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HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/9.0 smoothed by Eppler (hq2590sm-il)
Reynolds number: 50,000
Max Cl/Cd: 39.54 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2590sm-il-50000-n5.txt
Download as CSV file: xf-hq2590sm-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/9.0 smoothed by Eppler                   
  
 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   0.09937   0.09238  -0.0311   1.0000   0.1250
  -8.500  -0.4354   0.09027   0.08331  -0.0394   1.0000   0.0630
  -8.250  -0.4316   0.08691   0.08001  -0.0385   1.0000   0.0610
  -8.000  -0.4365   0.08342   0.07662  -0.0391   1.0000   0.0595
  -7.750  -0.4419   0.07933   0.07263  -0.0413   1.0000   0.0582
  -7.500  -0.4479   0.07497   0.06833  -0.0438   1.0000   0.0570
  -7.250  -0.4536   0.07080   0.06416  -0.0455   1.0000   0.0560
  -7.000  -0.4582   0.06670   0.06002  -0.0468   1.0000   0.0553
  -6.750  -0.4598   0.06289   0.05612  -0.0474   1.0000   0.0552
  -6.500  -0.4585   0.05927   0.05235  -0.0477   1.0000   0.0555
  -6.250  -0.4542   0.05559   0.04847  -0.0480   1.0000   0.0556
  -6.000  -0.4467   0.05179   0.04438  -0.0484   1.0000   0.0553
  -5.750  -0.4354   0.04789   0.04008  -0.0488   1.0000   0.0545
  -5.500  -0.4206   0.04434   0.03610  -0.0491   1.0000   0.0542
  -5.250  -0.4033   0.04118   0.03251  -0.0491   1.0000   0.0542
  -5.000  -0.3844   0.03855   0.02950  -0.0490   1.0000   0.0553
  -4.750  -0.3643   0.03637   0.02695  -0.0488   1.0000   0.0580
  -4.500  -0.3421   0.03418   0.02427  -0.0485   1.0000   0.0604
  -4.250  -0.3188   0.03210   0.02173  -0.0481   1.0000   0.0615
  -4.000  -0.2951   0.03031   0.01951  -0.0475   1.0000   0.0628
  -3.750  -0.2715   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  -0.2274   0.02658   0.01525  -0.0451   1.0000   0.0741
  -3.000  -0.2049   0.02569   0.01411  -0.0439   1.0000   0.0777
  -2.750  -0.1838   0.02476   0.01322  -0.0429   1.0000   0.0827
  -2.500  -0.1572   0.02408   0.01241  -0.0430   0.9982   0.0938
  -2.250  -0.1243   0.02333   0.01158  -0.0444   0.9944   0.1093
  -2.000  -0.0912   0.02242   0.01079  -0.0463   0.9904   0.1471
  -1.750  -0.0665   0.02004   0.01080  -0.0463   0.9881   0.6058
  -1.500  -0.0515   0.02001   0.01115  -0.0419   0.9827   0.7699
  -1.250  -0.0388   0.01970   0.01106  -0.0370   0.9763   0.8955
  -1.000   0.0083   0.01963   0.01070  -0.0413   0.9707   1.0000
  -0.750   0.0421   0.01987   0.01060  -0.0435   0.9648   1.0000
  -0.500   0.0783   0.02017   0.01060  -0.0460   0.9587   1.0000
  -0.250   0.1143   0.02048   0.01066  -0.0484   0.9518   1.0000
   0.000   0.1534   0.02079   0.01075  -0.0512   0.9432   1.0000
   0.250   0.1914   0.02102   0.01081  -0.0536   0.9321   1.0000
   0.500   0.2318   0.02123   0.01087  -0.0562   0.9206   1.0000
   0.750   0.2737   0.02141   0.01094  -0.0591   0.9097   1.0000
   1.000   0.3124   0.02157   0.01101  -0.0612   0.8988   1.0000
   1.250   0.3464   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   0.8660   1.0000
   2.000   0.4581   0.02202   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   0.5555   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   0.6210   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   0.6791   0.02177   0.01190  -0.0683   0.7423   1.0000
   4.000   0.7090   0.02161   0.01187  -0.0677   0.7198   1.0000
   4.250   0.7371   0.02148   0.01187  -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  -0.0630   0.5808   1.0000
   5.250   0.8422   0.02142   0.01183  -0.0615   0.5332   1.0000
   5.500   0.8655   0.02189   0.01205  -0.0600   0.4853   1.0000
   5.750   0.8863   0.02261   0.01260  -0.0585   0.4411   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   0.9576   0.02617   0.01592  -0.0523   0.2790   1.0000
   7.000   0.9722   0.02732   0.01694  -0.0505   0.2324   1.0000
   7.250   0.9865   0.02870   0.01811  -0.0489   0.1906   1.0000
   7.500   1.0007   0.03029   0.01943  -0.0474   0.1581   1.0000
   7.750   1.0164   0.03192   0.02096  -0.0462   0.1333   1.0000
   8.000   1.0332   0.03361   0.02262  -0.0450   0.1146   1.0000
   8.250   1.0506   0.03536   0.02445  -0.0439   0.1006   1.0000
   8.500   1.0680   0.03721   0.02630  -0.0428   0.0903   1.0000
   8.750   1.0862   0.03903   0.02831  -0.0418   0.0808   1.0000
   9.000   1.1080   0.04128   0.03073  -0.0410   0.0748   1.0000
   9.250   1.1288   0.04360   0.03331  -0.0402   0.0696   1.0000
   9.500   1.1471   0.04600   0.03573  -0.0396   0.0651   1.0000
   9.750   1.1602   0.04864   0.03892  -0.0381   0.0609   1.0000
  10.000   1.1728   0.05161   0.04225  -0.0368   0.0582   1.0000
  10.250   1.1828   0.05463   0.04556  -0.0355   0.0561   1.0000
  10.500   1.1918   0.05760   0.04865  -0.0344   0.0539   1.0000
  10.750   1.1880   0.06108   0.05250  -0.0322   0.0524   1.0000
  11.000   1.1761   0.06457   0.05642  -0.0295   0.0513   1.0000
  11.250   1.1612   0.06841   0.06062  -0.0276   0.0505   1.0000
  11.500   1.1436   0.07270   0.06522  -0.0266   0.0500   1.0000
  11.750   1.1234   0.07760   0.07040  -0.0266   0.0498   1.0000
  12.000   1.1007   0.08331   0.07635  -0.0280   0.0499   1.0000
  12.250   1.0760   0.09001   0.08324  -0.0309   0.0503   1.0000
  12.500   1.0505   0.09785   0.09123  -0.0352   0.0509   1.0000
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