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HQ 3.0/11 AIRFOIL (hq3011-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/11 AIRFOIL (hq3011-il)
Reynolds number: 50,000
Max Cl/Cd: 38.25 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3011-il-50000-n5.txt
Download as CSV file: xf-hq3011-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/11 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3658   0.12042   0.11326  -0.0358   1.0000   0.0983
 -10.250  -0.3659   0.11403   0.10686  -0.0391   1.0000   0.0616
  -9.750  -0.3733   0.10512   0.09810  -0.0437   1.0000   0.0506
  -9.500  -0.3700   0.10168   0.09472  -0.0436   1.0000   0.0495
  -9.250  -0.3701   0.09825   0.09137  -0.0440   1.0000   0.0486
  -9.000  -0.3729   0.09471   0.08793  -0.0445   1.0000   0.0478
  -8.750  -0.3774   0.09133   0.08465  -0.0449   1.0000   0.0470
  -8.500  -0.3847   0.08796   0.08140  -0.0453   1.0000   0.0462
  -8.250  -0.3959   0.08465   0.07823  -0.0453   1.0000   0.0456
  -8.000  -0.4120   0.08156   0.07528  -0.0450   1.0000   0.0449
  -7.750  -0.4299   0.07812   0.07196  -0.0453   1.0000   0.0442
  -7.500  -0.4467   0.07450   0.06841  -0.0455   1.0000   0.0435
  -7.250  -0.4622   0.07074   0.06464  -0.0456   1.0000   0.0427
  -7.000  -0.4752   0.06667   0.06048  -0.0457   1.0000   0.0420
  -6.750  -0.4831   0.06254   0.05619  -0.0458   1.0000   0.0415
  -6.500  -0.4860   0.05828   0.05168  -0.0460   1.0000   0.0411
  -6.250  -0.4833   0.05430   0.04738  -0.0461   1.0000   0.0409
  -6.000  -0.4758   0.05097   0.04378  -0.0459   1.0000   0.0414
  -5.750  -0.4624   0.04830   0.04090  -0.0461   0.9991   0.0432
  -5.500  -0.4336   0.04457   0.03666  -0.0493   0.9937   0.0461
  -5.250  -0.4033   0.04075   0.03216  -0.0519   0.9884   0.0486
  -5.000  -0.3700   0.03724   0.02788  -0.0541   0.9841   0.0505
  -4.750  -0.3404   0.03461   0.02485  -0.0553   0.9790   0.0536
  -4.500  -0.3082   0.03294   0.02285  -0.0569   0.9741   0.0612
  -4.250  -0.2761   0.03108   0.02066  -0.0579   0.9696   0.0685
  -4.000  -0.2456   0.02978   0.01902  -0.0583   0.9641   0.0792
  -3.750  -0.2132   0.02864   0.01777  -0.0594   0.9595   0.0933
  -3.500  -0.1840   0.02763   0.01665  -0.0597   0.9542   0.1070
  -3.250  -0.1545   0.02673   0.01569  -0.0604   0.9484   0.1228
  -3.000  -0.1201   0.02585   0.01480  -0.0621   0.9438   0.1439
  -2.750  -0.0927   0.02495   0.01410  -0.0628   0.9373   0.1865
  -2.500  -0.0645   0.02316   0.01382  -0.0640   0.9325   0.4343
  -2.250  -0.0421   0.02309   0.01407  -0.0621   0.9259   0.6251
  -2.000  -0.0209   0.02315   0.01421  -0.0598   0.9189   0.7032
  -1.750  -0.0049   0.02323   0.01444  -0.0559   0.9120   0.7770
  -1.500   0.0080   0.02326   0.01456  -0.0510   0.9046   0.8613
  -1.250   0.0588   0.02320   0.01436  -0.0539   0.9016   0.9364
  -1.000   0.1068   0.02322   0.01412  -0.0587   0.8946   0.9733
  -0.750   0.1493   0.02327   0.01390  -0.0627   0.8886   1.0000
  -0.500   0.1729   0.02341   0.01381  -0.0632   0.8790   1.0000
  -0.250   0.2119   0.02354   0.01370  -0.0660   0.8732   1.0000
   0.000   0.2359   0.02377   0.01375  -0.0662   0.8632   1.0000
   0.250   0.2703   0.02396   0.01375  -0.0679   0.8560   1.0000
   0.500   0.3006   0.02417   0.01382  -0.0689   0.8473   1.0000
   0.750   0.3292   0.02442   0.01395  -0.0696   0.8383   1.0000
   1.000   0.3657   0.02456   0.01397  -0.0713   0.8313   1.0000
   1.250   0.3908   0.02485   0.01419  -0.0712   0.8210   1.0000
   1.500   0.4239   0.02501   0.01427  -0.0723   0.8131   1.0000
   1.750   0.4538   0.02519   0.01441  -0.0727   0.8037   1.0000
   2.000   0.4801   0.02542   0.01461  -0.0726   0.7928   1.0000
   2.250   0.5110   0.02549   0.01466  -0.0730   0.7825   1.0000
   2.500   0.5483   0.02531   0.01449  -0.0740   0.7733   1.0000
   2.750   0.5757   0.02534   0.01454  -0.0737   0.7604   1.0000
   3.000   0.6033   0.02537   0.01458  -0.0733   0.7476   1.0000
   3.250   0.6311   0.02539   0.01464  -0.0729   0.7348   1.0000
   3.500   0.6592   0.02538   0.01472  -0.0726   0.7220   1.0000
   3.750   0.6877   0.02534   0.01474  -0.0722   0.7088   1.0000
   4.000   0.7160   0.02527   0.01474  -0.0717   0.6948   1.0000
   4.250   0.7441   0.02518   0.01476  -0.0711   0.6798   1.0000
   4.500   0.7723   0.02504   0.01470  -0.0704   0.6636   1.0000
   4.750   0.8012   0.02484   0.01458  -0.0698   0.6465   1.0000
   5.000   0.8258   0.02482   0.01465  -0.0686   0.6264   1.0000
   5.250   0.8512   0.02477   0.01472  -0.0675   0.6050   1.0000
   5.500   0.8755   0.02479   0.01482  -0.0663   0.5816   1.0000
   5.750   0.9016   0.02477   0.01484  -0.0653   0.5573   1.0000
   6.000   0.9265   0.02485   0.01494  -0.0641   0.5306   1.0000
   6.250   0.9496   0.02507   0.01519  -0.0629   0.5020   1.0000
   6.500   0.9715   0.02543   0.01553  -0.0615   0.4724   1.0000
   6.750   0.9923   0.02594   0.01599  -0.0601   0.4429   1.0000
   7.000   1.0119   0.02658   0.01657  -0.0586   0.4145   1.0000
   7.250   1.0305   0.02733   0.01731  -0.0571   0.3878   1.0000
   7.500   1.0476   0.02819   0.01816  -0.0556   0.3619   1.0000
   7.750   1.0644   0.02910   0.01908  -0.0540   0.3380   1.0000
   8.000   1.0809   0.03006   0.01999  -0.0525   0.3161   1.0000
   8.250   1.0960   0.03111   0.02109  -0.0509   0.2943   1.0000
   8.500   1.1107   0.03220   0.02215  -0.0493   0.2742   1.0000
   8.750   1.1239   0.03334   0.02337  -0.0476   0.2546   1.0000
   9.000   1.1350   0.03452   0.02466  -0.0456   0.2360   1.0000
   9.250   1.1449   0.03575   0.02593  -0.0436   0.2187   1.0000
   9.500   1.1542   0.03706   0.02726  -0.0417   0.2026   1.0000
   9.750   1.1625   0.03850   0.02879  -0.0398   0.1866   1.0000
  10.000   1.1707   0.04003   0.03042  -0.0380   0.1719   1.0000
  10.250   1.1781   0.04168   0.03214  -0.0363   0.1583   1.0000
  10.500   1.1844   0.04344   0.03396  -0.0347   0.1457   1.0000
  10.750   1.1921   0.04530   0.03592  -0.0332   0.1345   1.0000
  11.000   1.2000   0.04734   0.03817  -0.0318   0.1240   1.0000
  11.250   1.2053   0.04951   0.04055  -0.0304   0.1146   1.0000
  11.500   1.2091   0.05162   0.04263  -0.0292   0.1069   1.0000
  11.750   1.2141   0.05422   0.04558  -0.0280   0.0993   1.0000
  12.000   1.2188   0.05664   0.04803  -0.0270   0.0931   1.0000
  12.250   1.2163   0.05975   0.05148  -0.0261   0.0867   1.0000
  12.500   1.2149   0.06242   0.05409  -0.0255   0.0811   1.0000
  12.750   1.2087   0.06636   0.05846  -0.0252   0.0762   1.0000
  13.000   1.2034   0.06982   0.06203  -0.0251   0.0715   1.0000
  13.250   1.1947   0.07390   0.06624  -0.0256   0.0673   1.0000
  13.500   1.1804   0.07906   0.07173  -0.0268   0.0638   1.0000
  13.750   1.1686   0.08364   0.07639  -0.0285   0.0598   1.0000
  14.000   1.1587   0.08836   0.08113  -0.0302   0.0564   1.0000
  14.250   1.1409   0.09531   0.08843  -0.0332   0.0546   1.0000
  14.500   1.1231   0.10275   0.09614  -0.0368   0.0535   1.0000
  14.750   1.1037   0.11114   0.10478  -0.0411   0.0533   1.0000
  15.000   1.0810   0.12098   0.11483  -0.0465   0.0542   1.0000
  15.250   1.0575   0.13182   0.12579  -0.0526   0.0557   1.0000
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