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AH-7-47-6 AIRFOIL (ah7476-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: AH-7-47-6 AIRFOIL (ah7476-il)
Reynolds number: 500,000
Max Cl/Cd: 110.45 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah7476-il-500000-n5.txt
Download as CSV file: xf-ah7476-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2131   0.09772   0.09532  -0.0588   0.9834   0.0086
  -8.250  -0.2011   0.09412   0.09172  -0.0618   0.9811   0.0087
  -8.000  -0.1875   0.09027   0.08787  -0.0654   0.9793   0.0088
  -7.500  -0.1635   0.08397   0.08158  -0.0707   0.9721   0.0095
  -7.250  -0.1422   0.08123   0.07884  -0.0747   0.9703   0.0103
  -7.000  -0.1189   0.07739   0.07498  -0.0805   0.9689   0.0108
  -6.750  -0.1045   0.07402   0.07162  -0.0838   0.9631   0.0110
  -6.500  -0.0780   0.06955   0.06714  -0.0909   0.9608   0.0114
  -6.250  -0.0434   0.06341   0.06096  -0.1019   0.9589   0.0121
  -6.000  -0.0254   0.06177   0.05931  -0.1035   0.9528   0.0125
  -5.750   0.0057   0.05873   0.05625  -0.1095   0.9501   0.0137
  -5.500   0.0441   0.05394   0.05141  -0.1190   0.9473   0.0144
  -5.250   0.0901   0.04732   0.04470  -0.1321   0.9409   0.0155
  -5.000   0.1189   0.04582   0.04317  -0.1351   0.9383   0.0163
  -4.750   0.1646   0.04189   0.03915  -0.1442   0.9365   0.0179
  -4.500   0.2366   0.03320   0.03019  -0.1621   0.9323   0.0195
  -4.250   0.2610   0.03277   0.02975  -0.1628   0.9278   0.0203
  -4.000   0.3136   0.02872   0.02549  -0.1713   0.9255   0.0231
  -3.750   0.3640   0.02424   0.02074  -0.1791   0.9226   0.0228
  -3.250   0.4474   0.01885   0.01482  -0.1880   0.9128   0.0259
  -3.000   0.4883   0.01644   0.01204  -0.1916   0.9059   0.0261
  -2.750   0.5267   0.01464   0.00989  -0.1942   0.8983   0.0260
  -2.500   0.5611   0.01347   0.00845  -0.1958   0.8900   0.0261
  -2.000   0.6257   0.01201   0.00659  -0.1979   0.8717   0.0272
  -1.750   0.6574   0.01130   0.00568  -0.1987   0.8623   0.0265
  -1.500   0.6882   0.01075   0.00497  -0.1993   0.8533   0.0261
  -1.250   0.7181   0.01033   0.00442  -0.1997   0.8447   0.0261
  -0.750   0.7768   0.00971   0.00365  -0.2003   0.8281   0.0267
  -0.500   0.8058   0.00950   0.00338  -0.2005   0.8202   0.0272
  -0.250   0.8345   0.00933   0.00318  -0.2007   0.8115   0.0276
   0.000   0.8631   0.00920   0.00301  -0.2008   0.8025   0.0280
   0.250   0.8911   0.00915   0.00293  -0.2008   0.7920   0.0288
   0.500   0.9188   0.00913   0.00290  -0.2007   0.7810   0.0295
   0.750   0.9466   0.00905   0.00279  -0.2007   0.7652   0.0295
   1.000   0.9732   0.00905   0.00272  -0.2003   0.7384   0.0295
   1.250   0.9973   0.00923   0.00268  -0.1994   0.6871   0.0295
   1.500   1.0185   0.00967   0.00277  -0.1979   0.6208   0.0296
   1.750   1.0402   0.01016   0.00296  -0.1966   0.5606   0.0297
   2.000   1.0629   0.01058   0.00311  -0.1956   0.5083   0.0302
   2.500   1.1111   0.01126   0.00343  -0.1942   0.4440   0.0323
   2.750   1.1358   0.01155   0.00362  -0.1936   0.4227   0.0339
   3.000   1.1610   0.01178   0.00379  -0.1932   0.4058   0.0360
   3.250   1.1866   0.01197   0.00397  -0.1927   0.3936   0.0411
   3.500   1.2132   0.01206   0.00423  -0.1926   0.3819   0.1503
   4.000   1.2613   0.01142   0.00490  -0.1915   0.3503   1.0000
   4.250   1.2854   0.01176   0.00514  -0.1908   0.3259   1.0000
   4.500   1.3061   0.01243   0.00551  -0.1896   0.2703   1.0000
   4.750   1.3245   0.01334   0.00605  -0.1880   0.2077   1.0000
   5.000   1.3452   0.01404   0.00653  -0.1867   0.1700   1.0000
   5.250   1.3670   0.01458   0.00694  -0.1857   0.1453   1.0000
   5.500   1.3882   0.01518   0.00741  -0.1845   0.1175   1.0000
   5.750   1.4082   0.01590   0.00793  -0.1832   0.0836   1.0000
   6.000   1.4279   0.01661   0.00850  -0.1818   0.0609   1.0000
   6.250   1.4494   0.01711   0.00898  -0.1806   0.0508   1.0000
   6.500   1.4697   0.01771   0.00955  -0.1793   0.0376   1.0000
   6.750   1.4868   0.01861   0.01029  -0.1774   0.0172   1.0000
   7.000   1.5058   0.01928   0.01098  -0.1757   0.0136   1.0000
   7.250   1.5252   0.01986   0.01163  -0.1741   0.0118   1.0000
   7.500   1.5443   0.02043   0.01228  -0.1725   0.0109   1.0000
   7.750   1.5621   0.02107   0.01301  -0.1706   0.0100   1.0000
   8.000   1.5786   0.02179   0.01381  -0.1686   0.0092   1.0000
   8.250   1.5921   0.02273   0.01485  -0.1660   0.0083   1.0000
   8.500   1.6069   0.02348   0.01567  -0.1636   0.0078   1.0000
   8.750   1.6202   0.02419   0.01648  -0.1610   0.0074   1.0000
   9.000   1.6323   0.02504   0.01741  -0.1582   0.0070   1.0000
   9.250   1.6438   0.02594   0.01842  -0.1554   0.0066   1.0000
   9.500   1.6544   0.02693   0.01949  -0.1525   0.0063   1.0000
   9.750   1.6643   0.02798   0.02063  -0.1496   0.0060   1.0000
  10.000   1.6723   0.02918   0.02193  -0.1465   0.0058   1.0000
  10.250   1.6760   0.03075   0.02360  -0.1429   0.0056   1.0000
  10.500   1.6780   0.03248   0.02546  -0.1391   0.0054   1.0000
  10.750   1.6839   0.03393   0.02704  -0.1360   0.0053   1.0000
  11.000   1.6896   0.03544   0.02869  -0.1331   0.0051   1.0000
  11.250   1.6940   0.03708   0.03046  -0.1301   0.0050   1.0000
  11.500   1.6977   0.03884   0.03235  -0.1273   0.0048   1.0000
  11.750   1.7011   0.04066   0.03431  -0.1246   0.0046   1.0000
  12.000   1.7040   0.04258   0.03636  -0.1220   0.0044   1.0000
  12.250   1.7061   0.04464   0.03855  -0.1196   0.0043   1.0000
  12.500   1.7073   0.04686   0.04089  -0.1173   0.0041   1.0000
  12.750   1.7068   0.04934   0.04351  -0.1151   0.0040   1.0000
  13.000   1.7050   0.05202   0.04633  -0.1130   0.0040   1.0000
  13.250   1.7019   0.05495   0.04940  -0.1112   0.0039   1.0000
  13.500   1.6980   0.05810   0.05269  -0.1096   0.0038   1.0000
  13.750   1.6923   0.06163   0.05637  -0.1082   0.0038   1.0000
  14.000   1.6851   0.06550   0.06038  -0.1072   0.0037   1.0000
  14.250   1.6761   0.06983   0.06487  -0.1065   0.0036   1.0000
  14.500   1.6657   0.07461   0.06981  -0.1064   0.0036   1.0000
  14.750   1.6532   0.07994   0.07531  -0.1066   0.0035   1.0000
  15.000   1.6385   0.08585   0.08141  -0.1074   0.0035   1.0000
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