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AH 83-159 (ah83159-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: AH 83-159 (ah83159-il)
Reynolds number: 200,000
Max Cl/Cd: 63.46 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah83159-il-200000-n5.txt
Download as CSV file: xf-ah83159-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 83-159                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.1916   0.09033   0.08591  -0.0948   0.7952   0.0144
 -10.750  -0.1949   0.08557   0.08117  -0.0971   0.7923   0.0144
 -10.500  -0.1993   0.08069   0.07631  -0.0995   0.7896   0.0143
 -10.250  -0.2080   0.07467   0.07030  -0.1030   0.7871   0.0145
 -10.000  -0.2199   0.06786   0.06349  -0.1079   0.7845   0.0140
  -9.750  -0.2436   0.06078   0.05636  -0.1120   0.7807   0.0135
  -9.500  -0.2641   0.05611   0.05158  -0.1127   0.7770   0.0138
  -9.250  -0.2840   0.05229   0.04761  -0.1116   0.7736   0.0135
  -9.000  -0.3034   0.04910   0.04424  -0.1088   0.7708   0.0135
  -8.750  -0.3176   0.04610   0.04105  -0.1059   0.7675   0.0137
  -8.500  -0.3242   0.04300   0.03771  -0.1034   0.7643   0.0139
  -8.250  -0.3273   0.03976   0.03414  -0.1009   0.7615   0.0142
  -8.000  -0.3253   0.03672   0.03074  -0.0985   0.7590   0.0142
  -7.750  -0.3193   0.03373   0.02734  -0.0963   0.7568   0.0141
  -7.500  -0.3087   0.03111   0.02433  -0.0945   0.7542   0.0141
  -7.250  -0.2940   0.02883   0.02169  -0.0930   0.7513   0.0142
  -7.000  -0.2758   0.02681   0.01930  -0.0918   0.7488   0.0144
  -6.750  -0.2548   0.02508   0.01725  -0.0909   0.7466   0.0146
  -6.500  -0.2318   0.02366   0.01553  -0.0903   0.7446   0.0149
  -6.250  -0.2076   0.02243   0.01407  -0.0897   0.7428   0.0153
  -6.000  -0.1837   0.02127   0.01276  -0.0892   0.7410   0.0159
  -5.750  -0.1613   0.02041   0.01188  -0.0887   0.7381   0.0166
  -5.500  -0.1383   0.01977   0.01121  -0.0882   0.7355   0.0175
  -5.250  -0.1146   0.01926   0.01063  -0.0878   0.7333   0.0194
  -5.000  -0.0905   0.01879   0.01004  -0.0873   0.7312   0.0210
  -4.750  -0.0688   0.01804   0.00928  -0.0866   0.7294   0.0230
  -4.500  -0.0453   0.01752   0.00870  -0.0861   0.7276   0.0254
  -4.250  -0.0224   0.01709   0.00820  -0.0855   0.7252   0.0287
  -4.000   0.0003   0.01672   0.00783  -0.0850   0.7225   0.0355
  -3.750   0.0235   0.01633   0.00745  -0.0845   0.7202   0.0454
  -3.500   0.0471   0.01593   0.00711  -0.0841   0.7180   0.0650
  -3.250   0.0698   0.01539   0.00679  -0.0837   0.7160   0.1196
  -3.000   0.0896   0.01449   0.00645  -0.0832   0.7141   0.2609
  -2.750   0.1060   0.01329   0.00614  -0.0821   0.7125   0.4839
  -2.500   0.1169   0.01323   0.00704  -0.0777   0.7097   0.6844
  -2.250   0.1386   0.01384   0.00771  -0.0755   0.7071   0.7468
  -2.000   0.1633   0.01434   0.00812  -0.0744   0.7046   0.7786
  -1.750   0.1872   0.01490   0.00858  -0.0730   0.7025   0.8010
  -1.500   0.2109   0.01537   0.00896  -0.0716   0.7007   0.8186
  -1.250   0.2350   0.01567   0.00919  -0.0700   0.6992   0.8270
  -1.000   0.2599   0.01581   0.00923  -0.0695   0.6972   0.8349
  -0.750   0.2819   0.01598   0.00939  -0.0684   0.6940   0.8399
  -0.500   0.3066   0.01606   0.00940  -0.0682   0.6914   0.8462
  -0.250   0.3316   0.01608   0.00936  -0.0678   0.6891   0.8493
   0.000   0.3578   0.01607   0.00928  -0.0675   0.6871   0.8522
   0.250   0.3852   0.01603   0.00917  -0.0677   0.6853   0.8553
   0.500   0.4138   0.01600   0.00905  -0.0682   0.6838   0.8585
   0.750   0.4361   0.01613   0.00919  -0.0678   0.6803   0.8617
   1.000   0.4595   0.01618   0.00924  -0.0672   0.6773   0.8637
   1.250   0.4849   0.01619   0.00923  -0.0671   0.6748   0.8659
   1.500   0.5119   0.01617   0.00918  -0.0673   0.6727   0.8681
   1.750   0.5405   0.01613   0.00909  -0.0677   0.6708   0.8703
   2.000   0.5696   0.01611   0.00903  -0.0684   0.6690   0.8724
   2.250   0.5908   0.01632   0.00930  -0.0679   0.6648   0.8749
   2.500   0.6144   0.01636   0.00936  -0.0674   0.6616   0.8766
   2.750   0.6409   0.01634   0.00934  -0.0675   0.6590   0.8780
   3.000   0.6695   0.01628   0.00927  -0.0679   0.6568   0.8795
   3.250   0.6985   0.01622   0.00920  -0.0684   0.6546   0.8811
   3.500   0.7169   0.01646   0.00953  -0.0673   0.6496   0.8834
   3.750   0.7428   0.01649   0.00959  -0.0674   0.6460   0.8849
   4.000   0.7722   0.01643   0.00954  -0.0681   0.6432   0.8864
   4.250   0.8043   0.01632   0.00942  -0.0692   0.6408   0.8878
   4.500   0.8197   0.01656   0.00977  -0.0675   0.6347   0.8897
   4.750   0.8452   0.01652   0.00977  -0.0674   0.6305   0.8908
   5.000   0.8753   0.01638   0.00966  -0.0680   0.6274   0.8918
   5.250   0.8935   0.01656   0.00995  -0.0668   0.6220   0.8936
   5.500   0.9161   0.01663   0.01008  -0.0663   0.6172   0.8954
   5.750   0.9454   0.01653   0.01003  -0.0668   0.6135   0.8967
   6.000   0.9640   0.01672   0.01032  -0.0657   0.6076   0.8983
   6.250   0.9869   0.01679   0.01046  -0.0653   0.6020   0.8997
   6.500   1.0183   0.01665   0.01036  -0.0662   0.5980   0.9007
   6.750   1.0282   0.01698   0.01085  -0.0637   0.5899   0.9028
   7.000   1.0554   0.01684   0.01075  -0.0637   0.5843   0.9040
   7.250   1.0617   0.01713   0.01116  -0.0604   0.5751   0.9060
   7.500   1.0812   0.01713   0.01122  -0.0593   0.5669   0.9075
   7.750   1.0960   0.01727   0.01143  -0.0574   0.5567   0.9092
   8.000   1.1048   0.01765   0.01189  -0.0548   0.5445   0.9117
   8.250   1.1170   0.01799   0.01227  -0.0528   0.5303   0.9138
   8.500   1.1315   0.01831   0.01260  -0.0512   0.5140   0.9154
   8.750   1.1421   0.01879   0.01309  -0.0492   0.4946   0.9171
   9.000   1.1522   0.01935   0.01359  -0.0471   0.4715   0.9188
   9.250   1.1585   0.02015   0.01431  -0.0446   0.4435   0.9209
   9.500   1.1602   0.02125   0.01526  -0.0418   0.4124   0.9235
   9.750   1.1588   0.02265   0.01650  -0.0389   0.3804   0.9259
  10.000   1.1574   0.02421   0.01792  -0.0363   0.3505   0.9279
  10.750   1.1558   0.02933   0.02275  -0.0299   0.2692   0.9338
  11.000   1.1547   0.03127   0.02459  -0.0281   0.2410   0.9364
  11.250   1.1531   0.03339   0.02659  -0.0265   0.2114   0.9390
  11.500   1.1519   0.03562   0.02869  -0.0251   0.1824   0.9415
  12.000   1.1505   0.04041   0.03323  -0.0230   0.1249   0.9463
  12.250   1.1509   0.04287   0.03556  -0.0223   0.0994   0.9493
  12.500   1.1524   0.04533   0.03791  -0.0217   0.0774   0.9528
  13.000   1.1584   0.05006   0.04255  -0.0211   0.0470   0.9674
  13.500   1.1633   0.05465   0.04713  -0.0199   0.0314   1.0000
  13.750   1.1679   0.05702   0.04955  -0.0197   0.0261   1.0000
  14.000   1.1718   0.05954   0.05214  -0.0196   0.0225   1.0000
  14.250   1.1759   0.06209   0.05479  -0.0195   0.0195   1.0000
  14.500   1.1773   0.06502   0.05778  -0.0195   0.0172   1.0000
  14.750   1.1806   0.06778   0.06067  -0.0196   0.0154   1.0000
  15.000   1.1833   0.07066   0.06364  -0.0199   0.0139   1.0000
  15.250   1.1833   0.07393   0.06698  -0.0202   0.0124   1.0000
  15.500   1.1853   0.07704   0.07023  -0.0206   0.0117   1.0000
  15.750   1.1876   0.08015   0.07346  -0.0211   0.0107   1.0000
  16.000   1.1888   0.08345   0.07688  -0.0218   0.0102   1.0000
  16.250   1.1878   0.08712   0.08064  -0.0226   0.0096   1.0000
  16.500   1.1857   0.09101   0.08464  -0.0235   0.0093   1.0000
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