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AH 82-150 A (ah82150a-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: AH 82-150 A (ah82150a-il)
Reynolds number: 100,000
Max Cl/Cd: 41.88 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah82150a-il-100000-n5.txt
Download as CSV file: xf-ah82150a-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 82-150 A                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2900   0.08993   0.08514  -0.0869   0.9498   0.0301
 -10.500  -0.2878   0.08274   0.07794  -0.0937   0.9437   0.0299
 -10.250  -0.2937   0.07333   0.06849  -0.1029   0.9351   0.0297
 -10.000  -0.3076   0.06463   0.05963  -0.1115   0.9260   0.0295
  -9.750  -0.3229   0.05884   0.05364  -0.1158   0.9153   0.0293
  -9.500  -0.3402   0.05470   0.04930  -0.1167   0.9039   0.0295
  -9.250  -0.3565   0.05150   0.04585  -0.1154   0.8943   0.0298
  -9.000  -0.3673   0.04808   0.04206  -0.1139   0.8862   0.0304
  -8.750  -0.3744   0.04506   0.03860  -0.1117   0.8783   0.0311
  -8.500  -0.3743   0.04210   0.03511  -0.1099   0.8722   0.0318
  -8.250  -0.3700   0.03930   0.03191  -0.1082   0.8666   0.0324
  -8.000  -0.3596   0.03704   0.02941  -0.1069   0.8613   0.0332
  -7.750  -0.3434   0.03513   0.02724  -0.1062   0.8573   0.0342
  -7.500  -0.3270   0.03379   0.02569  -0.1052   0.8527   0.0360
  -7.250  -0.3106   0.03256   0.02419  -0.1041   0.8478   0.0385
  -7.000  -0.2900   0.03089   0.02210  -0.1033   0.8442   0.0407
  -6.750  -0.2657   0.02933   0.02011  -0.1028   0.8415   0.0423
  -6.500  -0.2468   0.02793   0.01867  -0.1019   0.8369   0.0446
  -6.250  -0.2257   0.02718   0.01785  -0.1012   0.8327   0.0479
  -6.000  -0.2008   0.02622   0.01669  -0.1008   0.8295   0.0513
  -5.750  -0.1741   0.02527   0.01554  -0.1006   0.8271   0.0540
  -5.500  -0.1555   0.02451   0.01483  -0.0994   0.8229   0.0578
  -5.250  -0.1355   0.02400   0.01427  -0.0984   0.8186   0.0625
  -5.000  -0.1126   0.02338   0.01354  -0.0977   0.8154   0.0665
  -4.750  -0.0897   0.02268   0.01283  -0.0971   0.8128   0.0714
  -4.500  -0.0713   0.02239   0.01250  -0.0958   0.8087   0.0793
  -4.250  -0.0536   0.02202   0.01216  -0.0944   0.8043   0.0876
  -4.000  -0.0318   0.02158   0.01169  -0.0936   0.8010   0.1002
  -3.750  -0.0089   0.02101   0.01128  -0.0931   0.7985   0.1327
  -3.500   0.0059   0.02039   0.01113  -0.0915   0.7945   0.2222
  -3.250   0.0150   0.01944   0.01098  -0.0894   0.7895   0.3937
  -3.000   0.0229   0.01978   0.01245  -0.0831   0.7863   0.6442
  -2.750   0.0491   0.02013   0.01258  -0.0827   0.7839   0.7054
  -2.500   0.0662   0.02077   0.01312  -0.0801   0.7799   0.7349
  -2.250   0.0776   0.02160   0.01393  -0.0758   0.7749   0.7635
  -2.000   0.0924   0.02230   0.01460  -0.0714   0.7718   0.7913
  -1.750   0.1111   0.02271   0.01490  -0.0681   0.7695   0.8146
  -1.500   0.1241   0.02306   0.01520  -0.0647   0.7650   0.8280
  -1.250   0.1381   0.02328   0.01536  -0.0621   0.7600   0.8362
  -1.000   0.1628   0.02322   0.01517  -0.0619   0.7571   0.8409
  -0.750   0.1915   0.02308   0.01488  -0.0626   0.7549   0.8445
  -0.500   0.2053   0.02329   0.01504  -0.0606   0.7495   0.8475
  -0.250   0.2241   0.02340   0.01508  -0.0595   0.7448   0.8506
   0.000   0.2521   0.02331   0.01490  -0.0599   0.7421   0.8531
   0.250   0.2837   0.02317   0.01465  -0.0609   0.7400   0.8554
   0.500   0.2923   0.02358   0.01505  -0.0587   0.7328   0.8589
   0.750   0.3174   0.02358   0.01499  -0.0585   0.7291   0.8607
   1.000   0.3481   0.02345   0.01480  -0.0593   0.7267   0.8624
   1.250   0.3819   0.02326   0.01456  -0.0605   0.7248   0.8639
   1.500   0.3853   0.02384   0.01517  -0.0574   0.7158   0.8671
   1.750   0.4166   0.02373   0.01502  -0.0583   0.7130   0.8690
   2.000   0.4517   0.02352   0.01476  -0.0598   0.7110   0.8707
   2.250   0.4575   0.02411   0.01540  -0.0571   0.7020   0.8737
   2.500   0.4884   0.02396   0.01525  -0.0578   0.6989   0.8750
   2.750   0.5235   0.02371   0.01498  -0.0591   0.6968   0.8762
   3.000   0.5278   0.02433   0.01566  -0.0560   0.6875   0.8798
   3.250   0.5603   0.02415   0.01549  -0.0570   0.6844   0.8817
   3.500   0.5971   0.02386   0.01523  -0.0586   0.6823   0.8832
   3.750   0.6019   0.02457   0.01601  -0.0559   0.6724   0.8865
   4.000   0.6364   0.02432   0.01579  -0.0571   0.6696   0.8879
   4.250   0.6699   0.02408   0.01562  -0.0581   0.6667   0.8895
   4.500   0.6728   0.02469   0.01632  -0.0547   0.6568   0.8934
   4.750   0.7104   0.02433   0.01602  -0.0563   0.6543   0.8954
   5.250   0.7497   0.02467   0.01653  -0.0545   0.6408   0.9017
   5.750   0.7898   0.02493   0.01701  -0.0526   0.6271   0.9081
   6.250   0.8335   0.02516   0.01747  -0.0515   0.6131   0.9158
   6.750   0.8778   0.02525   0.01785  -0.0501   0.5985   0.9255
   7.250   0.9279   0.02512   0.01802  -0.0496   0.5830   0.9367
   7.500   0.9418   0.02569   0.01879  -0.0484   0.5714   0.9464
   7.750   0.9656   0.02590   0.01917  -0.0484   0.5610   0.9583
   8.250   1.0276   0.02527   0.01888  -0.0496   0.5399   1.0000
   8.500   1.0437   0.02535   0.01899  -0.0482   0.5129   1.0000
   8.750   1.0588   0.02528   0.01874  -0.0463   0.4652   1.0000
   9.000   1.0686   0.02592   0.01902  -0.0442   0.4083   1.0000
   9.250   1.0679   0.02750   0.02020  -0.0416   0.3467   1.0000
   9.500   1.0621   0.02966   0.02193  -0.0390   0.2820   1.0000
   9.750   1.0532   0.03226   0.02406  -0.0365   0.2124   1.0000
  10.000   1.0429   0.03521   0.02649  -0.0342   0.1406   1.0000
  10.500   1.0311   0.04095   0.03146  -0.0307   0.0455   1.0000
  10.750   1.0334   0.04327   0.03373  -0.0296   0.0353   1.0000
  11.000   1.0364   0.04560   0.03607  -0.0287   0.0313   1.0000
  11.250   1.0422   0.04772   0.03838  -0.0279   0.0291   1.0000
  11.500   1.0463   0.05003   0.04084  -0.0273   0.0273   1.0000
  11.750   1.0495   0.05250   0.04343  -0.0267   0.0259   1.0000
  12.000   1.0513   0.05515   0.04620  -0.0261   0.0248   1.0000
  12.250   1.0517   0.05800   0.04915  -0.0256   0.0240   1.0000
  12.500   1.0551   0.06058   0.05184  -0.0251   0.0231   1.0000
  12.750   1.0617   0.06288   0.05428  -0.0248   0.0218   1.0000
  13.000   1.0685   0.06518   0.05670  -0.0245   0.0207   1.0000
  13.250   1.0758   0.06745   0.05907  -0.0242   0.0197   1.0000
  13.500   1.0847   0.06958   0.06132  -0.0238   0.0191   1.0000
  13.750   1.0955   0.07157   0.06339  -0.0234   0.0185   1.0000
  14.000   1.1077   0.07348   0.06537  -0.0229   0.0180   1.0000
  14.250   1.1234   0.07524   0.06718  -0.0223   0.0175   1.0000
  14.500   1.1422   0.07713   0.06916  -0.0215   0.0171   1.0000
  14.750   1.1518   0.07981   0.07208  -0.0214   0.0169   1.0000
  15.000   1.1569   0.08295   0.07549  -0.0214   0.0167   1.0000
  15.250   1.1577   0.08655   0.07937  -0.0217   0.0164   1.0000
  15.500   1.1551   0.09058   0.08368  -0.0223   0.0161   1.0000
  15.750   1.1502   0.09494   0.08831  -0.0233   0.0158   1.0000
  16.000   1.1430   0.09970   0.09334  -0.0246   0.0156   1.0000
  16.250   1.1339   0.10485   0.09876  -0.0264   0.0153   1.0000
  16.500   1.1234   0.11039   0.10455  -0.0286   0.0152   1.0000
  16.750   1.1113   0.11639   0.11079  -0.0313   0.0151   1.0000
  17.000   1.0977   0.12293   0.11757  -0.0347   0.0150   1.0000
  17.250   1.0829   0.13004   0.12490  -0.0387   0.0150   1.0000
  17.500   1.0664   0.13789   0.13297  -0.0434   0.0151   1.0000
  17.750   1.0490   0.14642   0.14169  -0.0488   0.0152   1.0000
  18.000   1.0299   0.15606   0.15152  -0.0551   0.0154   1.0000
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