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HQ 2.1/9.5 AIRFOIL (hq2195-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.1/9.5 AIRFOIL (hq2195-il)
Reynolds number: 200,000
Max Cl/Cd: 74.51 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2195-il-200000.txt
Download as CSV file: xf-hq2195-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.1/9.5 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4696   0.08974   0.08616  -0.0391   1.0000   0.0537
  -9.000  -0.4851   0.08392   0.08040  -0.0459   1.0000   0.0539
  -8.750  -0.5015   0.07993   0.07639  -0.0491   1.0000   0.0540
  -8.500  -0.5135   0.07637   0.07274  -0.0509   1.0000   0.0542
  -8.250  -0.5080   0.06973   0.06628  -0.0496   1.0000   0.0556
  -8.000  -0.4991   0.06765   0.06427  -0.0474   1.0000   0.0568
  -7.750  -0.4997   0.06482   0.06144  -0.0470   1.0000   0.0578
  -7.500  -0.5036   0.06186   0.05848  -0.0465   1.0000   0.0592
  -7.250  -0.5107   0.05899   0.05557  -0.0454   1.0000   0.0606
  -7.000  -0.5191   0.05628   0.05278  -0.0437   1.0000   0.0624
  -6.750  -0.5328   0.05578   0.05161  -0.0421   1.0000   0.0668
  -6.500  -0.5366   0.04949   0.04527  -0.0414   1.0000   0.0682
  -6.250  -0.5170   0.04602   0.04192  -0.0423   0.9981   0.0701
  -6.000  -0.4860   0.04299   0.03875  -0.0456   0.9944   0.0748
  -5.750  -0.4566   0.03913   0.03451  -0.0492   0.9894   0.0845
  -5.500  -0.4231   0.03642   0.03133  -0.0527   0.9851   0.0967
  -5.250  -0.3840   0.02619   0.01985  -0.0533   0.9832   0.0488
  -5.000  -0.3537   0.02319   0.01632  -0.0538   0.9788   0.0468
  -4.750  -0.3202   0.02169   0.01457  -0.0552   0.9750   0.0488
  -4.500  -0.2845   0.01992   0.01251  -0.0566   0.9723   0.0490
  -4.250  -0.2472   0.01857   0.01098  -0.0584   0.9701   0.0502
  -4.000  -0.2189   0.01764   0.00994  -0.0585   0.9647   0.0520
  -3.750  -0.1862   0.01665   0.00887  -0.0596   0.9610   0.0557
  -3.500  -0.1512   0.01571   0.00799  -0.0612   0.9581   0.0603
  -3.250  -0.1132   0.01508   0.00731  -0.0633   0.9559   0.0670
  -3.000  -0.0875   0.01440   0.00669  -0.0633   0.9498   0.0795
  -2.750  -0.0548   0.01347   0.00599  -0.0647   0.9460   0.1256
  -2.500  -0.0266   0.01145   0.00584  -0.0661   0.9432   0.5670
  -2.250   0.0093   0.01139   0.00600  -0.0673   0.9410   0.6626
  -2.000   0.0308   0.01150   0.00615  -0.0658   0.9340   0.7047
  -1.750   0.0657   0.01145   0.00615  -0.0666   0.9297   0.7392
  -1.500   0.1030   0.01129   0.00602  -0.0675   0.9234   0.7713
  -1.250   0.1333   0.01113   0.00591  -0.0666   0.9142   0.8035
  -1.000   0.1592   0.01106   0.00587  -0.0652   0.9064   0.8298
  -0.750   0.1862   0.01098   0.00578  -0.0644   0.9002   0.8465
  -0.500   0.2173   0.01084   0.00561  -0.0646   0.8959   0.8598
  -0.250   0.2393   0.01080   0.00558  -0.0631   0.8874   0.8740
   0.000   0.2681   0.01065   0.00541  -0.0628   0.8823   0.8879
   0.250   0.2909   0.01057   0.00536  -0.0615   0.8741   0.9035
   0.500   0.3191   0.01041   0.00519  -0.0610   0.8680   0.9193
   0.750   0.3478   0.01030   0.00511  -0.0608   0.8601   0.9370
   1.000   0.3851   0.01014   0.00495  -0.0624   0.8535   0.9537
   1.250   0.4265   0.01003   0.00486  -0.0650   0.8452   0.9710
   1.500   0.4709   0.00987   0.00468  -0.0682   0.8374   0.9891
   1.750   0.4992   0.00984   0.00466  -0.0687   0.8264   1.0000
   2.000   0.5238   0.00983   0.00462  -0.0681   0.8155   1.0000
   2.250   0.5508   0.00980   0.00455  -0.0677   0.8043   1.0000
   2.500   0.5779   0.00976   0.00449  -0.0673   0.7916   1.0000
   2.750   0.6043   0.00973   0.00445  -0.0667   0.7766   1.0000
   3.000   0.6296   0.00970   0.00441  -0.0659   0.7571   1.0000
   3.250   0.6553   0.00962   0.00427  -0.0649   0.7327   1.0000
   3.500   0.6798   0.00960   0.00420  -0.0637   0.6997   1.0000
   3.750   0.7042   0.00964   0.00416  -0.0626   0.6602   1.0000
   4.000   0.7280   0.00977   0.00415  -0.0615   0.6061   1.0000
   4.250   0.7496   0.01017   0.00419  -0.0600   0.5384   1.0000
   4.500   0.7709   0.01074   0.00446  -0.0588   0.4846   1.0000
   4.750   0.7934   0.01127   0.00480  -0.0578   0.4446   1.0000
   5.000   0.8162   0.01180   0.00517  -0.0570   0.4094   1.0000
   5.250   0.8390   0.01230   0.00555  -0.0562   0.3745   1.0000
   5.500   0.8611   0.01283   0.00595  -0.0553   0.3347   1.0000
   5.750   0.8826   0.01340   0.00634  -0.0544   0.2858   1.0000
   6.000   0.9028   0.01414   0.00680  -0.0534   0.2215   1.0000
   6.250   0.9204   0.01524   0.00748  -0.0521   0.1548   1.0000
   6.500   0.9388   0.01634   0.00832  -0.0509   0.1193   1.0000
   6.750   0.9586   0.01729   0.00919  -0.0497   0.0975   1.0000
   7.000   0.9770   0.01839   0.01019  -0.0484   0.0808   1.0000
   7.250   0.9955   0.01950   0.01126  -0.0471   0.0681   1.0000
   7.500   1.0145   0.02064   0.01245  -0.0458   0.0601   1.0000
   7.750   1.0319   0.02215   0.01388  -0.0444   0.0547   1.0000
   8.000   1.0532   0.02328   0.01513  -0.0433   0.0511   1.0000
   8.250   1.0742   0.02427   0.01619  -0.0424   0.0474   1.0000
   8.500   1.0946   0.02583   0.01772  -0.0416   0.0445   1.0000
   8.750   1.1172   0.02790   0.01994  -0.0409   0.0426   1.0000
   9.000   1.1387   0.02926   0.02152  -0.0400   0.0406   1.0000
   9.250   1.1588   0.03060   0.02302  -0.0390   0.0384   1.0000
   9.500   1.1781   0.03210   0.02463  -0.0381   0.0367   1.0000
   9.750   1.1975   0.03428   0.02692  -0.0373   0.0354   1.0000
  10.000   1.2124   0.03885   0.03181  -0.0364   0.0342   1.0000
  10.250   1.2227   0.04045   0.03379  -0.0342   0.0334   1.0000
  10.500   1.2298   0.04266   0.03637  -0.0319   0.0323   1.0000
  10.750   1.2326   0.04556   0.03965  -0.0294   0.0316   1.0000
  11.000   1.2293   0.04893   0.04339  -0.0265   0.0313   1.0000
  11.250   1.2190   0.05226   0.04704  -0.0231   0.0312   1.0000
  11.500   1.2030   0.05577   0.05084  -0.0197   0.0313   1.0000
  11.750   1.1839   0.05958   0.05492  -0.0172   0.0314   1.0000
  12.000   1.1622   0.06392   0.05951  -0.0158   0.0316   1.0000
  12.250   1.1390   0.06883   0.06465  -0.0157   0.0318   1.0000
  12.500   1.1145   0.07445   0.07048  -0.0169   0.0321   1.0000
  12.750   1.0893   0.08089   0.07710  -0.0196   0.0324   1.0000
  13.000   1.0626   0.08850   0.08487  -0.0240   0.0327   1.0000
  13.250   1.0356   0.09748   0.09399  -0.0299   0.0332   1.0000
  13.500   1.0084   0.10791   0.10450  -0.0369   0.0337   1.0000
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