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HQ 3.0/12 AIRFOIL (hq3012-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/12 AIRFOIL (hq3012-il)
Reynolds number: 200,000
Max Cl/Cd: 80.78 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3012-il-200000.txt
Download as CSV file: xf-hq3012-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/12 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3833   0.08928   0.08601  -0.0508   1.0000   0.0534
  -9.000  -0.4061   0.08589   0.08273  -0.0514   1.0000   0.0536
  -8.750  -0.4287   0.08379   0.08071  -0.0491   1.0000   0.0536
  -8.500  -0.4612   0.08230   0.07931  -0.0459   1.0000   0.0536
  -8.250  -0.3248   0.06998   0.06714  -0.0475   0.9907   0.0612
  -8.000  -0.4616   0.06962   0.06615  -0.0654   0.9846   0.0540
  -7.750  -0.4482   0.06155   0.05824  -0.0684   0.9823   0.0557
  -7.500  -0.4276   0.05913   0.05586  -0.0694   0.9766   0.0576
  -7.250  -0.4057   0.05475   0.05133  -0.0745   0.9713   0.0605
  -6.500  -0.3603   0.02831   0.02199  -0.0830   0.9487   0.0333
  -6.250  -0.3304   0.02470   0.01802  -0.0846   0.9450   0.0345
  -6.000  -0.2934   0.02312   0.01629  -0.0869   0.9426   0.0370
  -5.750  -0.2584   0.02223   0.01514  -0.0883   0.9390   0.0417
  -5.500  -0.2317   0.02040   0.01319  -0.0884   0.9329   0.0457
  -5.250  -0.1942   0.01961   0.01224  -0.0902   0.9299   0.0536
  -5.000  -0.1575   0.01845   0.01107  -0.0923   0.9275   0.0646
  -4.750  -0.1321   0.01766   0.01028  -0.0920   0.9210   0.0730
  -4.500  -0.1001   0.01702   0.00958  -0.0930   0.9164   0.0829
  -4.250  -0.0651   0.01634   0.00890  -0.0944   0.9134   0.0926
  -4.000  -0.0398   0.01568   0.00828  -0.0941   0.9070   0.1015
  -3.750  -0.0111   0.01506   0.00770  -0.0943   0.9016   0.1161
  -3.500   0.0210   0.01427   0.00704  -0.0953   0.8981   0.1481
  -3.250   0.0390   0.01296   0.00664  -0.0945   0.8903   0.3375
  -3.000   0.0634   0.01235   0.00678  -0.0936   0.8853   0.5595
  -2.750   0.0934   0.01234   0.00678  -0.0935   0.8812   0.6123
  -2.500   0.1166   0.01248   0.00690  -0.0922   0.8734   0.6440
  -2.250   0.1465   0.01248   0.00689  -0.0920   0.8691   0.6696
  -2.000   0.1711   0.01259   0.00695  -0.0910   0.8622   0.6900
  -1.750   0.1986   0.01260   0.00693  -0.0904   0.8564   0.7072
  -1.500   0.2260   0.01262   0.00696  -0.0895   0.8514   0.7282
  -1.250   0.2481   0.01276   0.00710  -0.0878   0.8435   0.7504
  -1.000   0.2763   0.01269   0.00700  -0.0872   0.8389   0.7660
  -0.750   0.2999   0.01275   0.00705  -0.0862   0.8311   0.7788
  -0.500   0.3270   0.01266   0.00694  -0.0856   0.8256   0.7909
  -0.250   0.3522   0.01262   0.00690  -0.0848   0.8191   0.8011
   0.000   0.3795   0.01255   0.00679  -0.0846   0.8125   0.8100
   0.250   0.4073   0.01243   0.00663  -0.0842   0.8063   0.8186
   0.500   0.4333   0.01228   0.00647  -0.0836   0.7973   0.8276
   0.750   0.4600   0.01215   0.00630  -0.0830   0.7886   0.8378
   1.000   0.4870   0.01196   0.00611  -0.0825   0.7811   0.8473
   1.250   0.5118   0.01189   0.00607  -0.0817   0.7727   0.8582
   1.500   0.5392   0.01174   0.00590  -0.0813   0.7658   0.8698
   1.750   0.5632   0.01167   0.00587  -0.0803   0.7566   0.8833
   2.000   0.5913   0.01149   0.00568  -0.0799   0.7495   0.8979
   2.250   0.6162   0.01138   0.00564  -0.0791   0.7389   0.9157
   2.500   0.6481   0.01124   0.00553  -0.0796   0.7282   0.9385
   2.750   0.6895   0.01109   0.00539  -0.0822   0.7170   0.9670
   3.000   0.7285   0.01101   0.00526  -0.0847   0.7058   1.0000
   3.250   0.7550   0.01106   0.00528  -0.0847   0.6932   1.0000
   3.500   0.7822   0.01110   0.00531  -0.0847   0.6800   1.0000
   3.750   0.8092   0.01116   0.00533  -0.0846   0.6662   1.0000
   4.000   0.8357   0.01122   0.00535  -0.0843   0.6511   1.0000
   4.250   0.8619   0.01129   0.00540  -0.0839   0.6349   1.0000
   4.500   0.8873   0.01138   0.00545  -0.0834   0.6166   1.0000
   4.750   0.9117   0.01150   0.00555  -0.0827   0.5951   1.0000
   5.000   0.9358   0.01166   0.00565  -0.0819   0.5724   1.0000
   5.250   0.9588   0.01187   0.00578  -0.0809   0.5458   1.0000
   5.500   0.9808   0.01216   0.00596  -0.0798   0.5158   1.0000
   5.750   1.0016   0.01253   0.00621  -0.0785   0.4831   1.0000
   6.000   1.0213   0.01299   0.00653  -0.0770   0.4494   1.0000
   6.250   1.0399   0.01353   0.00691  -0.0755   0.4165   1.0000
   6.500   1.0582   0.01411   0.00734  -0.0739   0.3857   1.0000
   6.750   1.0761   0.01471   0.00782  -0.0724   0.3568   1.0000
   7.000   1.0937   0.01533   0.00833  -0.0708   0.3301   1.0000
   7.250   1.1108   0.01598   0.00887  -0.0692   0.3067   1.0000
   7.500   1.1277   0.01663   0.00943  -0.0676   0.2850   1.0000
   7.750   1.1438   0.01733   0.01003  -0.0659   0.2665   1.0000
   8.000   1.1609   0.01794   0.01062  -0.0643   0.2487   1.0000
   8.250   1.1773   0.01856   0.01124  -0.0627   0.2325   1.0000
   8.500   1.1922   0.01919   0.01185  -0.0608   0.2178   1.0000
   8.750   1.2059   0.01984   0.01249  -0.0587   0.2042   1.0000
   9.000   1.2190   0.02054   0.01318  -0.0566   0.1914   1.0000
   9.250   1.2312   0.02131   0.01392  -0.0545   0.1789   1.0000
   9.500   1.2430   0.02211   0.01471  -0.0524   0.1666   1.0000
   9.750   1.2550   0.02290   0.01555  -0.0504   0.1539   1.0000
  10.000   1.2660   0.02377   0.01644  -0.0485   0.1407   1.0000
  10.250   1.2764   0.02470   0.01739  -0.0466   0.1277   1.0000
  10.500   1.2861   0.02574   0.01843  -0.0447   0.1149   1.0000
  10.750   1.2951   0.02686   0.01956  -0.0428   0.1029   1.0000
  11.000   1.3031   0.02813   0.02085  -0.0410   0.0930   1.0000
  11.250   1.3093   0.02956   0.02225  -0.0392   0.0842   1.0000
  11.500   1.3178   0.03087   0.02360  -0.0377   0.0761   1.0000
  11.750   1.3241   0.03243   0.02525  -0.0361   0.0704   1.0000
  12.000   1.3309   0.03396   0.02683  -0.0347   0.0648   1.0000
  12.250   1.3347   0.03582   0.02874  -0.0332   0.0605   1.0000
  12.500   1.3429   0.03734   0.03039  -0.0322   0.0556   1.0000
  12.750   1.3436   0.03956   0.03261  -0.0309   0.0516   1.0000
  13.000   1.3502   0.04134   0.03456  -0.0300   0.0472   1.0000
  13.250   1.3517   0.04362   0.03690  -0.0292   0.0425   1.0000
  13.500   1.3516   0.04620   0.03961  -0.0284   0.0377   1.0000
  13.750   1.3461   0.04942   0.04286  -0.0279   0.0325   1.0000
  14.000   1.3423   0.05270   0.04628  -0.0276   0.0269   1.0000
  14.250   1.3325   0.05675   0.05037  -0.0277   0.0247   1.0000
  14.500   1.3264   0.06060   0.05440  -0.0278   0.0225   1.0000
  14.750   1.3216   0.06445   0.05838  -0.0283   0.0207   1.0000
  15.000   1.3154   0.06862   0.06267  -0.0291   0.0197   1.0000
  15.250   1.3070   0.07323   0.06736  -0.0302   0.0189   1.0000
  15.500   1.2961   0.07827   0.07246  -0.0313   0.0182   1.0000
  15.750   1.2917   0.08269   0.07707  -0.0326   0.0177   1.0000
  16.000   1.2863   0.08734   0.08190  -0.0340   0.0172   1.0000
  16.250   1.2804   0.09221   0.08694  -0.0357   0.0167   1.0000
  16.500   1.2746   0.09715   0.09203  -0.0376   0.0163   1.0000
  16.750   1.2680   0.10235   0.09739  -0.0397   0.0160   1.0000
  17.000   1.2610   0.10774   0.10293  -0.0421   0.0156   1.0000
  17.250   1.2536   0.11331   0.10866  -0.0448   0.0154   1.0000
  17.500   1.2456   0.11916   0.11465  -0.0477   0.0152   1.0000
  17.750   1.2369   0.12525   0.12090  -0.0510   0.0150   1.0000
  18.000   1.2271   0.13173   0.12754  -0.0546   0.0150   1.0000
  18.250   1.2161   0.13868   0.13466  -0.0587   0.0149   1.0000
  18.500   1.2022   0.14654   0.14272  -0.0636   0.0149   1.0000
  18.750   1.1844   0.15573   0.15212  -0.0695   0.0151   1.0000
  19.000   1.1603   0.16710   0.16371  -0.0770   0.0154   1.0000
  19.250   1.1053   0.18908   0.18597  -0.0911   0.0167   1.0000
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