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GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il)
Reynolds number: 200,000
Max Cl/Cd: 77.7 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe173-il-200000.txt
Download as CSV file: xf-goe173-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 173 (ALBATROS 6020) AIRFOIL                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2735   0.09369   0.09060  -0.0237   1.0000   0.0262
  -7.000  -0.2781   0.09238   0.08938  -0.0238   1.0000   0.0265
  -6.750  -0.2845   0.09129   0.08839  -0.0239   1.0000   0.0267
  -6.500  -0.2706   0.08888   0.08601  -0.0305   0.9965   0.0269
  -6.250  -0.2244   0.08363   0.08069  -0.0443   0.9891   0.0271
  -6.000  -0.1998   0.07695   0.07402  -0.0491   0.9844   0.0275
  -5.750  -0.1810   0.07242   0.06951  -0.0496   0.9778   0.0283
  -5.500  -0.1483   0.06811   0.06517  -0.0553   0.9721   0.0298
  -5.250  -0.1106   0.06377   0.06076  -0.0632   0.9624   0.0323
  -5.000  -0.0421   0.05910   0.05585  -0.0799   0.9537   0.0355
  -4.750   0.0051   0.05322   0.04979  -0.0896   0.9454   0.0362
  -4.500   0.0248   0.04889   0.04550  -0.0908   0.9344   0.0376
  -4.250   0.0574   0.04554   0.04208  -0.0944   0.9223   0.0398
  -4.000   0.0989   0.04192   0.03826  -0.1000   0.9091   0.0440
  -3.750   0.1436   0.03751   0.03353  -0.1062   0.8951   0.0492
  -3.500   0.1719   0.03529   0.03122  -0.1077   0.8794   0.0544
  -3.250   0.2121   0.03197   0.02745  -0.1113   0.8640   0.0620
  -3.000   0.2369   0.03012   0.02551  -0.1118   0.8480   0.0670
  -2.750   0.2691   0.02781   0.02282  -0.1132   0.8329   0.0771
  -2.500   0.2979   0.02624   0.02093  -0.1138   0.8177   0.0907
  -2.250   0.3252   0.02484   0.01928  -0.1141   0.8031   0.1052
  -2.000   0.3519   0.02345   0.01770  -0.1143   0.7894   0.1202
  -1.750   0.3783   0.02211   0.01621  -0.1144   0.7769   0.1363
  -1.500   0.4050   0.02116   0.01507  -0.1145   0.7650   0.1641
  -1.000   0.4761   0.01635   0.00885  -0.1132   0.7442   0.0708
  -0.750   0.5042   0.01540   0.00767  -0.1128   0.7329   0.0693
  -0.500   0.5320   0.01470   0.00675  -0.1123   0.7222   0.0688
  -0.250   0.5595   0.01407   0.00595  -0.1118   0.7116   0.0674
   0.000   0.5865   0.01357   0.00537  -0.1113   0.6996   0.0674
   0.250   0.6133   0.01318   0.00494  -0.1108   0.6874   0.0684
   0.500   0.6402   0.01292   0.00464  -0.1104   0.6754   0.0714
   0.750   0.6670   0.01270   0.00437  -0.1099   0.6633   0.0749
   1.000   0.6940   0.01249   0.00411  -0.1096   0.6510   0.0791
   1.250   0.7209   0.01239   0.00394  -0.1091   0.6378   0.0877
   1.500   0.7422   0.01045   0.00395  -0.1077   0.6245   1.0000
   1.750   0.7686   0.01056   0.00385  -0.1071   0.6087   1.0000
   2.000   0.7947   0.01068   0.00382  -0.1066   0.5907   1.0000
   2.250   0.8204   0.01083   0.00381  -0.1060   0.5708   1.0000
   2.500   0.8457   0.01101   0.00384  -0.1053   0.5487   1.0000
   2.750   0.8706   0.01124   0.00389  -0.1046   0.5235   1.0000
   3.000   0.8951   0.01152   0.00399  -0.1039   0.4950   1.0000
   3.250   0.9193   0.01185   0.00413  -0.1032   0.4660   1.0000
   3.500   0.9437   0.01222   0.00434  -0.1026   0.4402   1.0000
   3.750   0.9680   0.01263   0.00457  -0.1020   0.4204   1.0000
   4.000   0.9928   0.01303   0.00485  -0.1014   0.4047   1.0000
   4.250   1.0175   0.01346   0.00514  -0.1010   0.3926   1.0000
   4.500   1.0428   0.01386   0.00550  -0.1006   0.3819   1.0000
   4.750   1.0681   0.01427   0.00586  -0.1002   0.3731   1.0000
   5.000   1.0933   0.01474   0.00624  -0.0998   0.3658   1.0000
   5.250   1.1190   0.01514   0.00666  -0.0995   0.3593   1.0000
   5.500   1.1447   0.01558   0.00710  -0.0993   0.3536   1.0000
   5.750   1.1705   0.01610   0.00758  -0.0991   0.3489   1.0000
   6.000   1.1963   0.01650   0.00807  -0.0988   0.3441   1.0000
   6.250   1.2216   0.01694   0.00851  -0.0985   0.3381   1.0000
   6.500   1.2460   0.01735   0.00900  -0.0980   0.3305   1.0000
   6.750   1.2703   0.01776   0.00940  -0.0976   0.3228   1.0000
   7.000   1.2930   0.01803   0.00977  -0.0968   0.3122   1.0000
   7.250   1.3159   0.01838   0.01016  -0.0962   0.3030   1.0000
   7.500   1.3382   0.01869   0.01050  -0.0954   0.2929   1.0000
   7.750   1.3596   0.01883   0.01081  -0.0944   0.2811   1.0000
   8.000   1.3815   0.01906   0.01116  -0.0935   0.2701   1.0000
   8.250   1.4018   0.01920   0.01138  -0.0924   0.2522   1.0000
   8.500   1.4223   0.01941   0.01166  -0.0913   0.2274   1.0000
   8.750   1.4384   0.02014   0.01216  -0.0896   0.1661   1.0000
   9.000   1.4281   0.02355   0.01460  -0.0851   0.0486   1.0000
   9.250   1.4351   0.02521   0.01618  -0.0823   0.0311   1.0000
   9.500   1.4444   0.02651   0.01759  -0.0797   0.0275   1.0000
   9.750   1.4515   0.02773   0.01900  -0.0768   0.0258   1.0000
  10.000   1.4557   0.02919   0.02062  -0.0739   0.0242   1.0000
  10.250   1.4565   0.03093   0.02253  -0.0709   0.0229   1.0000
  10.500   1.4541   0.03303   0.02480  -0.0681   0.0222   1.0000
  10.750   1.4493   0.03555   0.02749  -0.0658   0.0217   1.0000
  11.000   1.4426   0.03852   0.03065  -0.0640   0.0213   1.0000
  11.250   1.4349   0.04190   0.03419  -0.0628   0.0211   1.0000
  11.500   1.4264   0.04557   0.03801  -0.0619   0.0208   1.0000
  11.750   1.4181   0.04936   0.04192  -0.0612   0.0207   1.0000
  12.000   1.4128   0.05287   0.04552  -0.0605   0.0205   1.0000
  12.250   1.4097   0.05614   0.04891  -0.0598   0.0205   1.0000
  12.500   1.4081   0.05922   0.05209  -0.0589   0.0204   1.0000
  12.750   1.4084   0.06202   0.05498  -0.0578   0.0203   1.0000
  13.000   1.4113   0.06457   0.05762  -0.0564   0.0202   1.0000
  13.250   1.4144   0.06718   0.06036  -0.0554   0.0200   1.0000
  13.500   1.4169   0.06994   0.06325  -0.0546   0.0196   1.0000
  13.750   1.4190   0.07283   0.06631  -0.0539   0.0192   1.0000
  14.000   1.4227   0.07559   0.06922  -0.0528   0.0191   1.0000
  14.250   1.4258   0.07858   0.07239  -0.0516   0.0192   1.0000
  14.500   1.4269   0.08199   0.07599  -0.0508   0.0194   1.0000
  14.750   1.4256   0.08589   0.08010  -0.0503   0.0197   1.0000
  15.000   1.4218   0.09028   0.08470  -0.0500   0.0200   1.0000
  15.250   1.4300   0.09407   0.08866  -0.0481   0.0208   1.0000
  15.500   1.4232   0.09802   0.09279  -0.0496   0.0211   1.0000
  15.750   1.4126   0.10285   0.09784  -0.0518   0.0214   1.0000
  16.000   1.3965   0.10914   0.10444  -0.0551   0.0221   1.0000
  16.250   1.3732   0.11737   0.11303  -0.0596   0.0230   1.0000
  16.500   1.3507   0.12594   0.12188  -0.0647   0.0235   1.0000
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