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AH 82-150 F (ah82150f-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: AH 82-150 F (ah82150f-il)
Reynolds number: 1,000,000
Max Cl/Cd: 135.58 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah82150f-il-1000000.txt
Download as CSV file: xf-ah82150f-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 82-150 F                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.3637   0.05093   0.04826  -0.1371   0.8034   0.0076
 -12.000  -0.3978   0.04373   0.04090  -0.1408   0.8024   0.0076
 -11.750  -0.4112   0.04058   0.03763  -0.1404   0.8014   0.0075
 -11.500  -0.4160   0.03854   0.03551  -0.1392   0.8005   0.0074
 -11.250  -0.4287   0.03608   0.03292  -0.1369   0.7995   0.0074
 -11.000  -0.4475   0.03331   0.02996  -0.1333   0.7983   0.0074
 -10.750  -0.4746   0.03006   0.02644  -0.1277   0.7971   0.0074
 -10.500  -0.5016   0.02702   0.02308  -0.1209   0.7958   0.0075
 -10.250  -0.5167   0.02404   0.01972  -0.1153   0.7948   0.0076
 -10.000  -0.5150   0.02187   0.01725  -0.1120   0.7940   0.0077
  -9.750  -0.5067   0.02010   0.01524  -0.1095   0.7932   0.0079
  -9.500  -0.4920   0.01893   0.01389  -0.1079   0.7925   0.0081
  -9.250  -0.4732   0.01827   0.01315  -0.1069   0.7917   0.0085
  -9.000  -0.4533   0.01764   0.01242  -0.1060   0.7908   0.0087
  -8.750  -0.4321   0.01724   0.01195  -0.1053   0.7898   0.0091
  -8.500  -0.4104   0.01670   0.01134  -0.1047   0.7894   0.0095
  -8.250  -0.3881   0.01617   0.01074  -0.1041   0.7889   0.0100
  -8.000  -0.3657   0.01561   0.01008  -0.1035   0.7884   0.0105
  -7.750  -0.3430   0.01506   0.00944  -0.1029   0.7879   0.0108
  -7.500  -0.3191   0.01471   0.00903  -0.1025   0.7873   0.0110
  -7.250  -0.3018   0.01347   0.00763  -0.1010   0.7867   0.0118
  -7.000  -0.2799   0.01293   0.00705  -0.1003   0.7860   0.0127
  -6.750  -0.2561   0.01261   0.00670  -0.0998   0.7854   0.0134
  -6.500  -0.2315   0.01237   0.00644  -0.0996   0.7848   0.0145
  -6.250  -0.2064   0.01216   0.00619  -0.0994   0.7841   0.0157
  -6.000  -0.1841   0.01167   0.00566  -0.0986   0.7833   0.0183
  -5.750  -0.1583   0.01153   0.00554  -0.0986   0.7826   0.0209
  -5.500  -0.1318   0.01145   0.00545  -0.0986   0.7819   0.0227
  -5.250  -0.1084   0.01107   0.00503  -0.0981   0.7813   0.0262
  -5.000  -0.0826   0.01092   0.00488  -0.0980   0.7807   0.0292
  -4.750  -0.0561   0.01082   0.00477  -0.0981   0.7801   0.0315
  -4.500  -0.0301   0.01067   0.00459  -0.0980   0.7795   0.0335
  -4.250  -0.0050   0.01045   0.00438  -0.0979   0.7789   0.0393
  -4.000   0.0217   0.01036   0.00428  -0.0980   0.7782   0.0429
  -3.750   0.0478   0.01023   0.00411  -0.0979   0.7775   0.0471
  -3.500   0.0735   0.01012   0.00403  -0.0978   0.7768   0.0548
  -3.250   0.0988   0.01006   0.00400  -0.0977   0.7759   0.0662
  -3.000   0.1237   0.00982   0.00388  -0.0975   0.7753   0.0956
  -2.750   0.1456   0.00937   0.00375  -0.0968   0.7746   0.1849
  -2.500   0.1656   0.00880   0.00365  -0.0959   0.7736   0.3172
  -2.250   0.1863   0.00827   0.00354  -0.0951   0.7722   0.4411
  -2.000   0.2055   0.00759   0.00339  -0.0940   0.7706   0.5947
  -1.750   0.2237   0.00705   0.00351  -0.0922   0.7691   0.7855
  -1.500   0.2520   0.00716   0.00361  -0.0924   0.7678   0.8139
  -1.250   0.2808   0.00724   0.00366  -0.0927   0.7665   0.8243
  -1.000   0.3104   0.00730   0.00365  -0.0932   0.7652   0.8324
  -0.750   0.3385   0.00753   0.00388  -0.0930   0.7636   0.8437
  -0.500   0.3645   0.00791   0.00427  -0.0923   0.7617   0.8544
  -0.250   0.3919   0.00798   0.00434  -0.0924   0.7600   0.8604
   0.000   0.4189   0.00796   0.00432  -0.0923   0.7581   0.8627
   0.250   0.4460   0.00799   0.00436  -0.0923   0.7563   0.8650
   0.500   0.4736   0.00802   0.00439  -0.0924   0.7546   0.8675
   0.750   0.5014   0.00813   0.00448  -0.0924   0.7531   0.8730
   1.000   0.5268   0.00821   0.00457  -0.0917   0.7515   0.8784
   1.250   0.5533   0.00831   0.00467  -0.0913   0.7501   0.8826
   1.500   0.5826   0.00835   0.00469  -0.0919   0.7484   0.8844
   1.750   0.6099   0.00829   0.00465  -0.0922   0.7466   0.8854
   2.000   0.6377   0.00822   0.00460  -0.0926   0.7444   0.8861
   2.250   0.6664   0.00815   0.00454  -0.0931   0.7421   0.8870
   2.500   0.6959   0.00807   0.00447  -0.0939   0.7399   0.8875
   2.750   0.7259   0.00799   0.00438  -0.0947   0.7379   0.8880
   3.000   0.7562   0.00792   0.00430  -0.0956   0.7359   0.8883
   3.250   0.7845   0.00788   0.00429  -0.0961   0.7333   0.8888
   3.500   0.8105   0.00777   0.00423  -0.0960   0.7299   0.8895
   3.750   0.8382   0.00766   0.00415  -0.0963   0.7266   0.8900
   4.000   0.8668   0.00755   0.00405  -0.0968   0.7235   0.8904
   4.250   0.8921   0.00740   0.00394  -0.0965   0.7160   0.8909
   4.500   0.9187   0.00727   0.00384  -0.0966   0.7092   0.8913
   4.750   0.9430   0.00718   0.00378  -0.0961   0.6972   0.8918
   5.000   0.9653   0.00712   0.00370  -0.0952   0.6757   0.8924
   5.250   0.9753   0.00732   0.00370  -0.0917   0.6295   0.8936
   5.500   0.9731   0.00783   0.00397  -0.0859   0.5816   0.8952
   5.750   0.9654   0.00829   0.00428  -0.0789   0.5451   0.8969
   6.000   0.9572   0.00899   0.00482  -0.0723   0.5080   0.8987
   6.250   0.9467   0.00993   0.00556  -0.0658   0.4664   0.9005
   6.500   0.9378   0.01103   0.00645  -0.0599   0.4214   0.9020
   6.750   0.9307   0.01219   0.00737  -0.0546   0.3735   0.9036
   7.000   0.9260   0.01335   0.00827  -0.0499   0.3214   0.9051
   7.250   0.9147   0.01489   0.00940  -0.0443   0.2462   0.9066
   7.500   0.8922   0.01708   0.01095  -0.0374   0.1278   0.9084
   7.750   0.8807   0.01899   0.01235  -0.0323   0.0300   0.9098
   8.000   0.8916   0.01986   0.01315  -0.0304   0.0136   0.9106
   8.250   0.9085   0.02042   0.01375  -0.0294   0.0119   0.9114
   8.500   0.9250   0.02101   0.01439  -0.0283   0.0110   0.9121
   8.750   0.9405   0.02167   0.01508  -0.0272   0.0102   0.9129
   9.000   0.9537   0.02249   0.01595  -0.0257   0.0092   0.9137
   9.250   0.9645   0.02348   0.01701  -0.0240   0.0082   0.9147
   9.500   0.9780   0.02430   0.01789  -0.0227   0.0080   0.9155
   9.750   0.9936   0.02502   0.01864  -0.0217   0.0075   0.9162
  10.000   1.0057   0.02597   0.01965  -0.0203   0.0071   0.9170
  10.250   1.0162   0.02703   0.02079  -0.0188   0.0069   0.9181
  10.500   1.0288   0.02796   0.02177  -0.0176   0.0066   0.9192
  10.750   1.0399   0.02900   0.02286  -0.0163   0.0062   0.9202
  11.000   1.0476   0.03032   0.02423  -0.0146   0.0059   0.9214
  11.250   1.0539   0.03179   0.02577  -0.0129   0.0058   0.9225
  11.500   1.0461   0.03440   0.02850  -0.0098   0.0054   0.9236
  11.750   1.0558   0.03575   0.02992  -0.0085   0.0052   0.9247
  12.000   1.0652   0.03717   0.03141  -0.0073   0.0052   0.9258
  12.250   1.0775   0.03838   0.03269  -0.0065   0.0050   0.9269
  12.500   1.0893   0.03967   0.03405  -0.0056   0.0047   0.9280
  12.750   1.0988   0.04123   0.03571  -0.0046   0.0046   0.9289
  13.000   1.1097   0.04278   0.03734  -0.0037   0.0046   0.9297
  13.250   1.1227   0.04435   0.03902  -0.0028   0.0045   0.9302
  13.500   1.1365   0.04592   0.04070  -0.0021   0.0044   0.9311
  13.750   1.1523   0.04762   0.04254  -0.0015   0.0045   0.9316
  14.000   1.1712   0.05012   0.04526  -0.0011   0.0047   0.9312
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