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GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il)
Reynolds number: 1,000,000
Max Cl/Cd: 124.57 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe173-il-1000000.txt
Download as CSV file: xf-goe173-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3004   0.11397   0.11235  -0.0216   1.0000   0.0079
  -9.500  -0.2945   0.11088   0.10927  -0.0225   1.0000   0.0085
  -8.000  -0.2824   0.09378   0.09231  -0.0242   1.0000   0.0090
  -7.750  -0.2718   0.09090   0.08944  -0.0260   0.9988   0.0092
  -7.500  -0.2501   0.08717   0.08571  -0.0313   0.9954   0.0094
  -7.250  -0.2288   0.08345   0.08199  -0.0366   0.9893   0.0097
  -7.000  -0.2021   0.07936   0.07789  -0.0435   0.9826   0.0102
  -6.750  -0.1777   0.07529   0.07381  -0.0498   0.9676   0.0110
  -6.500  -0.1430   0.07023   0.06867  -0.0600   0.9324   0.0117
  -6.250  -0.1189   0.06618   0.06433  -0.0667   0.8597   0.0118
  -6.000  -0.0968   0.06247   0.06041  -0.0716   0.8214   0.0119
  -5.750  -0.0728   0.05855   0.05633  -0.0765   0.7983   0.0119
  -5.500  -0.0482   0.05276   0.05042  -0.0828   0.7813   0.0121
  -5.250  -0.0292   0.05061   0.04818  -0.0841   0.7654   0.0124
  -5.000  -0.0048   0.04821   0.04569  -0.0868   0.7522   0.0130
  -4.750   0.0238   0.04526   0.04262  -0.0905   0.7399   0.0142
  -4.500   0.0684   0.04031   0.03746  -0.0973   0.7288   0.0156
  -4.250   0.1003   0.03638   0.03337  -0.1006   0.7183   0.0157
  -4.000   0.1335   0.02991   0.02661  -0.1050   0.7095   0.0160
  -3.750   0.1588   0.02807   0.02464  -0.1062   0.6987   0.0165
  -3.500   0.1852   0.02683   0.02330  -0.1070   0.6879   0.0173
  -3.250   0.2204   0.02428   0.02047  -0.1077   0.6779   0.0204
  -3.000   0.2484   0.02003   0.01589  -0.1094   0.6682   0.0188
  -2.750   0.2812   0.01555   0.01082  -0.1100   0.6596   0.0198
  -2.500   0.3103   0.01333   0.00815  -0.1103   0.6505   0.0215
  -2.250   0.3360   0.01449   0.00951  -0.1104   0.6397   0.0240
  -2.000   0.3655   0.01274   0.00743  -0.1105   0.6301   0.0243
  -1.750   0.3941   0.01218   0.00659  -0.1104   0.6201   0.0281
  -1.500   0.4215   0.01149   0.00584  -0.1105   0.6094   0.0298
  -1.250   0.4496   0.01097   0.00520  -0.1105   0.5978   0.0310
  -1.000   0.4779   0.01028   0.00435  -0.1104   0.5860   0.0313
  -0.750   0.5058   0.00988   0.00383  -0.1103   0.5738   0.0326
  -0.500   0.5337   0.00941   0.00324  -0.1101   0.5619   0.0323
  -0.250   0.5615   0.00906   0.00280  -0.1100   0.5496   0.0321
   0.000   0.5892   0.00880   0.00247  -0.1099   0.5367   0.0322
   0.250   0.6168   0.00865   0.00224  -0.1098   0.5228   0.0331
   0.500   0.6445   0.00850   0.00202  -0.1097   0.5079   0.0335
   0.750   0.6721   0.00843   0.00187  -0.1096   0.4911   0.0343
   1.000   0.6995   0.00843   0.00178  -0.1095   0.4704   0.0349
   1.250   0.7265   0.00850   0.00173  -0.1093   0.4444   0.0354
   1.500   0.7529   0.00866   0.00173  -0.1091   0.4094   0.0356
   1.750   0.7790   0.00887   0.00176  -0.1088   0.3750   0.0361
   2.250   0.8323   0.00919   0.00184  -0.1084   0.3355   0.0397
   2.500   0.8593   0.00931   0.00192  -0.1083   0.3240   0.0460
   2.750   0.8790   0.00777   0.00229  -0.1071   0.3162   0.9429
   3.000   0.9081   0.00791   0.00238  -0.1074   0.3079   1.0000
   3.250   0.9354   0.00805   0.00248  -0.1074   0.3020   1.0000
   3.500   0.9624   0.00821   0.00260  -0.1072   0.2960   1.0000
   3.750   0.9894   0.00838   0.00274  -0.1071   0.2908   1.0000
   4.000   1.0166   0.00852   0.00286  -0.1070   0.2864   1.0000
   4.250   1.0434   0.00869   0.00300  -0.1069   0.2818   1.0000
   4.500   1.0700   0.00888   0.00317  -0.1067   0.2769   1.0000
   4.750   1.0971   0.00900   0.00329  -0.1067   0.2715   1.0000
   5.000   1.1235   0.00921   0.00345  -0.1065   0.2647   1.0000
   5.250   1.1504   0.00935   0.00360  -0.1064   0.2601   1.0000
   5.500   1.1770   0.00951   0.00376  -0.1063   0.2548   1.0000
   5.750   1.2032   0.00971   0.00393  -0.1061   0.2473   1.0000
   6.000   1.2296   0.00989   0.00409  -0.1059   0.2393   1.0000
   6.250   1.2557   0.01008   0.00428  -0.1058   0.2309   1.0000
   6.500   1.2811   0.01035   0.00448  -0.1055   0.2166   1.0000
   6.750   1.3044   0.01083   0.00477  -0.1049   0.1848   1.0000
   7.000   1.3090   0.01340   0.00643  -0.1017   0.0445   1.0000
   7.250   1.3283   0.01433   0.00722  -0.1004   0.0146   1.0000
   7.500   1.3519   0.01474   0.00770  -0.0998   0.0135   1.0000
   7.750   1.3745   0.01524   0.00826  -0.0990   0.0121   1.0000
   8.000   1.3954   0.01590   0.00900  -0.0980   0.0106   1.0000
   8.250   1.4157   0.01660   0.00979  -0.0969   0.0099   1.0000
   8.500   1.4371   0.01713   0.01038  -0.0960   0.0094   1.0000
   8.750   1.4574   0.01775   0.01107  -0.0949   0.0089   1.0000
   9.000   1.4766   0.01844   0.01183  -0.0937   0.0084   1.0000
   9.250   1.4946   0.01917   0.01262  -0.0923   0.0079   1.0000
   9.500   1.5108   0.02001   0.01352  -0.0907   0.0074   1.0000
   9.750   1.5162   0.02162   0.01527  -0.0875   0.0069   1.0000
  10.000   1.5214   0.02290   0.01668  -0.0842   0.0066   1.0000
  10.250   1.5320   0.02372   0.01756  -0.0818   0.0065   1.0000
  10.500   1.5397   0.02474   0.01867  -0.0791   0.0063   1.0000
  10.750   1.5451   0.02597   0.01998  -0.0763   0.0061   1.0000
  11.000   1.5483   0.02744   0.02155  -0.0737   0.0060   1.0000
  11.250   1.5503   0.02914   0.02334  -0.0713   0.0058   1.0000
  11.500   1.5512   0.03111   0.02542  -0.0693   0.0057   1.0000
  11.750   1.5515   0.03337   0.02777  -0.0677   0.0056   1.0000
  12.000   1.5523   0.03577   0.03028  -0.0666   0.0054   1.0000
  12.250   1.5520   0.03846   0.03308  -0.0659   0.0053   1.0000
  12.500   1.5509   0.04136   0.03607  -0.0653   0.0052   1.0000
  12.750   1.5486   0.04449   0.03930  -0.0649   0.0051   1.0000
  13.000   1.5463   0.04772   0.04262  -0.0647   0.0050   1.0000
  13.250   1.5423   0.05119   0.04618  -0.0647   0.0049   1.0000
  13.500   1.5364   0.05496   0.05005  -0.0646   0.0048   1.0000
  13.750   1.5294   0.05892   0.05409  -0.0647   0.0047   1.0000
  14.000   1.5212   0.06302   0.05828  -0.0648   0.0047   1.0000
  14.250   1.5106   0.06738   0.06272  -0.0647   0.0045   1.0000
  14.500   1.4940   0.07148   0.06690  -0.0619   0.0043   1.0000
  14.750   1.4909   0.07561   0.07116  -0.0634   0.0043   1.0000
  15.000   1.4878   0.07974   0.07541  -0.0646   0.0042   1.0000
  15.250   1.4840   0.08393   0.07971  -0.0657   0.0042   1.0000
  15.500   1.4794   0.08818   0.08408  -0.0667   0.0041   1.0000
  15.750   1.4742   0.09249   0.08851  -0.0676   0.0040   1.0000
  16.000   1.4687   0.09691   0.09303  -0.0685   0.0040   1.0000
  16.250   1.4626   0.10145   0.09770  -0.0696   0.0040   1.0000
  16.500   1.4557   0.10616   0.10253  -0.0708   0.0039   1.0000
  16.750   1.4487   0.11102   0.10751  -0.0722   0.0039   1.0000
  17.000   1.4412   0.11610   0.11272  -0.0739   0.0038   1.0000
  17.250   1.4328   0.12140   0.11815  -0.0759   0.0038   1.0000
  17.500   1.4242   0.12692   0.12380  -0.0782   0.0038   1.0000
  17.750   1.4146   0.13276   0.12977  -0.0808   0.0038   1.0000
  18.000   1.4047   0.13882   0.13597  -0.0838   0.0038   1.0000
  18.250   1.3942   0.14520   0.14249  -0.0872   0.0038   1.0000
  18.500   1.3837   0.15181   0.14923  -0.0909   0.0038   1.0000
  18.750   1.3722   0.15877   0.15633  -0.0950   0.0038   1.0000
  19.000   1.3613   0.16581   0.16350  -0.0993   0.0038   1.0000
  19.250   1.3490   0.17344   0.17126  -0.1042   0.0038   1.0000
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