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AH 79-100 A AIRFOIL (ah79100a-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: AH 79-100 A AIRFOIL (ah79100a-il)
Reynolds number: 200,000
Max Cl/Cd: 85.54 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah79100a-il-200000.txt
Download as CSV file: xf-ah79100a-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3837   0.09213   0.08872  -0.0446   1.0000   0.0562
  -8.500  -0.3975   0.08954   0.08624  -0.0446   1.0000   0.0564
  -8.250  -0.4181   0.08765   0.08445  -0.0426   1.0000   0.0565
  -8.000  -0.4364   0.08533   0.08222  -0.0413   1.0000   0.0565
  -7.750  -0.4377   0.08200   0.07892  -0.0356   1.0000   0.0580
  -7.500  -0.4440   0.08045   0.07743  -0.0326   1.0000   0.0586
  -7.250  -0.4501   0.07885   0.07587  -0.0301   1.0000   0.0595
  -7.000  -0.4578   0.07674   0.07381  -0.0291   1.0000   0.0602
  -6.750  -0.4471   0.07286   0.06994  -0.0332   0.9976   0.0623
  -6.500  -0.4075   0.05298   0.04943  -0.0716   0.9877   0.0707
  -6.250  -0.3776   0.03781   0.03341  -0.0815   0.9830   0.0429
  -6.000  -0.3400   0.02820   0.02259  -0.0886   0.9804   0.0373
  -5.750  -0.3056   0.02527   0.01920  -0.0911   0.9765   0.0380
  -5.500  -0.2695   0.02389   0.01757  -0.0934   0.9721   0.0419
  -5.250  -0.2293   0.02209   0.01528  -0.0959   0.9693   0.0444
  -5.000  -0.1947   0.01993   0.01294  -0.0979   0.9659   0.0484
  -4.750  -0.1619   0.01900   0.01189  -0.0991   0.9607   0.0525
  -4.500  -0.1238   0.01811   0.01080  -0.1010   0.9574   0.0570
  -4.250  -0.0852   0.01684   0.00958  -0.1035   0.9550   0.0637
  -4.000  -0.0549   0.01621   0.00884  -0.1039   0.9491   0.0700
  -3.750  -0.0188   0.01541   0.00807  -0.1057   0.9448   0.0832
  -3.500   0.0211   0.01440   0.00721  -0.1085   0.9419   0.1138
  -3.250   0.0629   0.01318   0.00665  -0.1120   0.9399   0.2572
  -3.000   0.0899   0.01287   0.00664  -0.1120   0.9319   0.3570
  -2.750   0.1296   0.01272   0.00657  -0.1142   0.9283   0.4178
  -2.500   0.1704   0.01259   0.00641  -0.1165   0.9255   0.4563
  -2.250   0.1974   0.01259   0.00642  -0.1161   0.9174   0.4844
  -2.000   0.2336   0.01247   0.00632  -0.1174   0.9130   0.5121
  -1.750   0.2676   0.01235   0.00620  -0.1183   0.9079   0.5350
  -1.500   0.2965   0.01228   0.00614  -0.1181   0.9000   0.5579
  -1.250   0.3321   0.01207   0.00592  -0.1191   0.8956   0.5784
  -1.000   0.3578   0.01199   0.00587  -0.1184   0.8860   0.5949
  -0.750   0.3906   0.01178   0.00566  -0.1188   0.8808   0.6128
  -0.500   0.4163   0.01170   0.00561  -0.1181   0.8711   0.6289
  -0.250   0.4477   0.01148   0.00540  -0.1182   0.8651   0.6472
   0.000   0.4731   0.01138   0.00534  -0.1174   0.8544   0.6656
   0.250   0.5002   0.01122   0.00522  -0.1168   0.8449   0.6838
   0.500   0.5285   0.01102   0.00507  -0.1163   0.8363   0.7033
   0.750   0.5539   0.01091   0.00503  -0.1155   0.8253   0.7267
   1.000   0.5799   0.01075   0.00496  -0.1147   0.8153   0.7535
   1.250   0.6061   0.01051   0.00481  -0.1137   0.8058   0.7887
   1.500   0.6296   0.01022   0.00472  -0.1123   0.7932   0.8485
   1.750   0.6650   0.00996   0.00455  -0.1135   0.7804   1.0000
   2.000   0.6936   0.01001   0.00451  -0.1135   0.7677   1.0000
   2.250   0.7218   0.01006   0.00451  -0.1134   0.7548   1.0000
   2.500   0.7493   0.01012   0.00450  -0.1131   0.7408   1.0000
   2.750   0.7765   0.01018   0.00450  -0.1127   0.7256   1.0000
   3.000   0.8034   0.01027   0.00454  -0.1122   0.7101   1.0000
   3.250   0.8302   0.01039   0.00463  -0.1118   0.6942   1.0000
   3.500   0.8565   0.01051   0.00470  -0.1112   0.6767   1.0000
   3.750   0.8826   0.01065   0.00474  -0.1105   0.6573   1.0000
   4.000   0.9079   0.01082   0.00490  -0.1098   0.6362   1.0000
   4.250   0.9335   0.01102   0.00505  -0.1092   0.6170   1.0000
   4.500   0.9589   0.01126   0.00523  -0.1085   0.5983   1.0000
   4.750   0.9837   0.01150   0.00545  -0.1078   0.5769   1.0000
   5.000   1.0082   0.01179   0.00569  -0.1070   0.5549   1.0000
   5.250   1.0321   0.01208   0.00595  -0.1061   0.5309   1.0000
   5.500   1.0554   0.01241   0.00622  -0.1051   0.5055   1.0000
   5.750   1.0782   0.01276   0.00651  -0.1041   0.4784   1.0000
   6.000   1.1005   0.01313   0.00686  -0.1030   0.4497   1.0000
   6.250   1.1221   0.01356   0.00722  -0.1018   0.4187   1.0000
   6.500   1.1425   0.01406   0.00763  -0.1005   0.3811   1.0000
   6.750   1.1602   0.01475   0.00811  -0.0988   0.3323   1.0000
   7.000   1.1765   0.01561   0.00871  -0.0970   0.2771   1.0000
   7.250   1.1918   0.01660   0.00942  -0.0952   0.2236   1.0000
   7.500   1.2066   0.01769   0.01023  -0.0934   0.1744   1.0000
   7.750   1.2208   0.01886   0.01115  -0.0916   0.1329   1.0000
   8.000   1.2339   0.02014   0.01220  -0.0895   0.0958   1.0000
   8.250   1.2421   0.02184   0.01363  -0.0868   0.0642   1.0000
   8.500   1.2507   0.02342   0.01518  -0.0839   0.0485   1.0000
   8.750   1.2558   0.02504   0.01677  -0.0807   0.0415   1.0000
   9.000   1.2671   0.02617   0.01801  -0.0781   0.0374   1.0000
   9.250   1.2755   0.02753   0.01942  -0.0755   0.0348   1.0000
   9.500   1.2785   0.02974   0.02162  -0.0724   0.0327   1.0000
   9.750   1.2911   0.03120   0.02320  -0.0704   0.0314   1.0000
  10.000   1.3048   0.03281   0.02493  -0.0686   0.0302   1.0000
  10.250   1.3185   0.03440   0.02665  -0.0669   0.0287   1.0000
  10.500   1.3312   0.03597   0.02829  -0.0653   0.0273   1.0000
  10.750   1.3446   0.03783   0.03019  -0.0640   0.0260   1.0000
  11.250   1.3825   0.04405   0.03680  -0.0625   0.0246   1.0000
  11.500   1.3902   0.04654   0.03957  -0.0605   0.0244   1.0000
  11.750   1.3944   0.04935   0.04267  -0.0584   0.0242   1.0000
  12.000   1.3940   0.05243   0.04605  -0.0561   0.0241   1.0000
  12.250   1.3898   0.05586   0.04980  -0.0540   0.0241   1.0000
  12.500   1.3819   0.05960   0.05383  -0.0520   0.0241   1.0000
  12.750   1.3705   0.06363   0.05814  -0.0504   0.0242   1.0000
  13.000   1.3563   0.06796   0.06274  -0.0493   0.0242   1.0000
  13.250   1.3402   0.07270   0.06773  -0.0488   0.0243   1.0000
  13.500   1.3224   0.07776   0.07303  -0.0490   0.0243   1.0000
  13.750   1.3030   0.08348   0.07898  -0.0501   0.0244   1.0000
  14.000   1.2826   0.08982   0.08553  -0.0519   0.0246   1.0000
  14.250   1.2615   0.09687   0.09277  -0.0545   0.0247   1.0000
  14.500   1.2433   0.10393   0.10002  -0.0575   0.0249   1.0000
  14.750   1.2268   0.11024   0.10649  -0.0613   0.0251   1.0000
  15.000   1.2092   0.11738   0.11382  -0.0662   0.0253   1.0000
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