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AH-7-47-6 AIRFOIL (ah7476-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: AH-7-47-6 AIRFOIL (ah7476-il)
Reynolds number: 50,000
Max Cl/Cd: 48.92 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah7476-il-50000-n5.txt
Download as CSV file: xf-ah7476-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH-7-47-6 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3379   0.12202   0.11525  -0.0260   1.0000   0.0666
  -8.000  -0.3492   0.12195   0.11530  -0.0245   1.0000   0.0670
  -7.750  -0.3585   0.12174   0.11521  -0.0242   1.0000   0.0673
  -7.500  -0.3462   0.11523   0.10872  -0.0216   1.0000   0.0692
  -7.250  -0.3444   0.11235   0.10588  -0.0199   1.0000   0.0716
  -7.000  -0.3460   0.11041   0.10401  -0.0188   1.0000   0.0744
  -6.750  -0.3486   0.10901   0.10266  -0.0189   1.0000   0.0775
  -6.500  -0.3501   0.10875   0.10253  -0.0224   1.0000   0.0794
  -6.250  -0.3469   0.10577   0.09960  -0.0233   1.0000   0.0806
  -6.000  -0.3439   0.10154   0.09539  -0.0187   1.0000   0.0842
  -5.750  -0.3394   0.09910   0.09299  -0.0191   1.0000   0.0882
  -5.500  -0.3255   0.09780   0.09172  -0.0269   1.0000   0.0928
  -5.250  -0.3167   0.09423   0.08820  -0.0283   1.0000   0.0945
  -5.000  -0.3137   0.09075   0.08475  -0.0249   1.0000   0.0976
  -4.750  -0.3013   0.08795   0.08195  -0.0270   1.0000   0.1030
  -4.500  -0.2737   0.08479   0.07877  -0.0362   1.0000   0.1089
  -4.250  -0.2690   0.08168   0.07569  -0.0331   1.0000   0.1144
  -4.000  -0.2351   0.07832   0.07227  -0.0427   1.0000   0.1237
  -3.750  -0.2242   0.07524   0.06918  -0.0416   1.0000   0.1289
  -3.500  -0.1812   0.07155   0.06536  -0.0523   0.9996   0.1385
  -3.000  -0.0941   0.06419   0.05776  -0.0684   0.9931   0.1679
  -2.750  -0.0584   0.06085   0.05434  -0.0732   0.9897   0.1846
  -2.250   0.0871   0.05112   0.04379  -0.1015   0.9858   0.1259
  -1.750   0.2317   0.04232   0.03364  -0.1249   0.9828   0.0782
  -1.500   0.2837   0.03998   0.03092  -0.1312   0.9801   0.0750
  -1.250   0.3393   0.03783   0.02823  -0.1378   0.9770   0.0723
  -1.000   0.3904   0.03631   0.02622  -0.1431   0.9711   0.0738
  -0.750   0.4409   0.03501   0.02447  -0.1480   0.9640   0.0754
  -0.500   0.4918   0.03383   0.02287  -0.1526   0.9574   0.0750
  -0.250   0.5360   0.03296   0.02167  -0.1557   0.9497   0.0752
   0.000   0.5731   0.03240   0.02083  -0.1575   0.9420   0.0759
   0.250   0.6147   0.03190   0.02009  -0.1600   0.9368   0.0773
   0.500   0.6469   0.03163   0.01967  -0.1609   0.9278   0.0791
   0.750   0.6833   0.03131   0.01936  -0.1628   0.9200   0.0847
   1.000   0.7221   0.03104   0.01906  -0.1649   0.9124   0.0939
   1.250   0.7546   0.03086   0.01897  -0.1659   0.9021   0.1051
   1.750   0.8234   0.02896   0.01883  -0.1685   0.8839   1.0000
   2.000   0.8528   0.02907   0.01881  -0.1685   0.8716   1.0000
   2.250   0.8848   0.02909   0.01872  -0.1690   0.8601   1.0000
   2.500   0.9243   0.02881   0.01838  -0.1706   0.8514   1.0000
   2.750   0.9535   0.02880   0.01838  -0.1705   0.8378   1.0000
   3.000   0.9836   0.02870   0.01830  -0.1704   0.8242   1.0000
   3.500   1.0462   0.02836   0.01811  -0.1704   0.7959   1.0000
   3.750   1.0782   0.02815   0.01799  -0.1705   0.7802   1.0000
   4.000   1.1101   0.02790   0.01783  -0.1704   0.7630   1.0000
   4.250   1.1388   0.02761   0.01764  -0.1695   0.7409   1.0000
   4.500   1.1689   0.02716   0.01730  -0.1686   0.7153   1.0000
   4.750   1.1971   0.02687   0.01708  -0.1675   0.6861   1.0000
   5.000   1.2282   0.02661   0.01686  -0.1669   0.6572   1.0000
   5.250   1.2598   0.02651   0.01682  -0.1666   0.6288   1.0000
   5.500   1.2899   0.02661   0.01693  -0.1661   0.6000   1.0000
   5.750   1.3173   0.02694   0.01726  -0.1653   0.5711   1.0000
   6.000   1.3424   0.02744   0.01782  -0.1642   0.5424   1.0000
   6.250   1.3653   0.02806   0.01846  -0.1628   0.5133   1.0000
   6.500   1.3850   0.02881   0.01921  -0.1609   0.4817   1.0000
   6.750   1.4018   0.02968   0.02006  -0.1586   0.4480   1.0000
   7.000   1.4154   0.03066   0.02101  -0.1558   0.4124   1.0000
   7.250   1.4267   0.03170   0.02210  -0.1527   0.3768   1.0000
   7.500   1.4368   0.03277   0.02327  -0.1496   0.3413   1.0000
   7.750   1.4459   0.03391   0.02448  -0.1464   0.3061   1.0000
   8.000   1.4514   0.03525   0.02572  -0.1428   0.2712   1.0000
   8.250   1.4549   0.03682   0.02717  -0.1390   0.2363   1.0000
   8.500   1.4565   0.03873   0.02889  -0.1354   0.1999   1.0000
   8.750   1.4573   0.04087   0.03085  -0.1320   0.1627   1.0000
   9.000   1.4590   0.04311   0.03304  -0.1289   0.1274   1.0000
   9.250   1.4597   0.04559   0.03542  -0.1259   0.0989   1.0000
   9.500   1.4571   0.04847   0.03816  -0.1226   0.0808   1.0000
   9.750   1.4532   0.05156   0.04123  -0.1194   0.0688   1.0000
  10.000   1.4519   0.05451   0.04433  -0.1165   0.0594   1.0000
  10.250   1.4476   0.05778   0.04763  -0.1137   0.0539   1.0000
  10.500   1.4495   0.06068   0.05082  -0.1111   0.0493   1.0000
  10.750   1.4505   0.06369   0.05401  -0.1088   0.0460   1.0000
  11.000   1.4498   0.06687   0.05728  -0.1067   0.0434   1.0000
  11.250   1.4544   0.06989   0.06059  -0.1047   0.0406   1.0000
  11.500   1.4568   0.07305   0.06411  -0.1030   0.0380   1.0000
  11.750   1.4567   0.07640   0.06769  -0.1015   0.0360   1.0000
  12.000   1.4566   0.07987   0.07135  -0.1001   0.0348   1.0000
  12.250   1.4570   0.08352   0.07515  -0.0989   0.0338   1.0000
  12.500   1.4545   0.08779   0.07971  -0.0979   0.0332   1.0000
  12.750   1.4472   0.09262   0.08492  -0.0974   0.0328   1.0000
  13.000   1.4363   0.09795   0.09061  -0.0977   0.0325   1.0000
  13.250   1.4228   0.10379   0.09678  -0.0988   0.0323   1.0000
  13.500   1.4075   0.11015   0.10343  -0.1008   0.0322   1.0000
  13.750   1.3911   0.11712   0.11068  -0.1038   0.0322   1.0000
  14.000   1.3742   0.12476   0.11857  -0.1079   0.0323   1.0000
  14.250   1.3572   0.13311   0.12712  -0.1129   0.0325   1.0000
  14.500   1.3408   0.14203   0.13622  -0.1188   0.0327   1.0000
  14.750   1.3252   0.15154   0.14588  -0.1252   0.0330   1.0000
  15.000   1.3113   0.16134   0.15579  -0.1319   0.0332   1.0000
  15.250   1.3001   0.17109   0.16560  -0.1384   0.0335   1.0000
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