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HQ 2.5/12 AIRFOIL (hq2512-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/12 AIRFOIL (hq2512-il)
Reynolds number: 100,000
Max Cl/Cd: 55.19 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2512-il-100000.txt
Download as CSV file: xf-hq2512-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/12 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3814   0.10197   0.09708  -0.0381   1.0000   0.1151
  -9.500  -0.4028   0.09879   0.09405  -0.0425   1.0000   0.1203
  -9.250  -0.4379   0.09527   0.09071  -0.0481   1.0000   0.1212
  -9.000  -0.3896   0.09172   0.08704  -0.0404   1.0000   0.1269
  -8.750  -0.3948   0.08877   0.08417  -0.0409   1.0000   0.1313
  -8.500  -0.4412   0.08580   0.08147  -0.0448   1.0000   0.1349
  -8.250  -0.4807   0.08336   0.07919  -0.0448   1.0000   0.1351
  -8.000  -0.4289   0.08017   0.07591  -0.0389   1.0000   0.1421
  -7.750  -0.4552   0.07852   0.07441  -0.0359   1.0000   0.1440
  -7.500  -0.4843   0.07648   0.07248  -0.0341   1.0000   0.1446
  -7.250  -0.5234   0.07363   0.06969  -0.0346   1.0000   0.1478
  -6.500  -0.5769   0.05016   0.04493  -0.0395   1.0000   0.0814
  -6.250  -0.5681   0.04311   0.03686  -0.0387   1.0000   0.0648
  -6.000  -0.5553   0.03918   0.03258  -0.0379   1.0000   0.0640
  -5.750  -0.5390   0.03675   0.02948  -0.0370   1.0000   0.0655
  -5.500  -0.5222   0.03342   0.02607  -0.0368   1.0000   0.0692
  -5.250  -0.4893   0.03091   0.02317  -0.0384   0.9964   0.0727
  -5.000  -0.4526   0.02875   0.02030  -0.0402   0.9919   0.0801
  -4.750  -0.4184   0.02704   0.01851  -0.0420   0.9870   0.0891
  -4.500  -0.3806   0.02564   0.01694  -0.0443   0.9827   0.1007
  -4.250  -0.3489   0.02451   0.01572  -0.0454   0.9770   0.1121
  -4.000  -0.3131   0.02355   0.01467  -0.0471   0.9720   0.1242
  -3.750  -0.2787   0.02273   0.01392  -0.0486   0.9668   0.1388
  -3.500  -0.2486   0.02198   0.01332  -0.0494   0.9606   0.1582
  -3.250  -0.2118   0.02110   0.01276  -0.0516   0.9559   0.2063
  -3.000  -0.1951   0.01912   0.01266  -0.0503   0.9494   0.5244
  -2.750  -0.1679   0.01962   0.01338  -0.0490   0.9429   0.6537
  -2.500  -0.1451   0.02009   0.01383  -0.0473   0.9353   0.7020
  -2.250  -0.1173   0.02050   0.01419  -0.0464   0.9287   0.7396
  -2.000  -0.0958   0.02081   0.01444  -0.0445   0.9212   0.7693
  -1.750  -0.0706   0.02103   0.01463  -0.0431   0.9143   0.7998
  -1.500  -0.0538   0.02119   0.01478  -0.0401   0.9066   0.8299
  -1.250  -0.0314   0.02123   0.01481  -0.0379   0.8997   0.8620
  -1.000  -0.0128   0.02127   0.01481  -0.0355   0.8917   0.8891
  -0.750   0.0213   0.02129   0.01478  -0.0360   0.8855   0.9162
  -0.500   0.0679   0.02146   0.01485  -0.0393   0.8799   0.9413
  -0.250   0.1223   0.02162   0.01491  -0.0449   0.8735   0.9568
   0.000   0.1886   0.02165   0.01482  -0.0524   0.8698   0.9666
   0.250   0.2464   0.02176   0.01486  -0.0589   0.8634   0.9770
   0.500   0.3092   0.02171   0.01474  -0.0660   0.8581   0.9857
   0.750   0.3776   0.02139   0.01436  -0.0736   0.8548   0.9922
   1.000   0.4157   0.02123   0.01418  -0.0763   0.8437   1.0000
   1.250   0.4352   0.02095   0.01388  -0.0750   0.8315   1.0000
   1.500   0.4864   0.02014   0.01303  -0.0783   0.8247   1.0000
   1.750   0.4908   0.02017   0.01304  -0.0747   0.8116   1.0000
   2.000   0.5050   0.02024   0.01308  -0.0727   0.7994   1.0000
   2.250   0.5316   0.02017   0.01298  -0.0725   0.7890   1.0000
   2.500   0.5712   0.01967   0.01247  -0.0738   0.7818   1.0000
   2.750   0.5962   0.01966   0.01244  -0.0732   0.7696   1.0000
   3.000   0.6246   0.01952   0.01233  -0.0729   0.7581   1.0000
   3.250   0.6566   0.01920   0.01201  -0.0729   0.7474   1.0000
   3.500   0.6926   0.01868   0.01148  -0.0732   0.7375   1.0000
   3.750   0.7204   0.01847   0.01129  -0.0726   0.7238   1.0000
   4.000   0.7490   0.01820   0.01104  -0.0720   0.7095   1.0000
   4.250   0.7783   0.01789   0.01073  -0.0714   0.6945   1.0000
   4.500   0.8046   0.01769   0.01058  -0.0704   0.6768   1.0000
   4.750   0.8305   0.01750   0.01040  -0.0693   0.6569   1.0000
   5.000   0.8593   0.01718   0.01006  -0.0686   0.6366   1.0000
   5.250   0.8829   0.01708   0.00996  -0.0672   0.6106   1.0000
   5.500   0.9070   0.01699   0.00986  -0.0658   0.5817   1.0000
   5.750   0.9307   0.01701   0.00977  -0.0644   0.5495   1.0000
   6.000   0.9514   0.01724   0.00990  -0.0628   0.5120   1.0000
   6.250   0.9724   0.01765   0.01009  -0.0612   0.4754   1.0000
   6.500   0.9918   0.01824   0.01052  -0.0596   0.4394   1.0000
   6.750   1.0114   0.01893   0.01102  -0.0582   0.4077   1.0000
   7.000   1.0308   0.01968   0.01163  -0.0568   0.3790   1.0000
   7.250   1.0500   0.02047   0.01230  -0.0555   0.3531   1.0000
   7.500   1.0698   0.02131   0.01299  -0.0543   0.3302   1.0000
   7.750   1.0889   0.02217   0.01384  -0.0530   0.3081   1.0000
   8.000   1.1094   0.02315   0.01466  -0.0520   0.2883   1.0000
   8.250   1.1278   0.02410   0.01565  -0.0507   0.2688   1.0000
   8.500   1.1471   0.02512   0.01666  -0.0496   0.2510   1.0000
   8.750   1.1660   0.02614   0.01765  -0.0484   0.2342   1.0000
   9.000   1.1843   0.02717   0.01869  -0.0472   0.2185   1.0000
   9.250   1.2020   0.02822   0.01976  -0.0459   0.2038   1.0000
   9.500   1.2185   0.02927   0.02086  -0.0444   0.1901   1.0000
   9.750   1.2347   0.03041   0.02210  -0.0429   0.1774   1.0000
  10.000   1.2504   0.03163   0.02344  -0.0414   0.1657   1.0000
  10.250   1.2625   0.03273   0.02462  -0.0395   0.1539   1.0000
  10.500   1.2687   0.03357   0.02550  -0.0369   0.1423   1.0000
  10.750   1.2669   0.03418   0.02609  -0.0333   0.1313   1.0000
  11.000   1.2624   0.03494   0.02694  -0.0296   0.1209   1.0000
  11.250   1.2585   0.03607   0.02825  -0.0265   0.1105   1.0000
  11.500   1.2567   0.03756   0.02986  -0.0241   0.0999   1.0000
  11.750   1.2533   0.03941   0.03179  -0.0218   0.0887   1.0000
  12.000   1.2460   0.04183   0.03427  -0.0197   0.0758   1.0000
  12.250   1.2371   0.04483   0.03729  -0.0178   0.0634   1.0000
  12.500   1.2289   0.04814   0.04060  -0.0164   0.0538   1.0000
  12.750   1.2252   0.05106   0.04354  -0.0154   0.0480   1.0000
  13.000   1.2237   0.05429   0.04691  -0.0145   0.0436   1.0000
  13.250   1.2229   0.05736   0.05015  -0.0139   0.0403   1.0000
  13.500   1.2226   0.06041   0.05322  -0.0136   0.0379   1.0000
  13.750   1.2264   0.06401   0.05689  -0.0128   0.0361   1.0000
  14.000   1.2230   0.06789   0.06107  -0.0127   0.0352   1.0000
  14.250   1.2166   0.07220   0.06567  -0.0130   0.0345   1.0000
  14.500   1.2074   0.07691   0.07065  -0.0137   0.0340   1.0000
  14.750   1.1947   0.08223   0.07624  -0.0151   0.0337   1.0000
  15.000   1.1794   0.08809   0.08237  -0.0172   0.0336   1.0000
  15.250   1.1604   0.09485   0.08939  -0.0202   0.0336   1.0000
  15.500   1.1400   0.10228   0.09705  -0.0240   0.0338   1.0000
  15.750   1.1167   0.11078   0.10578  -0.0290   0.0341   1.0000
  16.000   1.0927   0.12009   0.11529  -0.0349   0.0347   1.0000
  16.250   1.0666   0.13065   0.12601  -0.0417   0.0353   1.0000
  16.500   1.0412   0.14180   0.13726  -0.0489   0.0360   1.0000
  16.750   0.9396   0.18433   0.17970  -0.0734   0.0480   1.0000
  17.000   0.9412   0.18996   0.18531  -0.0761   0.0475   1.0000
  17.250   0.9431   0.19571   0.19103  -0.0789   0.0473   1.0000
  17.500   0.9494   0.19990   0.19523  -0.0805   0.0467   1.0000
  17.750   0.7393   0.20731   0.20338  -0.0773   0.0934   1.0000
  18.000   0.7262   0.20974   0.20577  -0.0813   0.0926   1.0000
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