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HQ 2.5/12 AIRFOIL (hq2512-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/12 AIRFOIL (hq2512-il)
Reynolds number: 200,000
Max Cl/Cd: 76.86 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2512-il-200000.txt
Download as CSV file: xf-hq2512-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4021   0.10758   0.10400  -0.0419   1.0000   0.0522
 -10.500  -0.4099   0.10282   0.09929  -0.0460   1.0000   0.0526
 -10.250  -0.4145   0.09807   0.09459  -0.0492   1.0000   0.0528
 -10.000  -0.4230   0.09233   0.08891  -0.0532   1.0000   0.0529
  -9.750  -0.4188   0.08831   0.08494  -0.0495   1.0000   0.0542
  -9.500  -0.4130   0.08590   0.08255  -0.0482   1.0000   0.0552
  -9.250  -0.4125   0.08291   0.07960  -0.0482   1.0000   0.0561
  -9.000  -0.4167   0.07944   0.07619  -0.0489   1.0000   0.0572
  -8.750  -0.4298   0.07507   0.07191  -0.0506   1.0000   0.0573
  -8.500  -0.4593   0.07071   0.06767  -0.0517   1.0000   0.0573
  -8.250  -0.5120   0.06900   0.06604  -0.0476   1.0000   0.0563
  -8.000  -0.5387   0.06662   0.06365  -0.0454   0.9995   0.0563
  -7.750  -0.5225   0.06047   0.05733  -0.0529   0.9929   0.0580
  -7.500  -0.5408   0.03698   0.03199  -0.0623   0.9800   0.0304
  -7.250  -0.5180   0.03235   0.02675  -0.0639   0.9738   0.0306
  -7.000  -0.4862   0.02904   0.02281  -0.0662   0.9701   0.0316
  -6.750  -0.4616   0.02623   0.01984  -0.0672   0.9642   0.0342
  -6.500  -0.4284   0.02477   0.01817  -0.0688   0.9596   0.0374
  -6.250  -0.3913   0.02298   0.01597  -0.0706   0.9567   0.0406
  -6.000  -0.3609   0.02112   0.01401  -0.0718   0.9521   0.0459
  -5.750  -0.3279   0.02060   0.01327  -0.0728   0.9466   0.0526
  -5.500  -0.2918   0.01908   0.01175  -0.0749   0.9437   0.0617
  -5.250  -0.2526   0.01800   0.01063  -0.0774   0.9415   0.0709
  -5.000  -0.2246   0.01764   0.01015  -0.0775   0.9345   0.0787
  -4.750  -0.1915   0.01661   0.00919  -0.0789   0.9303   0.0877
  -4.500  -0.1554   0.01577   0.00836  -0.0806   0.9273   0.0981
  -4.250  -0.1302   0.01521   0.00782  -0.0803   0.9200   0.1099
  -4.000  -0.0989   0.01445   0.00715  -0.0812   0.9152   0.1340
  -3.750  -0.0700   0.01322   0.00651  -0.0821   0.9110   0.2442
  -3.500  -0.0534   0.01213   0.00640  -0.0806   0.9025   0.4731
  -3.250  -0.0231   0.01191   0.00641  -0.0806   0.8984   0.5678
  -3.000   0.0008   0.01199   0.00652  -0.0795   0.8908   0.6111
  -2.750   0.0301   0.01203   0.00651  -0.0793   0.8856   0.6447
  -2.500   0.0570   0.01211   0.00658  -0.0786   0.8797   0.6698
  -2.250   0.0832   0.01218   0.00661  -0.0778   0.8728   0.6903
  -2.000   0.1128   0.01218   0.00656  -0.0775   0.8685   0.7091
  -1.750   0.1349   0.01233   0.00674  -0.0759   0.8600   0.7288
  -1.500   0.1623   0.01236   0.00673  -0.0751   0.8549   0.7488
  -1.250   0.1861   0.01241   0.00677  -0.0739   0.8470   0.7620
  -1.000   0.2132   0.01236   0.00669  -0.0733   0.8413   0.7746
  -0.750   0.2377   0.01237   0.00670  -0.0723   0.8342   0.7876
  -0.500   0.2636   0.01233   0.00663  -0.0715   0.8278   0.8002
  -0.250   0.2902   0.01229   0.00656  -0.0710   0.8216   0.8112
   0.000   0.3159   0.01222   0.00648  -0.0703   0.8140   0.8201
   0.250   0.3425   0.01210   0.00633  -0.0697   0.8064   0.8290
   0.500   0.3694   0.01194   0.00613  -0.0692   0.7975   0.8389
   0.750   0.3940   0.01179   0.00598  -0.0682   0.7873   0.8483
   1.000   0.4211   0.01161   0.00577  -0.0675   0.7794   0.8581
   1.250   0.4460   0.01152   0.00569  -0.0667   0.7700   0.8693
   1.500   0.4715   0.01143   0.00561  -0.0660   0.7617   0.8812
   1.750   0.4974   0.01129   0.00548  -0.0652   0.7535   0.8935
   2.000   0.5222   0.01121   0.00545  -0.0644   0.7439   0.9075
   2.250   0.5514   0.01109   0.00533  -0.0643   0.7353   0.9225
   2.500   0.5831   0.01099   0.00525  -0.0648   0.7248   0.9403
   2.750   0.6212   0.01092   0.00522  -0.0669   0.7131   0.9587
   3.000   0.6635   0.01084   0.00516  -0.0699   0.7008   0.9792
   3.250   0.7008   0.01080   0.00510  -0.0721   0.6877   1.0000
   3.500   0.7245   0.01084   0.00510  -0.0716   0.6744   1.0000
   3.750   0.7501   0.01088   0.00511  -0.0713   0.6595   1.0000
   4.000   0.7759   0.01094   0.00513  -0.0709   0.6429   1.0000
   4.250   0.8015   0.01101   0.00515  -0.0704   0.6245   1.0000
   4.500   0.8266   0.01111   0.00522  -0.0698   0.6038   1.0000
   4.750   0.8510   0.01123   0.00529  -0.0691   0.5800   1.0000
   5.000   0.8745   0.01141   0.00540  -0.0682   0.5524   1.0000
   5.250   0.8970   0.01167   0.00556  -0.0672   0.5205   1.0000
   5.500   0.9181   0.01202   0.00577  -0.0660   0.4827   1.0000
   5.750   0.9378   0.01250   0.00605  -0.0645   0.4430   1.0000
   6.000   0.9563   0.01309   0.00642  -0.0630   0.4044   1.0000
   6.250   0.9753   0.01367   0.00684  -0.0616   0.3696   1.0000
   6.500   0.9943   0.01427   0.00732  -0.0603   0.3408   1.0000
   6.750   1.0132   0.01490   0.00781  -0.0589   0.3172   1.0000
   7.000   1.0328   0.01549   0.00833  -0.0577   0.2956   1.0000
   7.250   1.0518   0.01612   0.00888  -0.0565   0.2772   1.0000
   7.500   1.0707   0.01677   0.00946  -0.0552   0.2609   1.0000
   7.750   1.0894   0.01741   0.01008  -0.0539   0.2449   1.0000
   8.000   1.1080   0.01800   0.01067  -0.0526   0.2291   1.0000
   8.250   1.1259   0.01860   0.01127  -0.0512   0.2137   1.0000
   8.500   1.1430   0.01922   0.01190  -0.0497   0.1992   1.0000
   8.750   1.1590   0.01985   0.01253  -0.0481   0.1845   1.0000
   9.000   1.1728   0.02048   0.01318  -0.0461   0.1705   1.0000
   9.250   1.1855   0.02114   0.01383  -0.0440   0.1567   1.0000
   9.500   1.1977   0.02186   0.01455  -0.0419   0.1439   1.0000
   9.750   1.2092   0.02267   0.01534  -0.0399   0.1324   1.0000
  10.000   1.2210   0.02344   0.01610  -0.0380   0.1195   1.0000
  10.250   1.2328   0.02426   0.01693  -0.0363   0.1068   1.0000
  10.500   1.2462   0.02506   0.01779  -0.0348   0.0957   1.0000
  10.750   1.2584   0.02596   0.01873  -0.0333   0.0838   1.0000
  11.000   1.2687   0.02705   0.01984  -0.0317   0.0702   1.0000
  11.250   1.2719   0.02880   0.02145  -0.0296   0.0449   1.0000
  11.500   1.2650   0.03145   0.02395  -0.0267   0.0289   1.0000
  11.750   1.2643   0.03365   0.02625  -0.0246   0.0246   1.0000
  12.000   1.2641   0.03585   0.02855  -0.0229   0.0224   1.0000
  12.250   1.2598   0.03850   0.03129  -0.0213   0.0211   1.0000
  12.500   1.2558   0.04128   0.03421  -0.0199   0.0201   1.0000
  12.750   1.2553   0.04385   0.03692  -0.0189   0.0194   1.0000
  13.000   1.2541   0.04659   0.03980  -0.0181   0.0187   1.0000
  13.250   1.2529   0.04944   0.04278  -0.0176   0.0180   1.0000
  13.500   1.2517   0.05236   0.04580  -0.0174   0.0170   1.0000
  13.750   1.2491   0.05556   0.04912  -0.0173   0.0166   1.0000
  14.000   1.2450   0.05906   0.05271  -0.0175   0.0161   1.0000
  14.250   1.2388   0.06296   0.05670  -0.0178   0.0155   1.0000
  14.500   1.2345   0.06680   0.06068  -0.0179   0.0152   1.0000
  14.750   1.2320   0.07057   0.06460  -0.0184   0.0149   1.0000
  15.000   1.2298   0.07439   0.06859  -0.0191   0.0148   1.0000
  15.250   1.2256   0.07868   0.07307  -0.0203   0.0146   1.0000
  15.500   1.2212   0.08311   0.07767  -0.0215   0.0145   1.0000
  15.750   1.2145   0.08805   0.08280  -0.0233   0.0144   1.0000
  16.000   1.2077   0.09315   0.08808  -0.0253   0.0144   1.0000
  16.250   1.1982   0.09894   0.09407  -0.0279   0.0143   1.0000
  16.500   1.1879   0.10502   0.10034  -0.0308   0.0144   1.0000
  16.750   1.1746   0.11197   0.10750  -0.0346   0.0143   1.0000
  17.000   1.1613   0.11915   0.11487  -0.0386   0.0143   1.0000
  17.250   1.1477   0.12664   0.12253  -0.0431   0.0145   1.0000
  17.500   1.1330   0.13461   0.13068  -0.0480   0.0146   1.0000
  17.750   1.1156   0.14362   0.13987  -0.0538   0.0146   1.0000
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