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HQ 2.5/10 AIRFOIL (hq2510-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/10 AIRFOIL (hq2510-il)
Reynolds number: 500,000
Max Cl/Cd: 85.26 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2510-il-500000-n5.txt
Download as CSV file: xf-hq2510-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/10 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4453   0.08171   0.07951  -0.0380   1.0000   0.0041
  -9.250  -0.4553   0.07615   0.07400  -0.0406   1.0000   0.0041
  -9.000  -0.4686   0.07042   0.06834  -0.0435   1.0000   0.0040
  -8.750  -0.4819   0.06574   0.06371  -0.0459   1.0000   0.0039
  -8.500  -0.4937   0.05523   0.05315  -0.0597   0.9890   0.0038
  -8.250  -0.5276   0.02578   0.02212  -0.0767   0.9662   0.0038
  -8.000  -0.5036   0.02236   0.01818  -0.0783   0.9595   0.0040
  -7.750  -0.4793   0.02039   0.01586  -0.0787   0.9513   0.0042
  -7.500  -0.4547   0.01810   0.01318  -0.0792   0.9440   0.0044
  -7.250  -0.4305   0.01665   0.01146  -0.0792   0.9351   0.0047
  -7.000  -0.4045   0.01579   0.01045  -0.0793   0.9274   0.0050
  -6.750  -0.3778   0.01533   0.00991  -0.0793   0.9196   0.0055
  -6.500  -0.3519   0.01471   0.00917  -0.0792   0.9119   0.0061
  -6.250  -0.3263   0.01395   0.00824  -0.0789   0.9045   0.0067
  -6.000  -0.3010   0.01325   0.00740  -0.0785   0.8967   0.0071
  -5.750  -0.2756   0.01252   0.00651  -0.0781   0.8896   0.0075
  -5.500  -0.2508   0.01167   0.00552  -0.0777   0.8817   0.0084
  -5.250  -0.2247   0.01121   0.00494  -0.0774   0.8749   0.0094
  -5.000  -0.1983   0.01083   0.00448  -0.0772   0.8677   0.0106
  -4.750  -0.1715   0.01055   0.00411  -0.0770   0.8613   0.0120
  -4.500  -0.1450   0.01010   0.00361  -0.0768   0.8542   0.0157
  -4.250  -0.1181   0.00980   0.00330  -0.0766   0.8479   0.0227
  -4.000  -0.0908   0.00962   0.00308  -0.0765   0.8409   0.0296
  -3.500  -0.0363   0.00923   0.00263  -0.0763   0.8276   0.0447
  -3.250  -0.0089   0.00907   0.00244  -0.0762   0.8212   0.0537
  -3.000   0.0184   0.00886   0.00226  -0.0762   0.8140   0.0688
  -2.500   0.0729   0.00843   0.00191  -0.0761   0.7991   0.1195
  -2.250   0.0997   0.00812   0.00175  -0.0760   0.7912   0.1795
  -2.000   0.1264   0.00778   0.00161  -0.0760   0.7824   0.2555
  -1.750   0.1526   0.00732   0.00147  -0.0760   0.7741   0.3676
  -1.500   0.1791   0.00701   0.00139  -0.0759   0.7663   0.4638
  -1.250   0.2060   0.00682   0.00138  -0.0758   0.7583   0.5305
  -1.000   0.2329   0.00672   0.00137  -0.0755   0.7495   0.5826
  -0.750   0.2594   0.00665   0.00141  -0.0751   0.7389   0.6367
  -0.500   0.2863   0.00663   0.00142  -0.0748   0.7270   0.6672
  -0.250   0.3134   0.00665   0.00141  -0.0746   0.7145   0.6829
   0.000   0.3407   0.00667   0.00141  -0.0744   0.7023   0.6970
   0.250   0.3681   0.00670   0.00142  -0.0742   0.6914   0.7080
   0.500   0.3955   0.00674   0.00143  -0.0741   0.6809   0.7162
   0.750   0.4228   0.00679   0.00144  -0.0739   0.6688   0.7243
   1.250   0.4770   0.00691   0.00150  -0.0735   0.6400   0.7411
   1.750   0.5308   0.00705   0.00159  -0.0731   0.6070   0.7593
   2.000   0.5573   0.00715   0.00165  -0.0728   0.5881   0.7687
   2.250   0.5833   0.00728   0.00174  -0.0724   0.5633   0.7790
   2.500   0.6084   0.00747   0.00183  -0.0719   0.5320   0.7898
   2.750   0.6332   0.00768   0.00194  -0.0713   0.4976   0.8012
   3.000   0.6576   0.00792   0.00209  -0.0707   0.4626   0.8136
   3.250   0.6818   0.00817   0.00226  -0.0701   0.4285   0.8279
   3.500   0.7059   0.00840   0.00243  -0.0694   0.3986   0.8448
   3.750   0.7290   0.00864   0.00262  -0.0685   0.3659   0.8673
   4.000   0.7518   0.00883   0.00281  -0.0675   0.3321   0.9121
   4.250   0.7852   0.00921   0.00307  -0.0691   0.2941   1.0000
   4.500   0.8097   0.00958   0.00332  -0.0686   0.2672   1.0000
   4.750   0.8351   0.00986   0.00355  -0.0683   0.2503   1.0000
   5.000   0.8600   0.01019   0.00380  -0.0680   0.2290   1.0000
   5.250   0.8831   0.01068   0.00411  -0.0674   0.1910   1.0000
   5.500   0.9054   0.01126   0.00445  -0.0667   0.1514   1.0000
   5.750   0.9282   0.01177   0.00483  -0.0661   0.1213   1.0000
   6.000   0.9510   0.01229   0.00521  -0.0654   0.0958   1.0000
   6.250   0.9737   0.01280   0.00562  -0.0647   0.0739   1.0000
   6.500   0.9937   0.01359   0.00619  -0.0637   0.0402   1.0000
   6.750   1.0114   0.01464   0.00702  -0.0623   0.0072   1.0000
   7.000   1.0340   0.01515   0.00757  -0.0615   0.0050   1.0000
   7.250   1.0563   0.01565   0.00816  -0.0607   0.0042   1.0000
   7.500   1.0782   0.01620   0.00877  -0.0598   0.0037   1.0000
   7.750   1.0993   0.01682   0.00949  -0.0588   0.0033   1.0000
   8.000   1.1194   0.01752   0.01030  -0.0577   0.0031   1.0000
   8.250   1.1388   0.01827   0.01115  -0.0565   0.0029   1.0000
   8.500   1.1576   0.01901   0.01199  -0.0552   0.0028   1.0000
   8.750   1.1754   0.01982   0.01289  -0.0538   0.0026   1.0000
   9.000   1.1918   0.02069   0.01387  -0.0522   0.0026   1.0000
   9.250   1.2063   0.02166   0.01494  -0.0504   0.0025   1.0000
   9.500   1.2179   0.02268   0.01611  -0.0481   0.0024   1.0000
   9.750   1.2270   0.02374   0.01728  -0.0454   0.0024   1.0000
  10.000   1.2352   0.02486   0.01851  -0.0428   0.0024   1.0000
  10.250   1.2410   0.02620   0.01997  -0.0400   0.0023   1.0000
  10.500   1.2470   0.02757   0.02147  -0.0375   0.0023   1.0000
  10.750   1.2524   0.02905   0.02306  -0.0352   0.0023   1.0000
  11.000   1.2557   0.03078   0.02494  -0.0328   0.0022   1.0000
  11.250   1.2590   0.03258   0.02688  -0.0308   0.0022   1.0000
  11.500   1.2613   0.03456   0.02901  -0.0289   0.0022   1.0000
  11.750   1.2618   0.03681   0.03142  -0.0271   0.0022   1.0000
  12.000   1.2627   0.03909   0.03385  -0.0257   0.0022   1.0000
  12.250   1.2612   0.04173   0.03666  -0.0245   0.0022   1.0000
  12.500   1.2581   0.04468   0.03978  -0.0235   0.0022   1.0000
  12.750   1.2536   0.04792   0.04320  -0.0229   0.0022   1.0000
  13.000   1.2475   0.05153   0.04698  -0.0227   0.0022   1.0000
  13.250   1.2419   0.05521   0.05084  -0.0230   0.0022   1.0000
  13.500   1.2321   0.05971   0.05552  -0.0238   0.0022   1.0000
  13.750   1.2216   0.06459   0.06062  -0.0251   0.0022   1.0000
  14.000   1.2101   0.06996   0.06617  -0.0271   0.0022   1.0000
  14.250   1.1982   0.07575   0.07214  -0.0296   0.0022   1.0000
  14.500   1.1832   0.08260   0.07917  -0.0330   0.0022   1.0000
  14.750   1.1700   0.08956   0.08629  -0.0368   0.0022   1.0000
  15.000   1.1565   0.09695   0.09384  -0.0410   0.0023   1.0000
  15.250   1.1410   0.10519   0.10224  -0.0458   0.0023   1.0000
  15.500   1.1250   0.11391   0.11111  -0.0510   0.0023   1.0000
  15.750   1.1100   0.12268   0.12001  -0.0562   0.0023   1.0000
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