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HQ 2.5/8 AIRFOIL (hq258-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/8 AIRFOIL (hq258-il)
Reynolds number: 1,000,000
Max Cl/Cd: 124.09 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq258-il-1000000.txt
Download as CSV file: xf-hq258-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/8 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3970   0.08225   0.08070  -0.0307   1.0000   0.0073
  -7.750  -0.3986   0.07897   0.07746  -0.0315   1.0000   0.0073
  -7.500  -0.4057   0.07624   0.07477  -0.0311   1.0000   0.0073
  -7.250  -0.4182   0.07395   0.07252  -0.0298   1.0000   0.0073
  -7.000  -0.3926   0.06659   0.06515  -0.0428   0.9965   0.0073
  -6.750  -0.3658   0.05929   0.05777  -0.0541   0.9917   0.0073
  -6.500  -0.3392   0.05283   0.05119  -0.0623   0.9868   0.0073
  -6.250  -0.3101   0.04651   0.04471  -0.0695   0.9835   0.0073
  -6.000  -0.2804   0.04081   0.03881  -0.0749   0.9799   0.0073
  -5.750  -0.2539   0.03590   0.03368  -0.0782   0.9730   0.0073
  -5.500  -0.2344   0.02593   0.02312  -0.0818   0.9629   0.0079
  -5.250  -0.2109   0.02242   0.01927  -0.0826   0.9550   0.0084
  -5.000  -0.1882   0.02031   0.01692  -0.0823   0.9454   0.0089
  -4.750  -0.1640   0.01840   0.01477  -0.0820   0.9372   0.0094
  -4.250  -0.1135   0.01213   0.00765  -0.0797   0.9209   0.0062
  -4.000  -0.0879   0.01038   0.00563  -0.0789   0.9138   0.0061
  -3.750  -0.0618   0.00942   0.00452  -0.0784   0.9061   0.0067
  -3.500  -0.0354   0.00880   0.00377  -0.0780   0.8991   0.0078
  -3.250  -0.0092   0.00801   0.00281  -0.0776   0.8915   0.0085
  -3.000   0.0178   0.00759   0.00229  -0.0774   0.8843   0.0098
  -2.750   0.0450   0.00732   0.00194  -0.0771   0.8761   0.0113
  -2.500   0.0725   0.00706   0.00157  -0.0769   0.8674   0.0135
  -2.250   0.0997   0.00674   0.00133  -0.0767   0.8592   0.0513
  -2.000   0.1271   0.00655   0.00119  -0.0766   0.8511   0.0814
  -1.750   0.1537   0.00601   0.00105  -0.0767   0.8436   0.2183
  -1.500   0.1786   0.00504   0.00095  -0.0768   0.8354   0.5115
  -1.250   0.2056   0.00487   0.00092  -0.0766   0.8254   0.5804
  -1.000   0.2328   0.00480   0.00088  -0.0764   0.8141   0.6201
  -0.750   0.2601   0.00476   0.00085  -0.0762   0.8031   0.6498
  -0.500   0.2873   0.00472   0.00084  -0.0760   0.7925   0.6801
  -0.250   0.3143   0.00468   0.00085  -0.0757   0.7819   0.7166
   0.000   0.3411   0.00465   0.00087  -0.0754   0.7705   0.7523
   0.250   0.3681   0.00464   0.00088  -0.0751   0.7581   0.7723
   0.500   0.3953   0.00466   0.00089  -0.0749   0.7456   0.7872
   0.750   0.4226   0.00468   0.00089  -0.0748   0.7329   0.8000
   1.000   0.4496   0.00470   0.00091  -0.0746   0.7192   0.8139
   1.250   0.4765   0.00472   0.00093  -0.0743   0.7043   0.8297
   1.500   0.5027   0.00475   0.00096  -0.0739   0.6867   0.8487
   1.750   0.5281   0.00475   0.00100  -0.0733   0.6668   0.8765
   2.000   0.5561   0.00466   0.00102  -0.0732   0.6465   0.9616
   2.250   0.5874   0.00477   0.00106  -0.0740   0.6226   1.0000
   2.500   0.6139   0.00495   0.00113  -0.0738   0.5933   1.0000
   2.750   0.6403   0.00516   0.00124  -0.0736   0.5607   1.0000
   3.000   0.6654   0.00548   0.00136  -0.0732   0.5113   1.0000
   3.250   0.6903   0.00586   0.00152  -0.0727   0.4576   1.0000
   3.500   0.7152   0.00625   0.00170  -0.0723   0.4055   1.0000
   4.000   0.7625   0.00735   0.00219  -0.0713   0.2689   1.0000
   4.250   0.7878   0.00771   0.00243  -0.0710   0.2331   1.0000
   4.500   0.8121   0.00819   0.00268  -0.0706   0.1862   1.0000
   4.750   0.8348   0.00887   0.00303  -0.0699   0.1226   1.0000
   5.000   0.8557   0.00983   0.00355  -0.0690   0.0450   1.0000
   5.250   0.8778   0.01066   0.00416  -0.0682   0.0064   1.0000
   5.500   0.9034   0.01101   0.00457  -0.0677   0.0050   1.0000
   5.750   0.9280   0.01151   0.00522  -0.0671   0.0040   1.0000
   6.000   0.9523   0.01204   0.00583  -0.0664   0.0036   1.0000
   6.250   0.9757   0.01272   0.00662  -0.0656   0.0034   1.0000
   6.500   0.9978   0.01358   0.00762  -0.0645   0.0034   1.0000
   6.750   1.0185   0.01462   0.00879  -0.0632   0.0034   1.0000
   7.000   1.0372   0.01598   0.01031  -0.0615   0.0035   1.0000
   7.250   1.0543   0.01776   0.01225  -0.0596   0.0038   1.0000
   7.500   1.0741   0.01930   0.01388  -0.0582   0.0046   1.0000
  15.000   0.9395   0.18834   0.18685  -0.0948   0.0057   1.0000
  15.250   0.9441   0.19318   0.19169  -0.0974   0.0055   1.0000
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