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HQ 3.0/9 AIRFOIL (hq309-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/9 AIRFOIL (hq309-il)
Reynolds number: 50,000
Max Cl/Cd: 39.24 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq309-il-50000.txt
Download as CSV file: xf-hq309-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/9 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3718   0.09895   0.09244  -0.0254   1.0000   0.2249
  -7.750  -0.3930   0.09864   0.09232  -0.0253   1.0000   0.2328
  -7.500  -0.3883   0.09551   0.08927  -0.0235   1.0000   0.2461
  -7.250  -0.3879   0.09282   0.08668  -0.0216   1.0000   0.2596
  -7.000  -0.3895   0.09041   0.08437  -0.0193   1.0000   0.2732
  -6.750  -0.3967   0.08845   0.08254  -0.0167   1.0000   0.2874
  -6.500  -0.4064   0.08672   0.08095  -0.0142   1.0000   0.3021
  -6.250  -0.3931   0.08327   0.07753  -0.0106   1.0000   0.3247
  -6.000  -0.4094   0.08220   0.07662  -0.0077   1.0000   0.3436
  -5.750  -0.4056   0.07974   0.07423  -0.0036   1.0000   0.3703
  -5.500  -0.4091   0.07792   0.07250   0.0006   1.0000   0.3987
  -5.250  -0.3977   0.07526   0.06984   0.0058   1.0000   0.4385
  -4.000  -0.3209   0.04396   0.03666  -0.0490   1.0000   0.1468
  -3.750  -0.2903   0.03988   0.03198  -0.0508   1.0000   0.1300
  -3.500  -0.2576   0.03680   0.02794  -0.0522   1.0000   0.1211
  -3.250  -0.2303   0.03392   0.02472  -0.0525   1.0000   0.1182
  -3.000  -0.2010   0.03145   0.02174  -0.0526   1.0000   0.1157
  -2.750  -0.1727   0.02945   0.01928  -0.0522   1.0000   0.1174
  -2.500  -0.1470   0.02779   0.01740  -0.0518   1.0000   0.1297
  -2.250  -0.1220   0.02624   0.01570  -0.0507   1.0000   0.1429
  -2.000  -0.0982   0.02487   0.01433  -0.0496   1.0000   0.1741
  -1.750  -0.0709   0.02338   0.01304  -0.0493   1.0000   0.2276
  -1.500  -0.0569   0.02031   0.01274  -0.0443   1.0000   0.7497
  -1.250  -0.0486   0.01952   0.01192  -0.0388   1.0000   1.0000
  -1.000  -0.0236   0.01983   0.01164  -0.0393   1.0000   1.0000
  -0.750   0.0005   0.02019   0.01155  -0.0397   1.0000   1.0000
  -0.500   0.0240   0.02059   0.01159  -0.0401   1.0000   1.0000
  -0.250   0.0468   0.02103   0.01172  -0.0404   1.0000   1.0000
   0.000   0.0691   0.02151   0.01189  -0.0406   1.0000   1.0000
   0.250   0.0909   0.02204   0.01218  -0.0408   1.0000   1.0000
   0.500   0.1122   0.02260   0.01255  -0.0409   1.0000   1.0000
   0.750   0.1331   0.02322   0.01298  -0.0411   1.0000   1.0000
   1.000   0.1535   0.02388   0.01347  -0.0412   1.0000   1.0000
   1.250   0.1735   0.02458   0.01405  -0.0414   1.0000   1.0000
   1.500   0.1930   0.02535   0.01471  -0.0415   1.0000   1.0000
   1.750   0.2120   0.02616   0.01544  -0.0416   1.0000   1.0000
   2.000   0.2462   0.02740   0.01661  -0.0448   0.9924   1.0000
   2.250   0.2952   0.02890   0.01804  -0.0505   0.9749   1.0000
   2.500   0.3469   0.03036   0.01948  -0.0564   0.9565   1.0000
   2.750   0.3911   0.03149   0.02064  -0.0606   0.9361   1.0000
   3.000   0.4418   0.03259   0.02179  -0.0656   0.9156   1.0000
   3.250   0.4819   0.03344   0.02272  -0.0685   0.8937   1.0000
   3.500   0.5348   0.03418   0.02358  -0.0731   0.8732   1.0000
   3.750   0.5706   0.03476   0.02433  -0.0747   0.8499   1.0000
   4.000   0.6146   0.03513   0.02486  -0.0771   0.8269   1.0000
   4.250   0.6717   0.03489   0.02486  -0.0806   0.8045   1.0000
   4.500   0.7148   0.03460   0.02487  -0.0818   0.7791   1.0000
   4.750   0.7636   0.03381   0.02436  -0.0830   0.7536   1.0000
   5.000   0.8126   0.03255   0.02340  -0.0834   0.7278   1.0000
   5.250   0.8618   0.03088   0.02211  -0.0832   0.7003   1.0000
   5.500   0.9112   0.02889   0.02041  -0.0824   0.6696   1.0000
   5.750   0.9492   0.02755   0.01924  -0.0804   0.6315   1.0000
   6.000   0.9847   0.02648   0.01824  -0.0783   0.5879   1.0000
   6.250   1.0132   0.02617   0.01793  -0.0759   0.5400   1.0000
   6.500   1.0380   0.02645   0.01805  -0.0735   0.4911   1.0000
   6.750   1.0596   0.02721   0.01862  -0.0712   0.4435   1.0000
   7.000   1.0787   0.02827   0.01950  -0.0689   0.3970   1.0000
   7.250   1.0969   0.02948   0.02047  -0.0666   0.3516   1.0000
   7.500   1.1128   0.03094   0.02174  -0.0643   0.3074   1.0000
   7.750   1.1279   0.03276   0.02350  -0.0620   0.2641   1.0000
   8.000   1.1430   0.03476   0.02531  -0.0598   0.2242   1.0000
   8.250   1.1610   0.03733   0.02793  -0.0580   0.1929   1.0000
   8.500   1.1763   0.03958   0.03019  -0.0561   0.1669   1.0000
   8.750   1.1975   0.04276   0.03344  -0.0548   0.1477   1.0000
   9.000   1.2098   0.04584   0.03675  -0.0526   0.1297   1.0000
   9.250   1.2176   0.04909   0.04034  -0.0500   0.1135   1.0000
   9.500   1.2266   0.05105   0.04195  -0.0483   0.0931   1.0000
   9.750   1.2252   0.05482   0.04644  -0.0450   0.0863   1.0000
  10.000   1.2353   0.05926   0.05093  -0.0435   0.0801   1.0000
  10.250   1.2259   0.06353   0.05582  -0.0403   0.0786   1.0000
  10.500   1.2126   0.06781   0.06056  -0.0374   0.0775   1.0000
  10.750   1.1959   0.07198   0.06507  -0.0347   0.0773   1.0000
  11.000   1.1763   0.07621   0.06956  -0.0324   0.0776   1.0000
  11.250   1.1556   0.08083   0.07439  -0.0312   0.0782   1.0000
  11.500   1.1339   0.08592   0.07966  -0.0312   0.0789   1.0000
  11.750   1.1139   0.09155   0.08543  -0.0322   0.0796   1.0000
  12.000   1.0959   0.09773   0.09170  -0.0340   0.0803   1.0000
  12.250   1.0794   0.10441   0.09845  -0.0365   0.0809   1.0000
  12.500   1.0169   0.11986   0.11406  -0.0494   0.0941   1.0000
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