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AH 79-100 A AIRFOIL (ah79100a-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: AH 79-100 A AIRFOIL (ah79100a-il)
Reynolds number: 500,000
Max Cl/Cd: 116.19 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah79100a-il-500000.txt
Download as CSV file: xf-ah79100a-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2879   0.08606   0.08396  -0.0406   1.0000   0.0255
  -9.500  -0.2998   0.08181   0.07976  -0.0410   1.0000   0.0264
  -9.250  -0.3131   0.07923   0.07723  -0.0393   1.0000   0.0266
  -8.500  -0.4848   0.04207   0.03951  -0.0837   0.9890   0.0157
  -8.250  -0.4642   0.03294   0.02979  -0.0959   0.9822   0.0153
  -8.000  -0.4335   0.02686   0.02305  -0.1033   0.9796   0.0154
  -7.750  -0.4067   0.02354   0.01924  -0.1060   0.9742   0.0157
  -7.500  -0.3764   0.01956   0.01479  -0.1092   0.9715   0.0162
  -7.250  -0.3412   0.01853   0.01368  -0.1116   0.9699   0.0173
  -7.000  -0.3052   0.01747   0.01248  -0.1139   0.9686   0.0184
  -6.750  -0.2747   0.01625   0.01106  -0.1148   0.9643   0.0195
  -6.500  -0.2422   0.01542   0.01004  -0.1159   0.9601   0.0205
  -6.250  -0.2099   0.01363   0.00814  -0.1175   0.9566   0.0226
  -6.000  -0.1778   0.01309   0.00753  -0.1185   0.9527   0.0248
  -5.750  -0.1497   0.01266   0.00702  -0.1185   0.9465   0.0265
  -5.500  -0.1202   0.01177   0.00608  -0.1192   0.9421   0.0298
  -5.250  -0.0913   0.01145   0.00572  -0.1194   0.9371   0.0326
  -5.000  -0.0636   0.01124   0.00545  -0.1193   0.9309   0.0347
  -4.750  -0.0355   0.01041   0.00455  -0.1195   0.9259   0.0387
  -4.500  -0.0085   0.01011   0.00421  -0.1192   0.9193   0.0426
  -4.250   0.0191   0.00968   0.00371  -0.1191   0.9131   0.0477
  -4.000   0.0468   0.00936   0.00336  -0.1190   0.9069   0.0563
  -3.750   0.0739   0.00893   0.00299  -0.1188   0.9001   0.0775
  -3.500   0.1018   0.00851   0.00269  -0.1189   0.8946   0.1201
  -3.250   0.1282   0.00807   0.00249  -0.1188   0.8873   0.1895
  -3.000   0.1557   0.00773   0.00232  -0.1188   0.8814   0.2601
  -2.750   0.1827   0.00750   0.00224  -0.1186   0.8741   0.3190
  -2.500   0.2102   0.00734   0.00217  -0.1184   0.8671   0.3674
  -2.250   0.2375   0.00725   0.00214  -0.1182   0.8594   0.4008
  -2.000   0.2652   0.00721   0.00207  -0.1180   0.8524   0.4231
  -1.750   0.2928   0.00717   0.00204  -0.1177   0.8449   0.4434
  -1.500   0.3204   0.00713   0.00201  -0.1175   0.8375   0.4664
  -1.250   0.3480   0.00711   0.00199  -0.1173   0.8294   0.4829
  -1.000   0.3756   0.00710   0.00194  -0.1170   0.8210   0.5013
  -0.750   0.4027   0.00706   0.00194  -0.1167   0.8111   0.5189
  -0.500   0.4304   0.00706   0.00191  -0.1164   0.8026   0.5323
  -0.250   0.4578   0.00705   0.00190  -0.1162   0.7934   0.5473
   0.000   0.4853   0.00704   0.00190  -0.1159   0.7837   0.5616
   0.250   0.5125   0.00703   0.00189  -0.1156   0.7733   0.5752
   0.500   0.5397   0.00703   0.00189  -0.1153   0.7616   0.5900
   0.750   0.5667   0.00703   0.00190  -0.1149   0.7490   0.6055
   1.000   0.5937   0.00704   0.00192  -0.1146   0.7366   0.6211
   1.250   0.6207   0.00705   0.00195  -0.1143   0.7241   0.6368
   1.500   0.6473   0.00707   0.00199  -0.1139   0.7096   0.6545
   1.750   0.6735   0.00709   0.00203  -0.1134   0.6938   0.6762
   2.000   0.6996   0.00711   0.00209  -0.1129   0.6779   0.7017
   2.250   0.7252   0.00712   0.00217  -0.1123   0.6621   0.7343
   2.500   0.7496   0.00710   0.00225  -0.1114   0.6450   0.7845
   2.750   0.7791   0.00684   0.00228  -0.1115   0.6244   1.0000
   3.000   0.8053   0.00703   0.00236  -0.1111   0.6027   1.0000
   3.250   0.8315   0.00723   0.00248  -0.1107   0.5843   1.0000
   3.500   0.8577   0.00742   0.00261  -0.1103   0.5673   1.0000
   3.750   0.8839   0.00762   0.00275  -0.1100   0.5489   1.0000
   4.000   0.9098   0.00783   0.00291  -0.1096   0.5299   1.0000
   4.250   0.9352   0.00808   0.00308  -0.1091   0.5097   1.0000
   4.500   0.9606   0.00832   0.00326  -0.1086   0.4871   1.0000
   4.750   0.9853   0.00861   0.00345  -0.1080   0.4611   1.0000
   5.000   1.0100   0.00891   0.00368  -0.1074   0.4354   1.0000
   5.250   1.0346   0.00922   0.00391  -0.1068   0.4099   1.0000
   5.500   1.0585   0.00959   0.00418  -0.1061   0.3808   1.0000
   5.750   1.0806   0.01011   0.00450  -0.1052   0.3375   1.0000
   6.000   1.1015   0.01076   0.00490  -0.1041   0.2876   1.0000
   6.250   1.1222   0.01144   0.00533  -0.1030   0.2397   1.0000
   6.500   1.1430   0.01213   0.00580  -0.1020   0.1977   1.0000
   6.750   1.1632   0.01286   0.00632  -0.1009   0.1577   1.0000
   7.000   1.1836   0.01357   0.00686  -0.0998   0.1255   1.0000
   7.250   1.2039   0.01426   0.00741  -0.0987   0.0984   1.0000
   7.500   1.2237   0.01499   0.00800  -0.0975   0.0729   1.0000
   7.750   1.2420   0.01584   0.00869  -0.0961   0.0480   1.0000
   8.000   1.2584   0.01688   0.00959  -0.0943   0.0287   1.0000
   8.250   1.2760   0.01774   0.01047  -0.0927   0.0229   1.0000
   8.500   1.2936   0.01857   0.01132  -0.0911   0.0201   1.0000
   8.750   1.3090   0.01952   0.01234  -0.0892   0.0183   1.0000
   9.000   1.3262   0.02025   0.01315  -0.0875   0.0171   1.0000
   9.250   1.3414   0.02106   0.01402  -0.0856   0.0162   1.0000
   9.500   1.3531   0.02195   0.01498  -0.0831   0.0155   1.0000
   9.750   1.3609   0.02308   0.01618  -0.0802   0.0149   1.0000
  10.000   1.3634   0.02460   0.01781  -0.0766   0.0143   1.0000
  10.250   1.3676   0.02613   0.01944  -0.0735   0.0139   1.0000
  10.500   1.3769   0.02731   0.02072  -0.0713   0.0137   1.0000
  10.750   1.3854   0.02861   0.02213  -0.0690   0.0135   1.0000
  11.000   1.3931   0.03005   0.02367  -0.0669   0.0132   1.0000
  11.250   1.4007   0.03156   0.02528  -0.0649   0.0128   1.0000
  11.500   1.4081   0.03312   0.02695  -0.0630   0.0125   1.0000
  11.750   1.4154   0.03470   0.02863  -0.0613   0.0121   1.0000
  12.000   1.4216   0.03642   0.03045  -0.0597   0.0117   1.0000
  12.250   1.4267   0.03837   0.03250  -0.0581   0.0115   1.0000
  12.500   1.4312   0.04042   0.03464  -0.0567   0.0112   1.0000
  12.750   1.4342   0.04276   0.03709  -0.0553   0.0110   1.0000
  13.000   1.4359   0.04543   0.03988  -0.0540   0.0108   1.0000
  13.250   1.4359   0.04857   0.04316  -0.0527   0.0106   1.0000
  13.500   1.4337   0.05219   0.04697  -0.0516   0.0105   1.0000
  13.750   1.4278   0.05644   0.05145  -0.0506   0.0104   1.0000
  14.000   1.4200   0.06069   0.05591  -0.0501   0.0103   1.0000
  14.250   1.4128   0.06441   0.05982  -0.0502   0.0103   1.0000
  14.500   1.4038   0.06875   0.06436  -0.0507   0.0102   1.0000
  14.750   1.3927   0.07357   0.06939  -0.0517   0.0102   1.0000
  15.000   1.3805   0.07885   0.07486  -0.0532   0.0102   1.0000
  15.250   1.3669   0.08466   0.08087  -0.0553   0.0102   1.0000
  15.500   1.3514   0.09113   0.08753  -0.0580   0.0102   1.0000
  15.750   1.3345   0.09823   0.09482  -0.0614   0.0102   1.0000
  16.000   1.3165   0.10594   0.10272  -0.0654   0.0102   1.0000
  16.250   1.2968   0.11441   0.11137  -0.0701   0.0103   1.0000
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