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AH 80-136 (ah80136-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: AH 80-136 (ah80136-il)
Reynolds number: 50,000
Max Cl/Cd: 13.82 at α=12.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah80136-il-50000-n5.txt
Download as CSV file: xf-ah80136-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 80-136                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3347   0.10466   0.09906  -0.0134   0.7501   0.0658
  -9.250  -0.3335   0.10041   0.09482  -0.0149   0.7480   0.0642
  -9.000  -0.4700   0.10270   0.09692  -0.0114   0.7560   0.0550
  -8.750  -0.4584   0.09912   0.09334  -0.0110   0.7527   0.0537
  -8.500  -0.4546   0.09430   0.08853  -0.0146   0.7498   0.0528
  -8.250  -0.4540   0.08903   0.08324  -0.0195   0.7472   0.0520
  -8.000  -0.4582   0.08451   0.07867  -0.0227   0.7450   0.0513
  -7.750  -0.4587   0.07966   0.07372  -0.0264   0.7425   0.0507
  -7.500  -0.4571   0.07489   0.06881  -0.0297   0.7395   0.0504
  -7.250  -0.4537   0.07043   0.06414  -0.0321   0.7366   0.0503
  -7.000  -0.4484   0.06622   0.05966  -0.0336   0.7339   0.0502
  -6.750  -0.4410   0.06226   0.05537  -0.0344   0.7313   0.0501
  -6.500  -0.4301   0.05841   0.05113  -0.0350   0.7287   0.0498
  -6.250  -0.4145   0.05464   0.04694  -0.0360   0.7254   0.0493
  -6.000  -0.3974   0.05130   0.04313  -0.0363   0.7224   0.0492
  -5.750  -0.3791   0.04833   0.03967  -0.0361   0.7196   0.0494
  -5.500  -0.3597   0.04580   0.03661  -0.0354   0.7170   0.0508
  -5.250  -0.3376   0.04363   0.03385  -0.0350   0.7142   0.0534
  -5.000  -0.3110   0.04173   0.03132  -0.0353   0.7105   0.0553
  -4.750  -0.2852   0.03946   0.02885  -0.0356   0.7074   0.0569
  -4.500  -0.2591   0.03785   0.02704  -0.0355   0.7046   0.0595
  -4.250  -0.2332   0.03666   0.02560  -0.0351   0.7021   0.0647
  -4.000  -0.2039   0.03559   0.02413  -0.0352   0.6991   0.0689
  -3.750  -0.1748   0.03439   0.02298  -0.0360   0.6954   0.0735
  -3.500  -0.1471   0.03373   0.02210  -0.0361   0.6923   0.0822
  -3.250  -0.1216   0.03293   0.02127  -0.0359   0.6895   0.0901
  -3.000  -0.0972   0.03229   0.02048  -0.0354   0.6872   0.1018
  -2.750  -0.0714   0.03177   0.01999  -0.0360   0.6836   0.1241
  -2.500  -0.0495   0.03075   0.01952  -0.0363   0.6799   0.2018
  -2.250  -0.0407   0.02878   0.01969  -0.0327   0.6770   0.6314
  -2.000   0.1195   0.02927   0.02010  -0.0495   0.6753   0.9947
  -1.500   0.1705   0.02975   0.02001  -0.0518   0.6687   1.0000
  -1.250   0.1915   0.03021   0.02026  -0.0524   0.6647   1.0000
  -1.000   0.2110   0.03058   0.02043  -0.0521   0.6614   1.0000
  -0.750   0.2299   0.03090   0.02052  -0.0512   0.6586   1.0000
  -0.500   0.2499   0.03152   0.02098  -0.0514   0.6547   1.0000
  -0.250   0.2693   0.03224   0.02156  -0.0517   0.6501   1.0000
   0.000   0.2882   0.03276   0.02192  -0.0511   0.6465   1.0000
   0.250   0.3074   0.03316   0.02215  -0.0499   0.6437   1.0000
   0.500   0.3249   0.03407   0.02296  -0.0501   0.6388   1.0000
   0.750   0.3420   0.03488   0.02367  -0.0497   0.6340   1.0000
   1.000   0.3610   0.03541   0.02408  -0.0487   0.6306   1.0000
   1.250   0.3816   0.03577   0.02431  -0.0474   0.6279   1.0000
   1.500   0.3931   0.03718   0.02569  -0.0477   0.6208   1.0000
   1.750   0.4115   0.03780   0.02622  -0.0467   0.6166   1.0000
   2.000   0.4329   0.03819   0.02651  -0.0455   0.6137   1.0000
   2.500   0.4612   0.04028   0.02852  -0.0444   0.6018   1.0000
   2.750   0.4843   0.04064   0.02882  -0.0433   0.5989   1.0000
   3.000   0.4910   0.04226   0.03044  -0.0430   0.5903   1.0000
   3.250   0.5127   0.04278   0.03094  -0.0422   0.5863   1.0000
   3.500   0.5251   0.04400   0.03214  -0.0416   0.5796   1.0000
   3.750   0.5420   0.04489   0.03303  -0.0410   0.5737   1.0000
   4.000   0.5670   0.04525   0.03337  -0.0402   0.5703   1.0000
   4.500   0.5957   0.04747   0.03565  -0.0391   0.5570   1.0000
   4.750   0.6032   0.04902   0.03723  -0.0386   0.5485   1.0000
   5.000   0.6247   0.04967   0.03791  -0.0380   0.5435   1.0000
   5.500   0.6531   0.05190   0.04022  -0.0368   0.5299   1.0000
   5.750   0.6793   0.05227   0.04068  -0.0363   0.5262   1.0000
   6.000   0.6794   0.05415   0.04260  -0.0353   0.5160   1.0000
   6.500   0.7063   0.05646   0.04503  -0.0339   0.5020   1.0000
   6.750   0.7308   0.05691   0.04562  -0.0334   0.4975   1.0000
   7.000   0.7341   0.05879   0.04756  -0.0327   0.4878   1.0000
   7.500   0.7624   0.06112   0.05008  -0.0315   0.4733   1.0000
   8.000   0.7910   0.06345   0.05263  -0.0304   0.4587   1.0000
   8.250   0.7953   0.06547   0.05478  -0.0300   0.4491   1.0000
   8.500   0.8202   0.06572   0.05519  -0.0294   0.4439   1.0000
   8.750   0.8220   0.06802   0.05759  -0.0290   0.4335   1.0000
   9.000   0.8500   0.06790   0.05765  -0.0282   0.4291   1.0000
   9.250   0.8494   0.07050   0.06037  -0.0280   0.4180   1.0000
   9.750   0.8780   0.07283   0.06305  -0.0269   0.4025   1.0000
  10.000   0.8808   0.07521   0.06556  -0.0267   0.3921   1.0000
  10.250   0.9086   0.07482   0.06541  -0.0257   0.3870   1.0000
  10.500   0.9083   0.07757   0.06829  -0.0255   0.3756   1.0000
  10.750   0.9152   0.07951   0.07040  -0.0252   0.3658   1.0000
  11.000   0.9416   0.07893   0.07012  -0.0240   0.3591   1.0000
  11.250   0.9455   0.08101   0.07236  -0.0236   0.3471   1.0000
  11.500   0.9613   0.08085   0.07242  -0.0223   0.3339   1.0000
  11.750   0.9950   0.07682   0.06868  -0.0195   0.3178   1.0000
  12.250   1.0255   0.07568   0.06800  -0.0168   0.2803   1.0000
  12.500   1.0407   0.07529   0.06776  -0.0155   0.2556   1.0000
  12.750   1.0455   0.07680   0.06934  -0.0150   0.2249   1.0000
  13.000   1.0505   0.07809   0.07039  -0.0141   0.1822   1.0000
  13.250   1.0462   0.08106   0.07293  -0.0139   0.1459   1.0000
  13.500   1.0376   0.08510   0.07665  -0.0142   0.1219   1.0000
  13.750   1.0302   0.08922   0.08055  -0.0146   0.1053   1.0000
  14.000   1.0244   0.09325   0.08442  -0.0151   0.0927   1.0000
  14.250   1.0199   0.09708   0.08812  -0.0156   0.0828   1.0000
  14.500   1.0191   0.10057   0.09164  -0.0159   0.0739   1.0000
  14.750   1.0191   0.10389   0.09494  -0.0162   0.0670   1.0000
  15.000   1.0208   0.10697   0.09809  -0.0164   0.0610   1.0000
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