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AH 82-150 F (ah82150f-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: AH 82-150 F (ah82150f-il)
Reynolds number: 200,000
Max Cl/Cd: 58.22 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah82150f-il-200000.txt
Download as CSV file: xf-ah82150f-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.1230   0.11872   0.11477  -0.1216   0.9230   0.0422
 -12.750  -0.1263   0.11576   0.11183  -0.1249   0.9211   0.0433
 -12.500  -0.1295   0.11256   0.10866  -0.1281   0.9190   0.0437
 -12.250  -0.1281   0.10906   0.10515  -0.1303   0.9173   0.0439
 -12.000  -0.1275   0.10531   0.10141  -0.1327   0.9157   0.0440
 -11.750  -0.1194   0.09966   0.09577  -0.1319   0.9151   0.0454
 -11.500  -0.1081   0.09716   0.09326  -0.1317   0.9141   0.0466
 -11.250  -0.1026   0.09443   0.09052  -0.1324   0.9129   0.0475
 -11.000  -0.0988   0.09157   0.08767  -0.1333   0.9115   0.0491
 -10.750  -0.0979   0.08838   0.08450  -0.1347   0.9101   0.0506
 -10.500  -0.0990   0.08501   0.08116  -0.1364   0.9086   0.0520
 -10.250  -0.1085   0.08068   0.07688  -0.1398   0.9069   0.0549
 -10.000  -0.1233   0.07542   0.07166  -0.1452   0.9046   0.0558
  -9.750  -0.1447   0.07076   0.06696  -0.1488   0.9021   0.0560
  -9.500  -0.1683   0.06816   0.06429  -0.1485   0.9001   0.0563
  -9.250  -0.1984   0.06720   0.06327  -0.1448   0.8974   0.0565
  -9.000  -0.2214   0.06660   0.06261  -0.1401   0.8949   0.0566
  -8.750  -0.2433   0.06608   0.06198  -0.1351   0.8921   0.0567
  -8.500  -0.2630   0.06553   0.06130  -0.1299   0.8901   0.0568
  -8.250  -0.2799   0.06471   0.06033  -0.1248   0.8885   0.0569
  -7.500  -0.5762   0.08384   0.08082  -0.0526   0.9605   0.0456
  -7.250  -0.5674   0.08095   0.07791  -0.0530   0.9578   0.0466
  -7.000  -0.5735   0.07802   0.07490  -0.0507   0.9518   0.0471
  -6.750  -0.5681   0.07467   0.07145  -0.0505   0.9461   0.0485
  -6.500  -0.5556   0.07105   0.06763  -0.0519   0.9431   0.0511
  -6.250  -0.5629   0.06791   0.06433  -0.0481   0.9347   0.0523
  -6.000  -0.5439   0.06685   0.06233  -0.0479   0.9296   0.0569
  -5.750  -0.5543   0.05945   0.05493  -0.0449   0.9236   0.0585
  -5.500  -0.5377   0.05653   0.05200  -0.0449   0.9192   0.0602
  -5.250  -0.5150   0.04943   0.04401  -0.0428   0.9169   0.0421
  -5.000  -0.4885   0.04548   0.03957  -0.0433   0.9153   0.0399
  -4.750  -0.3894   0.03795   0.03084  -0.0527   0.8727   0.0395
  -4.500  -0.3716   0.03670   0.02927  -0.0511   0.8738   0.0402
  -4.250  -0.3683   0.03596   0.02831  -0.0470   0.8714   0.0420
  -4.000  -0.3541   0.03605   0.02817  -0.0449   0.8712   0.0440
  -3.750  -0.3108   0.03345   0.02548  -0.0471   0.8554   0.0507
  -3.500  -0.2892   0.03290   0.02479  -0.0461   0.8512   0.0547
  -3.250  -0.2397   0.03179   0.02363  -0.0498   0.8469   0.0631
  -2.750  -0.2064   0.03094   0.02273  -0.0463   0.8359   0.0748
  -2.500  -0.1633   0.03045   0.02220  -0.0489   0.8329   0.0854
  -2.250  -0.1583   0.03020   0.02201  -0.0454   0.8253   0.0935
  -2.000  -0.1291   0.02976   0.02163  -0.0459   0.8213   0.1167
  -1.750  -0.1086   0.02719   0.02121  -0.0454   0.8191   0.5583
  -1.500  -0.1274   0.02742   0.02245  -0.0346   0.8102   0.8255
  -1.250  -0.1134   0.02807   0.02303  -0.0297   0.8063   0.8802
  -1.000  -0.0937   0.02854   0.02340  -0.0259   0.8031   0.9092
  -0.500   0.2194   0.03163   0.02598  -0.0748   0.8070   0.9846
  -0.250   0.2998   0.03150   0.02572  -0.0857   0.8063   0.9929
   0.000   0.3776   0.03120   0.02532  -0.0962   0.8057   0.9997
   0.250   0.4207   0.03097   0.02502  -0.0994   0.8044   1.0000
   0.500   0.4016   0.03144   0.02549  -0.0915   0.7931   1.0000
   0.750   0.4405   0.03119   0.02518  -0.0937   0.7914   1.0000
   1.000   0.4838   0.03088   0.02483  -0.0967   0.7902   1.0000
   1.250   0.4663   0.03129   0.02524  -0.0891   0.7785   1.0000
   1.500   0.4673   0.03158   0.02552  -0.0848   0.7699   1.0000
   1.750   0.4937   0.03140   0.02532  -0.0847   0.7660   1.0000
   2.000   0.5303   0.03105   0.02496  -0.0863   0.7641   1.0000
   2.250   0.5709   0.03064   0.02454  -0.0885   0.7629   1.0000
   2.500   0.5581   0.03104   0.02495  -0.0818   0.7514   1.0000
   2.750   0.5957   0.03060   0.02452  -0.0835   0.7499   1.0000
   3.000   0.6359   0.03010   0.02405  -0.0856   0.7488   1.0000
   3.250   0.6238   0.03045   0.02442  -0.0790   0.7372   1.0000
   3.500   0.6254   0.03062   0.02460  -0.0747   0.7283   1.0000
   3.750   0.6541   0.03021   0.02422  -0.0748   0.7249   1.0000
   4.000   0.6898   0.02960   0.02366  -0.0759   0.7232   1.0000
   4.250   0.7284   0.02893   0.02305  -0.0775   0.7220   1.0000
   4.750   0.7268   0.02911   0.02329  -0.0680   0.7023   1.0000
   5.000   0.7530   0.02856   0.02281  -0.0675   0.6984   1.0000
   5.250   0.7875   0.02777   0.02210  -0.0682   0.6965   1.0000
   5.500   0.8251   0.02683   0.02127  -0.0694   0.6952   1.0000
   5.750   0.8205   0.02691   0.02139  -0.0640   0.6838   1.0000
   6.000   0.8562   0.02591   0.02049  -0.0647   0.6824   1.0000
   6.250   0.8914   0.02484   0.01955  -0.0653   0.6809   1.0000
   6.750   0.9275   0.02321   0.01812  -0.0609   0.6679   1.0000
   7.000   0.9391   0.02199   0.01695  -0.0570   0.6547   1.0000
   7.250   0.9396   0.02135   0.01633  -0.0517   0.6352   1.0000
   7.500   0.9840   0.01930   0.01429  -0.0526   0.6110   1.0000
   7.750   1.0282   0.01766   0.01227  -0.0533   0.5392   1.0000
   8.000   1.0123   0.01820   0.01245  -0.0457   0.4863   1.0000
   8.250   0.9915   0.01908   0.01302  -0.0380   0.4397   1.0000
   8.500   0.9729   0.02051   0.01408  -0.0315   0.3800   1.0000
   8.750   0.9544   0.02249   0.01557  -0.0259   0.3028   1.0000
   9.000   0.9282   0.02537   0.01764  -0.0200   0.1809   1.0000
   9.250   0.9063   0.02849   0.01991  -0.0151   0.0593   1.0000
   9.500   0.9067   0.03038   0.02163  -0.0126   0.0363   1.0000
   9.750   0.9165   0.03168   0.02306  -0.0111   0.0324   1.0000
  10.000   0.9228   0.03327   0.02474  -0.0094   0.0295   1.0000
  10.250   0.9231   0.03536   0.02695  -0.0073   0.0272   1.0000
  10.500   0.9320   0.03683   0.02853  -0.0060   0.0259   1.0000
  10.750   0.9380   0.03859   0.03039  -0.0046   0.0248   1.0000
  11.000   0.9444   0.04038   0.03225  -0.0032   0.0239   1.0000
  11.250   0.9523   0.04209   0.03406  -0.0018   0.0232   1.0000
  11.500   0.9633   0.04365   0.03567  -0.0006   0.0225   1.0000
  11.750   0.9796   0.04494   0.03701   0.0004   0.0223   1.0000
  12.000   1.0047   0.04593   0.03805   0.0010   0.0221   1.0000
  12.250   1.0323   0.04705   0.03924   0.0013   0.0212   1.0000
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