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HQ 2.5/10 AIRFOIL (hq2510-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/10 AIRFOIL (hq2510-il)
Reynolds number: 100,000
Max Cl/Cd: 57.5 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2510-il-100000.txt
Download as CSV file: xf-hq2510-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4037   0.10205   0.09721  -0.0347   1.0000   0.0869
  -9.000  -0.4221   0.09948   0.09478  -0.0400   1.0000   0.0880
  -8.750  -0.4404   0.09651   0.09195  -0.0439   1.0000   0.0883
  -8.500  -0.3984   0.09140   0.08673  -0.0358   1.0000   0.0932
  -8.250  -0.3988   0.08849   0.08389  -0.0362   1.0000   0.0964
  -8.000  -0.4112   0.08560   0.08112  -0.0378   1.0000   0.0996
  -7.750  -0.4385   0.08274   0.07844  -0.0410   1.0000   0.1011
  -7.500  -0.4665   0.07970   0.07540  -0.0454   1.0000   0.1018
  -7.250  -0.4548   0.07565   0.07151  -0.0408   1.0000   0.1043
  -7.000  -0.4520   0.07359   0.06950  -0.0374   1.0000   0.1075
  -6.750  -0.4622   0.07092   0.06686  -0.0369   1.0000   0.1107
  -6.250  -0.4831   0.06430   0.06017  -0.0376   1.0000   0.1190
  -6.000  -0.4821   0.06200   0.05783  -0.0364   1.0000   0.1269
  -5.750  -0.4816   0.05878   0.05459  -0.0358   1.0000   0.1341
  -5.500  -0.4786   0.05592   0.05164  -0.0356   1.0000   0.1472
  -5.250  -0.4724   0.05324   0.04891  -0.0350   1.0000   0.1613
  -5.000  -0.4637   0.05052   0.04610  -0.0344   1.0000   0.1760
  -4.750  -0.4209   0.03858   0.03262  -0.0410   1.0000   0.0828
  -4.500  -0.3896   0.03279   0.02555  -0.0407   1.0000   0.0602
  -4.250  -0.3658   0.02966   0.02196  -0.0404   1.0000   0.0591
  -4.000  -0.3410   0.02734   0.01914  -0.0398   1.0000   0.0597
  -3.750  -0.3182   0.02540   0.01698  -0.0395   1.0000   0.0659
  -3.500  -0.2946   0.02401   0.01532  -0.0387   1.0000   0.0715
  -3.250  -0.2708   0.02237   0.01355  -0.0380   1.0000   0.0794
  -3.000  -0.2373   0.02127   0.01238  -0.0392   0.9967   0.0998
  -2.750  -0.2007   0.02021   0.01146  -0.0413   0.9919   0.1260
  -2.500  -0.1649   0.01931   0.01071  -0.0432   0.9864   0.1598
  -2.250  -0.1350   0.01693   0.01056  -0.0442   0.9827   0.5754
  -2.000  -0.1138   0.01718   0.01111  -0.0415   0.9748   0.7326
  -1.750  -0.0856   0.01755   0.01147  -0.0405   0.9681   0.7985
  -1.500  -0.0644   0.01759   0.01150  -0.0383   0.9596   0.8477
  -1.250  -0.0356   0.01763   0.01152  -0.0376   0.9529   0.9025
  -1.000   0.0352   0.01768   0.01145  -0.0456   0.9485   1.0000
  -0.750   0.0795   0.01789   0.01141  -0.0501   0.9416   1.0000
  -0.500   0.1111   0.01803   0.01138  -0.0522   0.9317   1.0000
  -0.250   0.1509   0.01827   0.01144  -0.0554   0.9240   1.0000
   0.000   0.1909   0.01847   0.01149  -0.0585   0.9159   1.0000
   0.250   0.2249   0.01870   0.01160  -0.0604   0.9067   1.0000
   0.500   0.2719   0.01885   0.01165  -0.0644   0.9004   1.0000
   0.750   0.3023   0.01908   0.01180  -0.0654   0.8900   1.0000
   1.000   0.3407   0.01921   0.01187  -0.0676   0.8813   1.0000
   1.250   0.3941   0.01897   0.01159  -0.0720   0.8730   1.0000
   1.500   0.4330   0.01880   0.01141  -0.0736   0.8611   1.0000
   1.750   0.4692   0.01869   0.01129  -0.0748   0.8499   1.0000
   2.000   0.5088   0.01849   0.01110  -0.0765   0.8411   1.0000
   2.250   0.5469   0.01823   0.01086  -0.0776   0.8315   1.0000
   2.500   0.5775   0.01812   0.01080  -0.0776   0.8193   1.0000
   2.750   0.6087   0.01792   0.01064  -0.0775   0.8068   1.0000
   3.000   0.6400   0.01766   0.01042  -0.0772   0.7939   1.0000
   3.250   0.6708   0.01736   0.01016  -0.0768   0.7802   1.0000
   3.500   0.7009   0.01704   0.00992  -0.0761   0.7656   1.0000
   3.750   0.7308   0.01670   0.00962  -0.0754   0.7500   1.0000
   4.000   0.7609   0.01633   0.00928  -0.0746   0.7334   1.0000
   4.250   0.7855   0.01617   0.00918  -0.0732   0.7113   1.0000
   4.500   0.8128   0.01589   0.00897  -0.0720   0.6887   1.0000
   4.750   0.8387   0.01570   0.00879  -0.0706   0.6623   1.0000
   5.000   0.8625   0.01563   0.00874  -0.0691   0.6300   1.0000
   5.250   0.8863   0.01562   0.00868  -0.0675   0.5928   1.0000
   5.500   0.9080   0.01579   0.00879  -0.0657   0.5470   1.0000
   5.750   0.9286   0.01618   0.00896  -0.0638   0.4971   1.0000
   6.000   0.9476   0.01683   0.00936  -0.0620   0.4462   1.0000
   6.250   0.9663   0.01765   0.00991  -0.0603   0.4012   1.0000
   6.500   0.9850   0.01853   0.01061  -0.0587   0.3610   1.0000
   6.750   1.0040   0.01946   0.01138  -0.0573   0.3260   1.0000
   7.000   1.0234   0.02047   0.01232  -0.0560   0.2955   1.0000
   7.250   1.0430   0.02153   0.01329  -0.0548   0.2679   1.0000
   7.500   1.0625   0.02261   0.01430  -0.0536   0.2429   1.0000
   7.750   1.0818   0.02368   0.01528  -0.0524   0.2204   1.0000
   8.000   1.0977   0.02447   0.01618  -0.0507   0.1967   1.0000
   8.250   1.1090   0.02500   0.01675  -0.0486   0.1708   1.0000
   8.500   1.1188   0.02547   0.01726  -0.0465   0.1414   1.0000
   8.750   1.1285   0.02652   0.01828  -0.0443   0.1026   1.0000
   9.000   1.1253   0.02934   0.02063  -0.0404   0.0535   1.0000
   9.250   1.1288   0.03143   0.02279  -0.0371   0.0440   1.0000
   9.500   1.1322   0.03365   0.02498  -0.0343   0.0395   1.0000
   9.750   1.1444   0.03588   0.02737  -0.0322   0.0365   1.0000
  10.000   1.1600   0.03825   0.02992  -0.0306   0.0341   1.0000
  10.250   1.1769   0.04083   0.03268  -0.0294   0.0324   1.0000
  10.500   1.1928   0.04376   0.03583  -0.0283   0.0313   1.0000
  10.750   1.2056   0.04709   0.03941  -0.0270   0.0306   1.0000
  11.000   1.2120   0.05059   0.04322  -0.0251   0.0303   1.0000
  11.250   1.2117   0.05419   0.04712  -0.0231   0.0299   1.0000
  11.500   1.2060   0.05766   0.05090  -0.0208   0.0298   1.0000
  11.750   1.1946   0.06196   0.05546  -0.0190   0.0293   1.0000
  12.000   1.1814   0.06579   0.05957  -0.0176   0.0293   1.0000
  12.250   1.1659   0.06991   0.06396  -0.0168   0.0293   1.0000
  12.500   1.1499   0.07387   0.06821  -0.0167   0.0296   1.0000
  12.750   1.1296   0.07877   0.07340  -0.0176   0.0300   1.0000
  13.000   1.1057   0.08483   0.07974  -0.0200   0.0303   1.0000
  13.250   1.0518   0.09694   0.09233  -0.0277   0.0328   1.0000
  13.500   1.0155   0.10849   0.10407  -0.0359   0.0339   1.0000
  13.750   0.9815   0.12191   0.11759  -0.0454   0.0352   1.0000
  14.000   0.9563   0.13486   0.13054  -0.0533   0.0367   1.0000
  14.250   0.9428   0.14488   0.14052  -0.0586   0.0377   1.0000
  14.500   0.9374   0.15226   0.14786  -0.0619   0.0385   1.0000
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