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HQ 2.5/9 B AIRFOIL (hq259b-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/9 B AIRFOIL (hq259b-il)
Reynolds number: 50,000
Max Cl/Cd: 39.53 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq259b-il-50000-n5.txt
Download as CSV file: xf-hq259b-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/9 B AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4209   0.09935   0.09236  -0.0311   1.0000   0.1250
  -8.500  -0.4355   0.09030   0.08334  -0.0395   1.0000   0.0631
  -8.250  -0.4314   0.08694   0.08003  -0.0385   1.0000   0.0609
  -8.000  -0.4363   0.08344   0.07663  -0.0391   1.0000   0.0595
  -7.750  -0.4418   0.07934   0.07263  -0.0413   1.0000   0.0580
  -7.500  -0.4479   0.07495   0.06830  -0.0438   1.0000   0.0568
  -7.250  -0.4537   0.07077   0.06413  -0.0455   1.0000   0.0559
  -7.000  -0.4581   0.06673   0.06005  -0.0467   1.0000   0.0554
  -6.750  -0.4599   0.06288   0.05611  -0.0474   1.0000   0.0552
  -6.500  -0.4585   0.05928   0.05237  -0.0477   1.0000   0.0555
  -6.250  -0.4543   0.05560   0.04848  -0.0480   1.0000   0.0556
  -6.000  -0.4467   0.05178   0.04437  -0.0484   1.0000   0.0553
  -5.750  -0.4354   0.04788   0.04007  -0.0488   1.0000   0.0545
  -5.500  -0.4207   0.04434   0.03610  -0.0490   1.0000   0.0542
  -5.250  -0.4033   0.04118   0.03251  -0.0491   1.0000   0.0542
  -5.000  -0.3845   0.03855   0.02951  -0.0490   1.0000   0.0553
  -4.750  -0.3643   0.03637   0.02695  -0.0488   1.0000   0.0581
  -4.500  -0.3422   0.03418   0.02427  -0.0485   1.0000   0.0604
  -4.250  -0.3189   0.03210   0.02174  -0.0481   1.0000   0.0615
  -4.000  -0.2951   0.03031   0.01952  -0.0475   1.0000   0.0628
  -3.750  -0.2716   0.02880   0.01766  -0.0467   1.0000   0.0644
  -3.500  -0.2499   0.02754   0.01640  -0.0461   1.0000   0.0687
  -3.250  -0.2275   0.02659   0.01526  -0.0451   1.0000   0.0740
  -3.000  -0.2050   0.02570   0.01412  -0.0439   1.0000   0.0777
  -2.750  -0.1838   0.02476   0.01322  -0.0429   1.0000   0.0826
  -2.500  -0.1572   0.02408   0.01241  -0.0430   0.9982   0.0937
  -2.250  -0.1244   0.02334   0.01158  -0.0444   0.9944   0.1092
  -2.000  -0.0912   0.02241   0.01079  -0.0463   0.9904   0.1478
  -1.750  -0.0665   0.02005   0.01079  -0.0463   0.9881   0.6023
  -1.500  -0.0514   0.02001   0.01114  -0.0419   0.9827   0.7696
  -1.250  -0.0388   0.01970   0.01105  -0.0370   0.9762   0.8944
  -1.000   0.0083   0.01963   0.01070  -0.0413   0.9707   1.0000
  -0.750   0.0421   0.01987   0.01060  -0.0435   0.9647   1.0000
  -0.500   0.0783   0.02017   0.01060  -0.0460   0.9586   1.0000
  -0.250   0.1142   0.02048   0.01066  -0.0484   0.9518   1.0000
   0.000   0.1532   0.02079   0.01075  -0.0511   0.9433   1.0000
   0.250   0.1914   0.02102   0.01081  -0.0536   0.9322   1.0000
   0.500   0.2317   0.02124   0.01087  -0.0562   0.9206   1.0000
   0.750   0.2736   0.02141   0.01094  -0.0590   0.9097   1.0000
   1.000   0.3124   0.02157   0.01102  -0.0612   0.8988   1.0000
   1.250   0.3463   0.02173   0.01113  -0.0625   0.8872   1.0000
   1.500   0.3820   0.02187   0.01126  -0.0641   0.8761   1.0000
   1.750   0.4217   0.02196   0.01134  -0.0661   0.8659   1.0000
   2.000   0.4581   0.02201   0.01143  -0.0675   0.8546   1.0000
   2.250   0.4902   0.02209   0.01156  -0.0681   0.8415   1.0000
   2.500   0.5229   0.02212   0.01166  -0.0686   0.8279   1.0000
   2.750   0.5556   0.02211   0.01173  -0.0690   0.8136   1.0000
   3.000   0.5882   0.02205   0.01179  -0.0693   0.7984   1.0000
   3.250   0.6209   0.02194   0.01179  -0.0694   0.7823   1.0000
   3.500   0.6513   0.02184   0.01181  -0.0691   0.7639   1.0000
   3.750   0.6790   0.02177   0.01190  -0.0683   0.7423   1.0000
   4.000   0.7090   0.02161   0.01187  -0.0677   0.7199   1.0000
   4.250   0.7371   0.02148   0.01186  -0.0668   0.6935   1.0000
   4.500   0.7619   0.02147   0.01197  -0.0655   0.6609   1.0000
   4.750   0.7880   0.02142   0.01205  -0.0642   0.6236   1.0000
   5.000   0.8152   0.02134   0.01195  -0.0629   0.5808   1.0000
   5.250   0.8422   0.02142   0.01183  -0.0615   0.5332   1.0000
   5.500   0.8654   0.02189   0.01208  -0.0600   0.4852   1.0000
   5.750   0.8862   0.02261   0.01260  -0.0585   0.4412   1.0000
   6.000   0.9056   0.02344   0.01329  -0.0570   0.4005   1.0000
   6.250   0.9240   0.02430   0.01408  -0.0555   0.3617   1.0000
   6.500   0.9416   0.02519   0.01495  -0.0539   0.3222   1.0000
   6.750   0.9575   0.02617   0.01592  -0.0523   0.2789   1.0000
   7.000   0.9722   0.02731   0.01693  -0.0505   0.2326   1.0000
   7.250   0.9865   0.02870   0.01810  -0.0489   0.1906   1.0000
   7.500   1.0007   0.03029   0.01943  -0.0474   0.1582   1.0000
   7.750   1.0164   0.03192   0.02096  -0.0462   0.1333   1.0000
   8.000   1.0331   0.03361   0.02262  -0.0450   0.1146   1.0000
   8.250   1.0505   0.03536   0.02445  -0.0439   0.1006   1.0000
   8.500   1.0680   0.03721   0.02631  -0.0428   0.0902   1.0000
   8.750   1.0863   0.03903   0.02831  -0.0418   0.0809   1.0000
   9.000   1.1079   0.04128   0.03073  -0.0410   0.0748   1.0000
   9.250   1.1287   0.04360   0.03331  -0.0402   0.0696   1.0000
   9.500   1.1470   0.04599   0.03572  -0.0396   0.0651   1.0000
   9.750   1.1601   0.04864   0.03891  -0.0381   0.0609   1.0000
  10.000   1.1728   0.05161   0.04225  -0.0368   0.0582   1.0000
  10.250   1.1827   0.05463   0.04556  -0.0355   0.0561   1.0000
  10.500   1.1918   0.05760   0.04864  -0.0343   0.0538   1.0000
  10.750   1.1880   0.06107   0.05249  -0.0321   0.0524   1.0000
  11.000   1.1760   0.06456   0.05641  -0.0295   0.0513   1.0000
  11.250   1.1610   0.06840   0.06061  -0.0276   0.0505   1.0000
  11.500   1.1435   0.07268   0.06520  -0.0265   0.0500   1.0000
  11.750   1.1234   0.07758   0.07038  -0.0266   0.0498   1.0000
  12.000   1.1006   0.08330   0.07633  -0.0280   0.0499   1.0000
  12.250   1.0760   0.08998   0.08321  -0.0308   0.0503   1.0000
  12.500   1.0504   0.09781   0.09119  -0.0352   0.0509   1.0000
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