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HQ 0/10 AIRFOIL (hq010-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 0/10 AIRFOIL (hq010-il)
Reynolds number: 200,000
Max Cl/Cd: 41.37 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq010-il-200000-n5.txt
Download as CSV file: xf-hq010-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 0/10 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.8067   0.10179   0.09837   0.0055   1.0000   0.0085
 -13.000  -0.8454   0.08703   0.08358  -0.0030   1.0000   0.0077
 -12.750  -0.8795   0.07371   0.07010  -0.0124   1.0000   0.0072
 -12.500  -0.9086   0.06384   0.06002  -0.0196   1.0000   0.0069
 -12.250  -0.9328   0.05660   0.05255  -0.0241   1.0000   0.0068
 -12.000  -0.9507   0.05131   0.04704  -0.0264   1.0000   0.0069
 -11.750  -0.9665   0.04691   0.04241  -0.0273   1.0000   0.0071
 -11.500  -0.9804   0.04314   0.03838  -0.0270   1.0000   0.0070
 -11.250  -0.9903   0.04009   0.03507  -0.0255   1.0000   0.0071
 -11.000  -0.9967   0.03750   0.03221  -0.0232   1.0000   0.0076
 -10.750  -0.9990   0.03502   0.02944  -0.0207   1.0000   0.0079
 -10.500  -0.9935   0.03274   0.02681  -0.0189   1.0000   0.0086
 -10.250  -0.9839   0.03116   0.02510  -0.0175   1.0000   0.0094
 -10.000  -0.9658   0.03088   0.02480  -0.0169   1.0000   0.0107
  -9.750  -0.9504   0.02965   0.02335  -0.0157   1.0000   0.0124
  -9.500  -0.9335   0.02826   0.02160  -0.0146   1.0000   0.0138
  -9.250  -0.9194   0.02662   0.01987  -0.0134   1.0000   0.0154
  -9.000  -0.9001   0.02583   0.01897  -0.0127   1.0000   0.0170
  -8.750  -0.8789   0.02530   0.01829  -0.0121   1.0000   0.0195
  -8.500  -0.8565   0.02489   0.01766  -0.0115   1.0000   0.0212
  -8.250  -0.8390   0.02320   0.01592  -0.0105   1.0000   0.0235
  -8.000  -0.8176   0.02247   0.01511  -0.0099   1.0000   0.0255
  -7.750  -0.7959   0.02156   0.01408  -0.0091   1.0000   0.0273
  -7.500  -0.7746   0.02051   0.01286  -0.0082   1.0000   0.0286
  -7.250  -0.7531   0.01957   0.01179  -0.0073   1.0000   0.0299
  -7.000  -0.7311   0.01877   0.01087  -0.0065   1.0000   0.0309
  -6.750  -0.7118   0.01764   0.00972  -0.0054   1.0000   0.0332
  -6.500  -0.6903   0.01690   0.00895  -0.0045   1.0000   0.0358
  -6.250  -0.6679   0.01632   0.00830  -0.0038   1.0000   0.0396
  -6.000  -0.6458   0.01572   0.00764  -0.0029   1.0000   0.0441
  -5.750  -0.6241   0.01511   0.00700  -0.0020   1.0000   0.0503
  -5.500  -0.6022   0.01457   0.00645  -0.0011   1.0000   0.0578
  -5.250  -0.5807   0.01408   0.00597  -0.0002   1.0000   0.0690
  -5.000  -0.5605   0.01356   0.00553   0.0009   1.0000   0.0864
  -4.750  -0.5326   0.01293   0.00505   0.0003   0.9923   0.1170
  -4.500  -0.4998   0.01220   0.00465  -0.0015   0.9800   0.1836
  -4.250  -0.4663   0.01167   0.00427  -0.0032   0.9686   0.2349
  -4.000  -0.4341   0.01111   0.00392  -0.0046   0.9566   0.2892
  -3.750  -0.4042   0.01047   0.00364  -0.0055   0.9438   0.3710
  -3.500  -0.3749   0.01000   0.00343  -0.0061   0.9310   0.4476
  -3.250  -0.3471   0.00964   0.00331  -0.0061   0.9183   0.5153
  -3.000  -0.3197   0.00944   0.00327  -0.0059   0.9060   0.5728
  -2.750  -0.2925   0.00934   0.00326  -0.0055   0.8946   0.6182
  -2.500  -0.2655   0.00930   0.00323  -0.0050   0.8836   0.6489
  -2.250  -0.2387   0.00927   0.00315  -0.0045   0.8715   0.6654
  -2.000  -0.2122   0.00925   0.00307  -0.0040   0.8587   0.6785
  -1.750  -0.1858   0.00924   0.00300  -0.0034   0.8463   0.6913
  -1.500  -0.1592   0.00923   0.00295  -0.0029   0.8358   0.7046
  -1.250  -0.1326   0.00923   0.00291  -0.0025   0.8264   0.7177
  -1.000  -0.1060   0.00922   0.00288  -0.0020   0.8165   0.7293
  -0.750  -0.0796   0.00921   0.00288  -0.0015   0.8064   0.7419
  -0.500  -0.0532   0.00921   0.00288  -0.0009   0.7963   0.7549
  -0.250  -0.0267   0.00921   0.00286  -0.0004   0.7864   0.7656
   0.000   0.0000   0.00921   0.00286   0.0000   0.7756   0.7756
   0.250   0.0268   0.00921   0.00286   0.0004   0.7656   0.7864
   0.500   0.0532   0.00921   0.00288   0.0009   0.7548   0.7964
   0.750   0.0796   0.00921   0.00288   0.0015   0.7419   0.8064
   1.000   0.1061   0.00922   0.00288   0.0020   0.7293   0.8164
   1.250   0.1326   0.00923   0.00291   0.0025   0.7177   0.8265
   1.500   0.1592   0.00923   0.00295   0.0029   0.7046   0.8358
   1.750   0.1858   0.00924   0.00300   0.0034   0.6913   0.8463
   2.000   0.2122   0.00925   0.00307   0.0040   0.6785   0.8587
   2.250   0.2387   0.00927   0.00315   0.0045   0.6654   0.8715
   2.500   0.2655   0.00930   0.00323   0.0050   0.6488   0.8836
   2.750   0.2925   0.00934   0.00326   0.0055   0.6180   0.8946
   3.000   0.3197   0.00944   0.00327   0.0059   0.5729   0.9060
   3.250   0.3471   0.00964   0.00331   0.0061   0.5150   0.9182
   3.500   0.3750   0.01000   0.00343   0.0061   0.4481   0.9310
   3.750   0.4042   0.01047   0.00364   0.0055   0.3712   0.9438
   4.000   0.4341   0.01112   0.00392   0.0046   0.2889   0.9566
   4.250   0.4663   0.01167   0.00427   0.0032   0.2347   0.9686
   4.500   0.4998   0.01220   0.00465   0.0015   0.1840   0.9801
   4.750   0.5326   0.01293   0.00505  -0.0003   0.1168   0.9923
   5.000   0.5605   0.01355   0.00553  -0.0009   0.0864   1.0000
   5.250   0.5807   0.01408   0.00597   0.0002   0.0689   1.0000
   5.500   0.6022   0.01457   0.00645   0.0011   0.0579   1.0000
   5.750   0.6241   0.01511   0.00700   0.0020   0.0503   1.0000
   6.000   0.6457   0.01573   0.00765   0.0029   0.0438   1.0000
   6.250   0.6679   0.01632   0.00830   0.0038   0.0395   1.0000
   6.500   0.6903   0.01690   0.00894   0.0045   0.0357   1.0000
   6.750   0.7119   0.01764   0.00972   0.0054   0.0332   1.0000
   7.000   0.7311   0.01877   0.01087   0.0065   0.0309   1.0000
   7.250   0.7531   0.01957   0.01179   0.0073   0.0298   1.0000
   7.500   0.7746   0.02052   0.01287   0.0082   0.0286   1.0000
   7.750   0.7959   0.02157   0.01409   0.0091   0.0273   1.0000
   8.000   0.8175   0.02249   0.01513   0.0099   0.0255   1.0000
   8.250   0.8389   0.02323   0.01595   0.0105   0.0236   1.0000
   8.500   0.8566   0.02481   0.01759   0.0114   0.0212   1.0000
   8.750   0.8791   0.02522   0.01821   0.0120   0.0194   1.0000
   9.000   0.9001   0.02582   0.01896   0.0127   0.0170   1.0000
   9.250   0.9194   0.02661   0.01986   0.0134   0.0154   1.0000
   9.500   0.9333   0.02829   0.02163   0.0146   0.0138   1.0000
   9.750   0.9502   0.02970   0.02341   0.0158   0.0124   1.0000
  10.000   0.9656   0.03093   0.02485   0.0169   0.0107   1.0000
  10.250   0.9831   0.03135   0.02531   0.0176   0.0095   1.0000
  10.500   0.9933   0.03276   0.02683   0.0189   0.0086   1.0000
  10.750   0.9993   0.03499   0.02939   0.0207   0.0080   1.0000
  11.000   0.9968   0.03751   0.03222   0.0232   0.0076   1.0000
  11.250   0.9901   0.04015   0.03513   0.0255   0.0073   1.0000
  11.500   0.9805   0.04316   0.03840   0.0269   0.0070   1.0000
  11.750   0.9678   0.04680   0.04228   0.0273   0.0069   1.0000
  12.000   0.9530   0.05105   0.04677   0.0264   0.0067   1.0000
  12.250   0.9329   0.05665   0.05261   0.0240   0.0068   1.0000
  12.500   0.9098   0.06372   0.05990   0.0196   0.0069   1.0000
  12.750   0.8784   0.07408   0.07048   0.0120   0.0073   1.0000
  13.000   0.8388   0.08916   0.08574   0.0015   0.0076   1.0000
  13.250   0.7890   0.10678   0.10335  -0.0080   0.0091   1.0000
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