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AH 79-100 A AIRFOIL (ah79100a-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: AH 79-100 A AIRFOIL (ah79100a-il)
Reynolds number: 100,000
Max Cl/Cd: 61.95 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah79100a-il-100000.txt
Download as CSV file: xf-ah79100a-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 79-100 A 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3531   0.10222   0.09722  -0.0359   1.0000   0.1056
  -8.750  -0.3660   0.10025   0.09536  -0.0380   1.0000   0.1103
  -8.500  -0.3945   0.09939   0.09469  -0.0404   1.0000   0.1114
  -8.250  -0.3612   0.09401   0.08924  -0.0362   1.0000   0.1159
  -8.000  -0.3624   0.09199   0.08728  -0.0351   1.0000   0.1217
  -7.750  -0.3839   0.09068   0.08613  -0.0344   1.0000   0.1243
  -7.500  -0.4105   0.08977   0.08538  -0.0324   1.0000   0.1251
  -7.250  -0.4427   0.08754   0.08329  -0.0375   1.0000   0.1260
  -7.000  -0.4085   0.08482   0.08052  -0.0263   1.0000   0.1328
  -6.750  -0.4251   0.08305   0.07886  -0.0261   1.0000   0.1379
  -6.500  -0.4512   0.07822   0.07411  -0.0375   1.0000   0.1412
  -6.250  -0.4387   0.07757   0.07351  -0.0256   1.0000   0.1448
  -6.000  -0.4475   0.07207   0.06799  -0.0380   1.0000   0.1562
  -5.750  -0.4421   0.07062   0.06662  -0.0307   1.0000   0.1582
  -5.500  -0.4017   0.04333   0.03776  -0.0657   1.0000   0.0846
  -5.250  -0.3986   0.04710   0.04219  -0.0599   1.0000   0.1144
  -5.000  -0.3432   0.03253   0.02574  -0.0717   1.0000   0.0731
  -4.750  -0.3167   0.03026   0.02312  -0.0727   1.0000   0.0763
  -4.500  -0.2872   0.02763   0.01991  -0.0737   1.0000   0.0774
  -4.250  -0.2596   0.02601   0.01778  -0.0741   1.0000   0.0816
  -4.000  -0.2333   0.02423   0.01577  -0.0744   1.0000   0.0862
  -3.750  -0.2084   0.02309   0.01451  -0.0742   1.0000   0.0911
  -3.500  -0.1836   0.02213   0.01341  -0.0740   1.0000   0.0997
  -3.250  -0.1538   0.02132   0.01253  -0.0747   0.9983   0.1105
  -3.000  -0.1128   0.02037   0.01178  -0.0776   0.9932   0.1334
  -2.750  -0.0701   0.01932   0.01112  -0.0810   0.9884   0.2006
  -2.500  -0.0309   0.01871   0.01146  -0.0838   0.9817   0.4127
  -2.250   0.0060   0.01918   0.01196  -0.0856   0.9734   0.4823
  -2.000   0.0443   0.01967   0.01244  -0.0875   0.9657   0.5324
  -1.750   0.0794   0.01997   0.01276  -0.0887   0.9570   0.5700
  -1.500   0.1130   0.02019   0.01297  -0.0898   0.9481   0.6046
  -1.250   0.1526   0.02033   0.01312  -0.0918   0.9408   0.6384
  -1.000   0.1829   0.02036   0.01315  -0.0923   0.9306   0.6652
  -0.750   0.2226   0.02032   0.01314  -0.0943   0.9234   0.6927
  -0.500   0.2553   0.02023   0.01307  -0.0951   0.9133   0.7181
  -0.250   0.2887   0.02015   0.01300  -0.0960   0.9037   0.7458
   0.000   0.3300   0.01990   0.01280  -0.0982   0.8966   0.7772
   0.250   0.3593   0.01974   0.01272  -0.0983   0.8860   0.8110
   0.500   0.4041   0.01919   0.01233  -0.1007   0.8808   0.8650
   0.750   0.4486   0.01891   0.01213  -0.1043   0.8698   1.0000
   1.000   0.4966   0.01880   0.01189  -0.1084   0.8619   1.0000
   1.250   0.5393   0.01865   0.01164  -0.1111   0.8529   1.0000
   1.500   0.5734   0.01866   0.01158  -0.1121   0.8418   1.0000
   1.750   0.6180   0.01832   0.01120  -0.1145   0.8357   1.0000
   2.000   0.6474   0.01836   0.01121  -0.1145   0.8232   1.0000
   2.250   0.6783   0.01831   0.01114  -0.1146   0.8111   1.0000
   2.500   0.7110   0.01815   0.01100  -0.1148   0.8000   1.0000
   2.750   0.7478   0.01779   0.01062  -0.1154   0.7910   1.0000
   3.000   0.7759   0.01777   0.01062  -0.1149   0.7776   1.0000
   3.250   0.8045   0.01770   0.01059  -0.1143   0.7640   1.0000
   3.500   0.8335   0.01759   0.01050  -0.1138   0.7499   1.0000
   3.750   0.8624   0.01747   0.01040  -0.1132   0.7354   1.0000
   4.000   0.8910   0.01739   0.01034  -0.1125   0.7204   1.0000
   4.250   0.9197   0.01725   0.01023  -0.1118   0.7041   1.0000
   4.500   0.9482   0.01709   0.01006  -0.1109   0.6864   1.0000
   4.750   0.9728   0.01713   0.01014  -0.1096   0.6649   1.0000
   5.000   0.9999   0.01711   0.01013  -0.1087   0.6448   1.0000
   5.250   1.0253   0.01723   0.01027  -0.1076   0.6234   1.0000
   5.500   1.0505   0.01737   0.01041  -0.1065   0.6006   1.0000
   5.750   1.0742   0.01757   0.01062  -0.1051   0.5754   1.0000
   6.000   1.0975   0.01779   0.01085  -0.1037   0.5484   1.0000
   6.250   1.1194   0.01807   0.01111  -0.1021   0.5187   1.0000
   6.500   1.1398   0.01841   0.01144  -0.1004   0.4859   1.0000
   6.750   1.1591   0.01880   0.01178  -0.0985   0.4504   1.0000
   7.000   1.1764   0.01931   0.01226  -0.0964   0.4095   1.0000
   7.250   1.1911   0.02000   0.01280  -0.0940   0.3624   1.0000
   7.500   1.2024   0.02097   0.01352  -0.0912   0.3059   1.0000
   7.750   1.2106   0.02229   0.01448  -0.0883   0.2457   1.0000
   8.000   1.2172   0.02394   0.01573  -0.0854   0.1905   1.0000
   8.250   1.2220   0.02587   0.01729  -0.0824   0.1461   1.0000
   8.500   1.2255   0.02804   0.01915  -0.0791   0.1128   1.0000
   8.750   1.2308   0.03012   0.02109  -0.0761   0.0905   1.0000
   9.000   1.2381   0.03224   0.02304  -0.0734   0.0764   1.0000
   9.250   1.2525   0.03409   0.02497  -0.0714   0.0671   1.0000
   9.500   1.2768   0.03676   0.02763  -0.0709   0.0608   1.0000
   9.750   1.2970   0.03878   0.02976  -0.0699   0.0558   1.0000
  10.000   1.3241   0.04199   0.03296  -0.0702   0.0514   1.0000
  10.250   1.3440   0.04471   0.03608  -0.0690   0.0495   1.0000
  10.500   1.3607   0.04784   0.03958  -0.0676   0.0482   1.0000
  10.750   1.3715   0.05121   0.04334  -0.0656   0.0474   1.0000
  11.000   1.3759   0.05478   0.04732  -0.0632   0.0471   1.0000
  11.250   1.3728   0.05831   0.05124  -0.0602   0.0469   1.0000
  11.500   1.3638   0.06173   0.05501  -0.0569   0.0468   1.0000
  11.750   1.3507   0.06529   0.05890  -0.0538   0.0467   1.0000
  12.000   1.3345   0.06910   0.06301  -0.0513   0.0466   1.0000
  12.250   1.3145   0.07346   0.06767  -0.0495   0.0468   1.0000
  12.500   1.2916   0.07839   0.07289  -0.0487   0.0472   1.0000
  12.750   1.2665   0.08397   0.07874  -0.0490   0.0477   1.0000
  13.000   1.2397   0.09034   0.08534  -0.0506   0.0483   1.0000
  13.250   1.2123   0.09748   0.09270  -0.0534   0.0491   1.0000
  13.500   1.1858   0.10540   0.10078  -0.0574   0.0499   1.0000
  13.750   1.1605   0.11399   0.10950  -0.0623   0.0507   1.0000
  14.000   1.1395   0.12284   0.11844  -0.0674   0.0515   1.0000
  14.250   1.1277   0.13098   0.12660  -0.0710   0.0523   1.0000
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