0.00522  -0.0520   0.9528   0.8076
  -1.250   0.0667   0.01006   0.00511  -0.0517   0.9458   0.8481
  -1.000   0.1008   0.00986   0.00501  -0.0519   0.9422   0.9037
  -0.750   0.1466   0.00974   0.00489  -0.0549   0.9384   0.9515
  -0.500   0.2008   0.00960   0.00466  -0.0604   0.9347   0.9777
  -0.250   0.2553   0.00940   0.00438  -0.0660   0.9308   0.9985
   0.000   0.2884   0.00924   0.00414  -0.0673   0.9200   1.0000
   0.250   0.3193   0.00909   0.00392  -0.0678   0.9086   1.0000
   0.500   0.3484   0.00899   0.00375  -0.0678   0.8974   1.0000
   0.750   0.3759   0.00892   0.00361  -0.0674   0.8856   1.0000
   1.000   0.4023   0.00889   0.00352  -0.0668   0.8738   1.0000
   1.250   0.4278   0.00892   0.00352  -0.0662   0.8618   1.0000
   1.500   0.4535   0.00895   0.00355  -0.0655   0.8497   1.0000
   1.750   0.4793   0.00898   0.00356  -0.0648   0.8373   1.0000
   2.000   0.5051   0.00902   0.00358  -0.0642   0.8243   1.0000
   2.250   0.5310   0.00904   0.00360  -0.0635   0.8106   1.0000
   2.500   0.5568   0.00906   0.00362  -0.0627   0.7958   1.0000
   2.750   0.5827   0.00908   0.00367  -0.0620   0.7800   1.0000
   3.000   0.6083   0.00912   0.00371  -0.0612   0.7617   1.0000
   3.250   0.6338   0.00915   0.00375  -0.0603   0.7407   1.0000
   3.500   0.6590   0.00921   0.00380  -0.0594   0.7155   1.0000
   3.750   0.6835   0.00930   0.00383  -0.0583   0.6815   1.0000
   4.000   0.7066   0.00947   0.00389  -0.0569   0.6308   1.0000
   4.250   0.7287   0.00980   0.00399  -0.0555   0.5643   1.0000
   4.500   0.7497   0.01033   0.00420  -0.0540   0.4869   1.0000
   4.750   0.7700   0.01103   0.00455  -0.0527   0.4109   1.0000
   5.000   0.7905   0.01178   0.00499  -0.0516   0.3416   1.0000
   5.250   0.8117   0.01251   0.00553  -0.0507   0.2864   1.0000
   5.500   0.8337   0.01321   0.00607  -0.0499   0.2397   1.0000
   5.750   0.8537   0.01420   0.00669  -0.0489   0.1557   1.0000
   6.000   0.8705   0.01577   0.00777  -0.0474   0.0916   1.0000
   6.250   0.8914   0.01674   0.00870  -0.0464   0.0721   1.0000
   6.500   0.9136   0.01748   0.00941  -0.0458   0.0566   1.0000
   6.750   0.9349   0.01839   0.01039  -0.0449   0.0459   1.0000
   7.000   0.9522   0.01999   0.01199  -0.0433   0.0298   1.0000
   7.250   0.9704   0.02173   0.01391  -0.0416   0.0228   1.0000
   7.500   0.9884   0.02367   0.01592  -0.0401   0.0201   1.0000
   7.750   1.0064   0.02759   0.02005  -0.0385   0.0187   1.0000
   8.000   1.0273   0.03002   0.02279  -0.0373   0.0183   1.0000
   8.250   1.0469   0.03179   0.02490  -0.0359   0.0170   1.0000
   8.500   1.0646   0.03354   0.02695  -0.0346   0.0151   1.0000
   8.750   1.0780   0.03651   0.03031  -0.0328   0.0144   1.0000
   9.000   1.0856   0.04045   0.03474  -0.0304   0.0144   1.0000
   9.250   1.0863   0.04494   0.03974  -0.0277   0.0146   1.0000
   9.500   1.0809   0.04958   0.04482  -0.0249   0.0150   1.0000
   9.750   1.0697   0.05402   0.04963  -0.0221   0.0154   1.0000
  10.000   1.0532   0.05777   0.05363  -0.0190   0.0157   1.0000
  10.250   1.0338   0.06163   0.05771  -0.0169   0.0159   1.0000
  10.500   1.0144   0.06585   0.06212  -0.0164   0.0161   1.0000
  10.750   0.9932   0.07096   0.06740  -0.0177   0.0162   1.0000
  11.000   0.9736   0.07670   0.07329  -0.0206   0.0165   1.0000
  11.250   0.9527   0.08394   0.08067  -0.0257   0.0165   1.0000
  11.500   0.9322   0.09304   0.08988  -0.0327   0.0167   1.0000
  11.750   0.9125   0.10447   0.10136  -0.0409   0.0170   1.0000
  12.000   0.8979   0.11464   0.11151  -0.0467   0.0177   1.0000
  12.250   0.8857   0.12383   0.12067  -0.0513   0.0182   1.0000
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