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AH 82-150 F (ah82150f-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: AH 82-150 F (ah82150f-il)
Reynolds number: 500,000
Max Cl/Cd: 95.65 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah82150f-il-500000.txt
Download as CSV file: xf-ah82150f-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.1312   0.08845   0.08530  -0.1253   0.8351   0.0229
 -11.000  -0.1327   0.08394   0.08080  -0.1274   0.8343   0.0230
 -10.750  -0.1358   0.07906   0.07594  -0.1299   0.8334   0.0230
  -9.500  -0.2829   0.04501   0.04161  -0.1347   0.8268   0.0153
  -9.250  -0.3051   0.04217   0.03860  -0.1295   0.8250   0.0155
  -9.000  -0.3190   0.03908   0.03529  -0.1253   0.8237   0.0155
  -8.750  -0.3312   0.03563   0.03155  -0.1210   0.8225   0.0155
  -8.500  -0.3393   0.03208   0.02765  -0.1168   0.8214   0.0153
  -8.250  -0.3416   0.02860   0.02375  -0.1129   0.8204   0.0153
  -8.000  -0.3340   0.02605   0.02082  -0.1101   0.8195   0.0155
  -7.750  -0.3197   0.02427   0.01873  -0.1083   0.8188   0.0158
  -7.500  -0.3020   0.02300   0.01720  -0.1069   0.8180   0.0162
  -7.250  -0.2858   0.02006   0.01392  -0.1055   0.8172   0.0171
  -7.000  -0.2644   0.01918   0.01296  -0.1048   0.8162   0.0179
  -6.750  -0.2420   0.01863   0.01235  -0.1043   0.8154   0.0188
  -6.500  -0.2190   0.01849   0.01216  -0.1038   0.8145   0.0205
  -6.250  -0.1956   0.01810   0.01169  -0.1033   0.8136   0.0222
  -6.000  -0.1737   0.01719   0.01068  -0.1025   0.8127   0.0239
  -5.750  -0.1528   0.01656   0.01004  -0.1017   0.8117   0.0268
  -5.500  -0.1294   0.01634   0.00979  -0.1012   0.8105   0.0297
  -5.250  -0.1051   0.01623   0.00962  -0.1008   0.8096   0.0321
  -5.000  -0.0854   0.01561   0.00897  -0.0997   0.8087   0.0365
  -4.750  -0.0614   0.01549   0.00884  -0.0993   0.8079   0.0406
  -4.500  -0.0363   0.01544   0.00874  -0.0991   0.8070   0.0438
  -4.250  -0.0158   0.01492   0.00820  -0.0980   0.8060   0.0491
  -4.000   0.0082   0.01478   0.00803  -0.0976   0.8052   0.0540
  -3.750   0.0317   0.01463   0.00783  -0.0971   0.8044   0.0599
  -3.500   0.0535   0.01456   0.00778  -0.0963   0.8032   0.0683
  -3.250   0.0712   0.01452   0.00782  -0.0949   0.8010   0.0821
  -3.000   0.0875   0.01422   0.00783  -0.0933   0.7987   0.1480
  -2.750   0.0998   0.01346   0.00778  -0.0912   0.7966   0.3328
  -2.500   0.1129   0.01262   0.00763  -0.0890   0.7948   0.5223
  -2.250   0.1223   0.01200   0.00801  -0.0849   0.7934   0.7704
  -2.000   0.1495   0.01225   0.00821  -0.0847   0.7924   0.8191
  -1.750   0.1760   0.01259   0.00851  -0.0840   0.7914   0.8365
  -1.500   0.2032   0.01285   0.00868  -0.0837   0.7905   0.8478
  -1.250   0.2150   0.01347   0.00935  -0.0806   0.7864   0.8548
  -1.000   0.2320   0.01390   0.00979  -0.0782   0.7833   0.8653
  -0.750   0.2501   0.01433   0.01022  -0.0752   0.7813   0.8795
  -0.500   0.2717   0.01458   0.01045  -0.0728   0.7800   0.8924
  -0.250   0.3015   0.01456   0.01038  -0.0728   0.7789   0.8981
   0.000   0.3320   0.01441   0.01017  -0.0735   0.7777   0.9028
   0.250   0.3634   0.01432   0.01003  -0.0737   0.7767   0.9063
   0.500   0.3641   0.01478   0.01054  -0.0684   0.7708   0.9167
   0.750   0.3990   0.01475   0.01050  -0.0693   0.7689   0.9221
   1.000   0.4316   0.01460   0.01032  -0.0703   0.7673   0.9257
   1.250   0.4568   0.01439   0.01008  -0.0699   0.7656   0.9289
   1.500   0.4855   0.01414   0.00980  -0.0703   0.7643   0.9305
   1.750   0.5195   0.01388   0.00951  -0.0718   0.7632   0.9310
   2.000   0.5532   0.01369   0.00929  -0.0732   0.7621   0.9313
   2.250   0.5564   0.01380   0.00948  -0.0688   0.7558   0.9336
   2.500   0.5851   0.01357   0.00925  -0.0693   0.7535   0.9342
   2.750   0.6167   0.01332   0.00899  -0.0703   0.7518   0.9346
   3.000   0.6508   0.01305   0.00872  -0.0718   0.7504   0.9351
   3.250   0.6859   0.01279   0.00845  -0.0735   0.7491   0.9352
   3.500   0.6968   0.01278   0.00850  -0.0706   0.7439   0.9368
   3.750   0.7216   0.01257   0.00833  -0.0703   0.7404   0.9375
   4.000   0.7540   0.01230   0.00808  -0.0715   0.7382   0.9380
   4.250   0.7891   0.01199   0.00777  -0.0732   0.7363   0.9383
   4.500   0.8139   0.01180   0.00764  -0.0729   0.7326   0.9389
   4.750   0.8325   0.01165   0.00755  -0.0714   0.7271   0.9399
   5.000   0.8641   0.01135   0.00730  -0.0724   0.7239   0.9402
   5.250   0.8881   0.01102   0.00701  -0.0719   0.7175   0.9409
   5.500   0.9146   0.01048   0.00649  -0.0716   0.7085   0.9415
   5.750   0.9254   0.01023   0.00630  -0.0684   0.6957   0.9432
   6.000   0.9354   0.01001   0.00613  -0.0650   0.6816   0.9445
   6.250   0.9412   0.00984   0.00593  -0.0607   0.6553   0.9462
   6.500   0.9492   0.00993   0.00582  -0.0571   0.6157   0.9478
   6.750   0.9466   0.01050   0.00617  -0.0518   0.5737   0.9502
   7.000   0.9376   0.01141   0.00686  -0.0458   0.5305   0.9536
   7.250   0.9278   0.01259   0.00780  -0.0403   0.4856   0.9564
   7.500   0.9166   0.01398   0.00893  -0.0348   0.4330   0.9595
   7.750   0.9113   0.01531   0.01001  -0.0306   0.3840   0.9626
   8.000   0.9013   0.01702   0.01133  -0.0259   0.3112   0.9663
   8.250   0.8842   0.01932   0.01295  -0.0207   0.1943   0.9703
   8.500   0.8691   0.02209   0.01493  -0.0166   0.0558   0.9742
   8.750   0.8781   0.02362   0.01629  -0.0153   0.0200   0.9773
   9.000   0.8974   0.02452   0.01728  -0.0153   0.0169   0.9799
   9.250   0.9158   0.02548   0.01831  -0.0152   0.0152   0.9826
   9.500   0.9305   0.02666   0.01958  -0.0148   0.0140   0.9895
   9.750   0.9368   0.02822   0.02124  -0.0130   0.0130   1.0000
  10.000   0.9441   0.02968   0.02280  -0.0114   0.0126   1.0000
  10.250   0.9538   0.03104   0.02423  -0.0102   0.0123   1.0000
  10.500   0.9649   0.03233   0.02559  -0.0091   0.0119   1.0000
  10.750   0.9772   0.03354   0.02687  -0.0083   0.0110   1.0000
  11.000   0.9868   0.03498   0.02837  -0.0072   0.0104   1.0000
  11.250   0.9953   0.03656   0.03002  -0.0060   0.0102   1.0000
  11.500   1.0047   0.03809   0.03161  -0.0050   0.0097   1.0000
  11.750   1.0150   0.03959   0.03315  -0.0041   0.0094   1.0000
  12.000   1.0258   0.04111   0.03473  -0.0030   0.0093   1.0000
  12.250   1.0391   0.04255   0.03621  -0.0021   0.0090   1.0000
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