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HQ 3.0/10 AIRFOIL (hq3010-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/10 AIRFOIL (hq3010-il)
Reynolds number: 50,000
Max Cl/Cd: 39.77 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3010-il-50000-n5.txt
Download as CSV file: xf-hq3010-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/10 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3873   0.11879   0.11177  -0.0363   1.0000   0.0950
  -9.750  -0.3919   0.11607   0.10915  -0.0384   1.0000   0.0953
  -9.500  -0.3945   0.11300   0.10617  -0.0400   1.0000   0.0955
  -9.250  -0.3737   0.10400   0.09707  -0.0403   1.0000   0.0528
  -9.000  -0.3681   0.10045   0.09357  -0.0397   1.0000   0.0507
  -8.750  -0.3682   0.09709   0.09029  -0.0401   1.0000   0.0494
  -8.500  -0.3705   0.09386   0.08716  -0.0406   1.0000   0.0485
  -8.250  -0.3754   0.09069   0.08410  -0.0410   1.0000   0.0481
  -7.750  -0.4136   0.08176   0.07545  -0.0474   1.0000   0.0410
  -7.500  -0.4206   0.07863   0.07239  -0.0471   1.0000   0.0408
  -7.250  -0.4273   0.07555   0.06935  -0.0466   1.0000   0.0406
  -7.000  -0.4335   0.07242   0.06622  -0.0462   1.0000   0.0404
  -6.750  -0.4390   0.06902   0.06278  -0.0463   1.0000   0.0404
  -6.500  -0.4420   0.06543   0.05908  -0.0465   1.0000   0.0405
  -6.250  -0.4419   0.06165   0.05510  -0.0471   1.0000   0.0407
  -6.000  -0.4373   0.05797   0.05118  -0.0474   1.0000   0.0408
  -5.750  -0.4290   0.05426   0.04714  -0.0479   1.0000   0.0411
  -5.500  -0.4175   0.05059   0.04318  -0.0483   1.0000   0.0412
  -5.000  -0.3858   0.04344   0.03526  -0.0490   1.0000   0.0414
  -4.750  -0.3629   0.04000   0.03141  -0.0501   0.9987   0.0419
  -4.500  -0.3299   0.03680   0.02775  -0.0525   0.9943   0.0432
  -4.250  -0.2970   0.03425   0.02479  -0.0544   0.9897   0.0455
  -4.000  -0.2619   0.03222   0.02219  -0.0562   0.9853   0.0511
  -3.750  -0.2294   0.03023   0.01981  -0.0572   0.9807   0.0562
  -3.500  -0.1967   0.02879   0.01813  -0.0582   0.9759   0.0646
  -3.250  -0.1634   0.02746   0.01665  -0.0591   0.9718   0.0768
  -3.000  -0.1339   0.02644   0.01543  -0.0595   0.9659   0.0953
  -2.750  -0.1012   0.02541   0.01442  -0.0609   0.9609   0.1187
  -2.500  -0.0678   0.02445   0.01339  -0.0624   0.9557   0.1457
  -2.250  -0.0348   0.02294   0.01258  -0.0646   0.9503   0.2640
  -2.000  -0.0129   0.02198   0.01313  -0.0626   0.9452   0.6449
  -1.750   0.0044   0.02204   0.01325  -0.0594   0.9371   0.7399
  -1.500   0.0207   0.02189   0.01325  -0.0551   0.9308   0.8416
  -1.250   0.0670   0.02152   0.01285  -0.0573   0.9248   1.0000
  -1.000   0.1044   0.02170   0.01266  -0.0603   0.9183   1.0000
  -0.750   0.1349   0.02189   0.01255  -0.0618   0.9098   1.0000
  -0.500   0.1745   0.02211   0.01246  -0.0648   0.9037   1.0000
  -0.250   0.2036   0.02235   0.01247  -0.0659   0.8945   1.0000
   0.000   0.2422   0.02258   0.01248  -0.0685   0.8881   1.0000
   0.250   0.2722   0.02283   0.01255  -0.0694   0.8788   1.0000
   0.500   0.3041   0.02308   0.01265  -0.0707   0.8701   1.0000
   0.750   0.3412   0.02328   0.01272  -0.0727   0.8626   1.0000
   1.000   0.3694   0.02354   0.01288  -0.0732   0.8524   1.0000
   1.250   0.4037   0.02374   0.01300  -0.0745   0.8441   1.0000
   1.500   0.4365   0.02392   0.01313  -0.0756   0.8350   1.0000
   1.750   0.4641   0.02417   0.01335  -0.0757   0.8242   1.0000
   2.000   0.4949   0.02434   0.01350  -0.0763   0.8141   1.0000
   2.250   0.5326   0.02429   0.01345  -0.0777   0.8054   1.0000
   2.750   0.5909   0.02436   0.01359  -0.0775   0.7796   1.0000
   3.250   0.6498   0.02432   0.01365  -0.0772   0.7532   1.0000
   3.500   0.6791   0.02428   0.01372  -0.0769   0.7395   1.0000
   3.750   0.7085   0.02419   0.01372  -0.0766   0.7251   1.0000
   4.000   0.7384   0.02404   0.01366  -0.0762   0.7098   1.0000
   4.250   0.7687   0.02381   0.01353  -0.0757   0.6934   1.0000
   4.500   0.7924   0.02384   0.01371  -0.0744   0.6726   1.0000
   4.750   0.8218   0.02361   0.01358  -0.0737   0.6527   1.0000
   5.000   0.8457   0.02363   0.01372  -0.0724   0.6287   1.0000
   5.250   0.8711   0.02362   0.01380  -0.0712   0.6033   1.0000
   5.500   0.8961   0.02365   0.01396  -0.0700   0.5753   1.0000
   5.750   0.9209   0.02375   0.01409  -0.0688   0.5444   1.0000
   6.000   0.9455   0.02392   0.01424  -0.0675   0.5115   1.0000
   6.250   0.9671   0.02432   0.01463  -0.0660   0.4762   1.0000
   6.500   0.9884   0.02485   0.01506  -0.0645   0.4417   1.0000
   6.750   1.0075   0.02558   0.01580  -0.0630   0.4077   1.0000
   7.000   1.0258   0.02642   0.01658  -0.0614   0.3759   1.0000
   7.250   1.0432   0.02736   0.01747  -0.0599   0.3462   1.0000
   7.500   1.0598   0.02835   0.01845  -0.0583   0.3184   1.0000
   7.750   1.0753   0.02943   0.01951  -0.0567   0.2918   1.0000
   8.000   1.0901   0.03056   0.02064  -0.0550   0.2667   1.0000
   8.250   1.1037   0.03176   0.02182  -0.0533   0.2431   1.0000
   8.500   1.1159   0.03299   0.02319  -0.0515   0.2199   1.0000
   8.750   1.1275   0.03429   0.02454  -0.0497   0.1988   1.0000
   9.000   1.1371   0.03566   0.02596  -0.0476   0.1792   1.0000
   9.250   1.1455   0.03716   0.02745  -0.0456   0.1615   1.0000
   9.500   1.1550   0.03878   0.02920  -0.0438   0.1442   1.0000
   9.750   1.1660   0.04055   0.03109  -0.0421   0.1298   1.0000
  10.000   1.1738   0.04241   0.03305  -0.0403   0.1164   1.0000
  10.250   1.1800   0.04438   0.03511  -0.0386   0.1046   1.0000
  10.500   1.1876   0.04651   0.03727  -0.0370   0.0951   1.0000
  10.750   1.1901   0.04879   0.03975  -0.0354   0.0850   1.0000
  11.000   1.1879   0.05128   0.04244  -0.0339   0.0752   1.0000
  11.250   1.1859   0.05406   0.04541  -0.0327   0.0672   1.0000
  11.500   1.1814   0.05705   0.04850  -0.0319   0.0602   1.0000
  11.750   1.1754   0.06054   0.05222  -0.0314   0.0531   1.0000
  12.000   1.1669   0.06413   0.05584  -0.0315   0.0480   1.0000
  12.250   1.1610   0.06832   0.06030  -0.0315   0.0436   1.0000
  12.500   1.1539   0.07277   0.06500  -0.0319   0.0401   1.0000
  12.750   1.1464   0.07723   0.06958  -0.0328   0.0379   1.0000
  13.000   1.1383   0.08187   0.07421  -0.0339   0.0360   1.0000
  13.250   1.1273   0.08775   0.08046  -0.0357   0.0347   1.0000
  13.500   1.1144   0.09411   0.08713  -0.0382   0.0339   1.0000
  13.750   1.0999   0.10114   0.09444  -0.0416   0.0334   1.0000
  14.000   1.0845   0.10877   0.10230  -0.0455   0.0334   1.0000
  14.250   1.0681   0.11718   0.11092  -0.0502   0.0336   1.0000
  14.500   1.0510   0.12633   0.12023  -0.0555   0.0342   1.0000
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