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AH 80-129 (ah80129-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: AH 80-129 (ah80129-il)
Reynolds number: 50,000
Max Cl/Cd: 19.03 at α=10.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah80129-il-50000-n5.txt
Download as CSV file: xf-ah80129-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 80-129                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2748   0.12726   0.12102  -0.0606   0.9748   0.0885
 -10.750  -0.2806   0.12519   0.11901  -0.0674   0.9702   0.0916
 -10.500  -0.2801   0.12199   0.11584  -0.0721   0.9650   0.0920
 -10.250  -0.2567   0.11614   0.10996  -0.0721   0.9623   0.0933
 -10.000  -0.2405   0.11151   0.10530  -0.0741   0.9591   0.0953
  -9.750  -0.2294   0.10760   0.10137  -0.0778   0.9558   0.0956
  -9.500  -0.2272   0.10404   0.09783  -0.0809   0.9501   0.0946
  -9.250  -0.2168   0.09662   0.09030  -0.0863   0.9458   0.0483
  -9.000  -0.2088   0.09264   0.08632  -0.0899   0.9418   0.0477
  -8.750  -0.2067   0.08927   0.08297  -0.0915   0.9357   0.0458
  -8.500  -0.2034   0.08527   0.07899  -0.0951   0.9308   0.0444
  -8.250  -0.2093   0.08168   0.07542  -0.0977   0.9239   0.0423
  -8.000  -0.2126   0.07870   0.07244  -0.0995   0.9177   0.0438
  -7.750  -0.2438   0.07454   0.06808  -0.1007   0.9073   0.0379
  -7.500  -0.2443   0.07120   0.06464  -0.1010   0.9025   0.0377
  -7.250  -0.2535   0.06931   0.06269  -0.0982   0.8956   0.0375
  -7.000  -0.2549   0.06662   0.05983  -0.0973   0.8904   0.0376
  -6.750  -0.2514   0.06508   0.05842  -0.0956   0.8859   0.0414
  -6.500  -0.2574   0.06299   0.05620  -0.0929   0.8794   0.0422
  -6.250  -0.2526   0.05986   0.05280  -0.0922   0.8752   0.0420
  -6.000  -0.2626   0.05773   0.05042  -0.0879   0.8682   0.0406
  -5.750  -0.2563   0.05531   0.04774  -0.0861   0.8637   0.0419
  -5.500  -0.2513   0.05282   0.04482  -0.0838   0.8590   0.0413
  -5.250  -0.2505   0.05086   0.04253  -0.0802   0.8531   0.0409
  -5.000  -0.2367   0.04803   0.03920  -0.0784   0.8493   0.0409
  -4.750  -0.2282   0.04613   0.03694  -0.0756   0.8444   0.0415
  -4.500  -0.2184   0.04444   0.03485  -0.0729   0.8393   0.0417
  -4.250  -0.1965   0.04240   0.03236  -0.0719   0.8360   0.0431
  -4.000  -0.1743   0.04061   0.03012  -0.0708   0.8326   0.0446
  -3.750  -0.1643   0.03958   0.02879  -0.0677   0.8270   0.0458
  -3.500  -0.1379   0.03822   0.02702  -0.0672   0.8236   0.0525
  -3.250  -0.1052   0.03714   0.02576  -0.0681   0.8211   0.0585
  -3.000  -0.0905   0.03641   0.02475  -0.0656   0.8158   0.0648
  -2.750  -0.0666   0.03567   0.02385  -0.0651   0.8118   0.0793
  -2.500  -0.0359   0.03481   0.02293  -0.0658   0.8088   0.1060
  -2.250   0.2075   0.03052   0.02108  -0.1032   0.8209   1.0000
  -2.000   0.2000   0.03111   0.02151  -0.0980   0.8132   1.0000
  -1.750   0.2174   0.03135   0.02144  -0.0967   0.8088   1.0000
  -1.500   0.2195   0.03186   0.02174  -0.0930   0.8027   1.0000
  -1.250   0.2282   0.03226   0.02193  -0.0903   0.7970   1.0000
  -1.000   0.2527   0.03248   0.02187  -0.0901   0.7936   1.0000
  -0.750   0.2436   0.03317   0.02242  -0.0845   0.7855   1.0000
  -0.500   0.2645   0.03348   0.02251  -0.0837   0.7814   1.0000
  -0.250   0.2643   0.03406   0.02291  -0.0795   0.7747   1.0000
   0.000   0.2774   0.03451   0.02320  -0.0775   0.7694   1.0000
   0.250   0.3056   0.03481   0.02329  -0.0778   0.7662   1.0000
   0.500   0.2967   0.03554   0.02391  -0.0724   0.7579   1.0000
   0.750   0.3205   0.03592   0.02410  -0.0720   0.7540   1.0000
   1.000   0.3244   0.03657   0.02465  -0.0686   0.7472   1.0000
   1.250   0.3412   0.03707   0.02503  -0.0672   0.7420   1.0000
   1.500   0.3699   0.03742   0.02526  -0.0676   0.7389   1.0000
   1.750   0.3668   0.03825   0.02601  -0.0634   0.7305   1.0000
   2.000   0.3919   0.03867   0.02634  -0.0633   0.7266   1.0000
   2.250   0.3979   0.03943   0.02703  -0.0605   0.7195   1.0000
   2.500   0.4182   0.03995   0.02749  -0.0597   0.7145   1.0000
   2.750   0.4403   0.04047   0.02795  -0.0592   0.7102   1.0000
   3.000   0.4468   0.04131   0.02876  -0.0566   0.7027   1.0000
   3.250   0.4743   0.04170   0.02917  -0.0568   0.6990   1.0000
   3.500   0.4789   0.04265   0.03009  -0.0542   0.6909   1.0000
   3.750   0.5035   0.04313   0.03056  -0.0540   0.6865   1.0000
   4.000   0.5135   0.04398   0.03142  -0.0521   0.6791   1.0000
   4.250   0.5347   0.04457   0.03203  -0.0516   0.6738   1.0000
   4.500   0.5519   0.04530   0.03284  -0.0507   0.6681   1.0000
   4.750   0.5671   0.04605   0.03363  -0.0495   0.6611   1.0000
   5.000   0.5968   0.04638   0.03403  -0.0498   0.6576   1.0000
   5.250   0.6002   0.04758   0.03527  -0.0475   0.6481   1.0000
   5.500   0.6288   0.04796   0.03575  -0.0478   0.6443   1.0000
   5.750   0.6332   0.04922   0.03707  -0.0457   0.6350   1.0000
   6.000   0.6614   0.04959   0.03757  -0.0459   0.6309   1.0000
   6.250   0.6674   0.05082   0.03897  -0.0440   0.6212   1.0000
   6.500   0.6965   0.05113   0.03945  -0.0442   0.6171   1.0000
   6.750   0.7017   0.05247   0.04088  -0.0424   0.6070   1.0000
   7.000   0.7319   0.05269   0.04129  -0.0426   0.6031   1.0000
   7.250   0.7360   0.05419   0.04292  -0.0408   0.5926   1.0000
   7.500   0.7502   0.05518   0.04413  -0.0398   0.5843   1.0000
   7.750   0.7730   0.05564   0.04481  -0.0394   0.5776   1.0000
   8.000   0.7821   0.05695   0.04630  -0.0380   0.5676   1.0000
   8.250   0.8123   0.05693   0.04656  -0.0379   0.5624   1.0000
   8.500   0.8200   0.05824   0.04806  -0.0365   0.5510   1.0000
  10.000   0.9413   0.05142   0.04311  -0.0224   0.4169   1.0000
  10.250   0.9429   0.04955   0.03935  -0.0155   0.1768   1.0000
  10.500   0.9278   0.05340   0.04259  -0.0135   0.1127   1.0000
  10.750   0.9142   0.05745   0.04618  -0.0119   0.0753   1.0000
  11.000   0.9084   0.06083   0.04939  -0.0108   0.0605   1.0000
  11.250   0.9056   0.06402   0.05259  -0.0096   0.0518   1.0000
  11.500   0.9038   0.06711   0.05569  -0.0086   0.0464   1.0000
  11.750   0.9052   0.06989   0.05857  -0.0076   0.0398   1.0000
  12.000   0.9071   0.07255   0.06125  -0.0067   0.0360   1.0000
  12.250   0.9161   0.07444   0.06338  -0.0054   0.0329   1.0000
  12.500   0.9304   0.07572   0.06494  -0.0036   0.0310   1.0000
  12.750   0.9537   0.07623   0.06565  -0.0014   0.0292   1.0000
  13.000   0.9855   0.07647   0.06607   0.0006   0.0275   1.0000
  13.250   1.0228   0.07781   0.06762   0.0024   0.0258   1.0000
  13.500   1.0244   0.08110   0.07135   0.0030   0.0243   1.0000
  13.750   1.0266   0.08465   0.07527   0.0034   0.0234   1.0000
  14.000   1.0279   0.08833   0.07926   0.0037   0.0236   1.0000
  14.250   1.0228   0.09281   0.08406   0.0036   0.0235   1.0000
  14.500   1.0131   0.09751   0.08905   0.0030   0.0232   1.0000
  14.750   1.0004   0.10284   0.09463   0.0018   0.0230   1.0000
  15.000   0.9855   0.10871   0.10077   0.0001   0.0228   1.0000
  15.250   0.9713   0.11470   0.10697  -0.0022   0.0230   1.0000
  15.500   0.9558   0.12132   0.11379  -0.0052   0.0232   1.0000
  15.750   0.9420   0.12802   0.12063  -0.0085   0.0236   1.0000
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