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HQ 3.0/13 AIRFOIL (hq3013-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/13 AIRFOIL (hq3013-il)
Reynolds number: 100,000
Max Cl/Cd: 55.91 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3013-il-100000.txt
Download as CSV file: xf-hq3013-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/13 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3556   0.09685   0.09220  -0.0430   1.0000   0.1255
  -9.000  -0.3699   0.09461   0.09009  -0.0424   1.0000   0.1294
  -8.750  -0.4090   0.09327   0.08893  -0.0417   1.0000   0.1318
  -8.500  -0.4505   0.09223   0.08807  -0.0395   1.0000   0.1323
  -8.250  -0.4882   0.09095   0.08693  -0.0370   1.0000   0.1324
  -8.000  -0.4471   0.08733   0.08325  -0.0323   1.0000   0.1372
  -7.750  -0.4637   0.08589   0.08189  -0.0292   1.0000   0.1392
  -7.500  -0.4896   0.08440   0.08050  -0.0264   1.0000   0.1405
  -7.250  -0.5150   0.08170   0.07788  -0.0263   1.0000   0.1425
  -7.000  -0.5868   0.07694   0.07279  -0.0354   1.0000   0.1478
  -6.500  -0.5561   0.04934   0.04385  -0.0476   0.9912   0.0724
  -6.250  -0.5328   0.04344   0.03738  -0.0504   0.9863   0.0687
  -6.000  -0.5018   0.03927   0.03256  -0.0532   0.9820   0.0703
  -5.750  -0.4746   0.03614   0.02872  -0.0542   0.9766   0.0737
  -5.500  -0.4426   0.03289   0.02486  -0.0558   0.9724   0.0772
  -5.250  -0.4090   0.03154   0.02337  -0.0577   0.9679   0.0861
  -5.000  -0.3811   0.02979   0.02136  -0.0583   0.9624   0.0939
  -4.750  -0.3457   0.02875   0.01998  -0.0599   0.9577   0.1044
  -4.500  -0.3137   0.02759   0.01881  -0.0612   0.9530   0.1137
  -4.250  -0.2855   0.02657   0.01772  -0.0615   0.9471   0.1222
  -4.000  -0.2489   0.02587   0.01690  -0.0632   0.9426   0.1335
  -3.750  -0.2205   0.02514   0.01628  -0.0637   0.9371   0.1459
  -3.500  -0.1919   0.02446   0.01569  -0.0640   0.9309   0.1623
  -3.250  -0.1554   0.02368   0.01523  -0.0660   0.9266   0.1975
  -3.000  -0.1364   0.02214   0.01468  -0.0655   0.9199   0.3343
  -2.750  -0.1148   0.02210   0.01568  -0.0633   0.9138   0.6141
  -2.500  -0.0914   0.02266   0.01620  -0.0616   0.9070   0.6678
  -2.250  -0.0684   0.02309   0.01661  -0.0599   0.8999   0.7011
  -2.000  -0.0379   0.02350   0.01697  -0.0594   0.8944   0.7317
  -1.750  -0.0224   0.02379   0.01723  -0.0567   0.8857   0.7544
  -1.500   0.0101   0.02402   0.01743  -0.0563   0.8809   0.7822
  -1.250   0.0187   0.02426   0.01766  -0.0524   0.8713   0.8065
  -1.000   0.0461   0.02428   0.01767  -0.0507   0.8661   0.8367
  -0.750   0.0543   0.02438   0.01777  -0.0468   0.8564   0.8582
  -0.500   0.0876   0.02427   0.01760  -0.0471   0.8513   0.8797
  -0.250   0.1018   0.02436   0.01767  -0.0447   0.8418   0.8993
   0.000   0.1437   0.02426   0.01751  -0.0470   0.8368   0.9153
   0.250   0.1739   0.02444   0.01766  -0.0481   0.8279   0.9311
   0.500   0.2271   0.02440   0.01755  -0.0529   0.8227   0.9448
   0.750   0.2877   0.02429   0.01737  -0.0590   0.8187   0.9567
   1.000   0.3376   0.02447   0.01753  -0.0640   0.8096   0.9727
   1.250   0.4087   0.02390   0.01690  -0.0714   0.8062   0.9809
   1.500   0.4630   0.02369   0.01667  -0.0767   0.7962   0.9983
   1.750   0.5122   0.02287   0.01580  -0.0800   0.7909   1.0000
   2.000   0.5141   0.02301   0.01590  -0.0766   0.7779   1.0000
   2.250   0.5395   0.02303   0.01587  -0.0766   0.7677   1.0000
   2.500   0.5835   0.02246   0.01527  -0.0789   0.7617   1.0000
   2.750   0.6092   0.02252   0.01532  -0.0787   0.7505   1.0000
   3.000   0.6561   0.02173   0.01449  -0.0810   0.7452   1.0000
   3.250   0.6818   0.02170   0.01446  -0.0805   0.7328   1.0000
   3.500   0.7125   0.02143   0.01419  -0.0805   0.7215   1.0000
   3.750   0.7576   0.02050   0.01323  -0.0821   0.7143   1.0000
   4.000   0.7851   0.02027   0.01300  -0.0816   0.7008   1.0000
   4.250   0.8137   0.02001   0.01276  -0.0811   0.6874   1.0000
   4.500   0.8432   0.01970   0.01246  -0.0807   0.6736   1.0000
   4.750   0.8731   0.01939   0.01215  -0.0803   0.6591   1.0000
   5.000   0.9028   0.01908   0.01184  -0.0799   0.6433   1.0000
   5.250   0.9323   0.01879   0.01153  -0.0794   0.6263   1.0000
   5.500   0.9583   0.01864   0.01137  -0.0785   0.6064   1.0000
   5.750   0.9827   0.01857   0.01131  -0.0774   0.5842   1.0000
   6.000   1.0075   0.01853   0.01121  -0.0763   0.5605   1.0000
   6.250   1.0320   0.01857   0.01115  -0.0752   0.5349   1.0000
   6.500   1.0527   0.01883   0.01134  -0.0736   0.5066   1.0000
   6.750   1.0730   0.01921   0.01160  -0.0721   0.4777   1.0000
   7.000   1.0926   0.01972   0.01198  -0.0705   0.4492   1.0000
   7.250   1.1115   0.02035   0.01247  -0.0690   0.4220   1.0000
   7.500   1.1307   0.02106   0.01301  -0.0676   0.3969   1.0000
   7.750   1.1485   0.02181   0.01368  -0.0660   0.3731   1.0000
   8.000   1.1664   0.02260   0.01437  -0.0645   0.3513   1.0000
   8.250   1.1835   0.02342   0.01513  -0.0629   0.3308   1.0000
   8.500   1.2014   0.02427   0.01587  -0.0615   0.3123   1.0000
   8.750   1.2205   0.02520   0.01670  -0.0604   0.2949   1.0000
   9.000   1.2365   0.02613   0.01763  -0.0588   0.2783   1.0000
   9.250   1.2525   0.02708   0.01857  -0.0572   0.2627   1.0000
   9.500   1.2678   0.02804   0.01952  -0.0556   0.2479   1.0000
   9.750   1.2827   0.02902   0.02049  -0.0539   0.2340   1.0000
  10.000   1.2968   0.03000   0.02146  -0.0522   0.2205   1.0000
  10.250   1.3060   0.03093   0.02248  -0.0497   0.2082   1.0000
  10.500   1.3141   0.03198   0.02362  -0.0472   0.1962   1.0000
  10.750   1.3226   0.03313   0.02483  -0.0448   0.1845   1.0000
  11.000   1.3327   0.03439   0.02609  -0.0428   0.1733   1.0000
  11.250   1.3443   0.03569   0.02732  -0.0411   0.1622   1.0000
  11.500   1.3486   0.03700   0.02876  -0.0385   0.1523   1.0000
  11.750   1.3553   0.03861   0.03051  -0.0364   0.1429   1.0000
  12.000   1.3684   0.04018   0.03201  -0.0351   0.1339   1.0000
  12.250   1.3703   0.04180   0.03384  -0.0327   0.1265   1.0000
  12.500   1.3827   0.04365   0.03571  -0.0316   0.1193   1.0000
  12.750   1.3865   0.04552   0.03777  -0.0296   0.1133   1.0000
  13.000   1.4016   0.04747   0.03969  -0.0289   0.1071   1.0000
  13.250   1.3959   0.04969   0.04223  -0.0265   0.1027   1.0000
  13.500   1.4071   0.05114   0.04355  -0.0256   0.0968   1.0000
  13.750   1.4015   0.05385   0.04657  -0.0237   0.0930   1.0000
  14.000   1.3934   0.05650   0.04950  -0.0221   0.0895   1.0000
  14.250   1.4060   0.05791   0.05064  -0.0216   0.0831   1.0000
  14.500   1.3885   0.06120   0.05433  -0.0202   0.0809   1.0000
  14.750   1.3741   0.06461   0.05803  -0.0194   0.0779   1.0000
  15.000   1.3716   0.06687   0.06029  -0.0191   0.0737   1.0000
  15.250   1.3669   0.07016   0.06364  -0.0189   0.0700   1.0000
  15.500   1.3491   0.07478   0.06860  -0.0193   0.0680   1.0000
  15.750   1.3323   0.07956   0.07364  -0.0202   0.0658   1.0000
  16.000   1.3433   0.08115   0.07495  -0.0201   0.0599   1.0000
  16.250   1.3202   0.08718   0.08133  -0.0219   0.0589   1.0000
  16.500   1.2965   0.09391   0.08839  -0.0244   0.0579   1.0000
  16.750   1.2720   0.10132   0.09610  -0.0278   0.0571   1.0000
  17.000   1.2460   0.10966   0.10470  -0.0320   0.0571   1.0000
  17.250   1.2157   0.11944   0.11473  -0.0375   0.0579   1.0000
  17.500   1.1838   0.13028   0.12576  -0.0440   0.0590   1.0000
  17.750   1.1505   0.14233   0.13793  -0.0515   0.0600   1.0000
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