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GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il)
Reynolds number: 500,000
Max Cl/Cd: 101.46 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe173-il-500000-n5.txt
Download as CSV file: xf-goe173-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2653   0.11002   0.10783  -0.0263   1.0000   0.0078
  -9.000  -0.2611   0.10741   0.10525  -0.0266   1.0000   0.0080
  -8.750  -0.2574   0.10486   0.10273  -0.0268   1.0000   0.0082
  -8.500  -0.2479   0.10170   0.09957  -0.0288   0.9982   0.0087
  -8.250  -0.2315   0.09781   0.09569  -0.0331   0.9936   0.0095
  -7.750  -0.0932   0.06911   0.06681  -0.0544   0.8561   0.0100
  -7.500  -0.1854   0.08661   0.08450  -0.0462   0.9572   0.0097
  -7.250  -0.1620   0.08233   0.08018  -0.0531   0.9271   0.0097
  -7.000  -0.1402   0.07825   0.07595  -0.0588   0.8811   0.0098
  -6.750  -0.1253   0.07488   0.07239  -0.0620   0.8406   0.0098
  -6.500  -0.0644   0.05405   0.05134  -0.0597   0.7606   0.0091
  -6.250  -0.0994   0.06886   0.06612  -0.0653   0.7932   0.0091
  -6.000  -0.0803   0.06540   0.06257  -0.0695   0.7759   0.0084
  -5.750  -0.0574   0.06130   0.05837  -0.0750   0.7615   0.0078
  -5.500  -0.0311   0.05676   0.05373  -0.0811   0.7493   0.0075
  -5.250  -0.0028   0.05255   0.04940  -0.0869   0.7378   0.0075
  -5.000   0.0272   0.04854   0.04528  -0.0923   0.7270   0.0077
  -4.750   0.0590   0.04444   0.04105  -0.0977   0.7170   0.0080
  -4.250   0.1328   0.03388   0.03004  -0.1092   0.6979   0.0095
  -4.000   0.1702   0.02796   0.02376  -0.1138   0.6897   0.0100
  -3.750   0.1999   0.02573   0.02131  -0.1152   0.6795   0.0106
  -3.500   0.2393   0.01633   0.01089  -0.1185   0.6727   0.0138
  -3.250   0.2664   0.01618   0.01061  -0.1185   0.6611   0.0145
  -3.000   0.2940   0.01572   0.00997  -0.1186   0.6492   0.0155
  -2.750   0.3234   0.01406   0.00782  -0.1187   0.6378   0.0188
  -2.500   0.3512   0.01324   0.00675  -0.1187   0.6248   0.0202
  -2.250   0.3786   0.01306   0.00647  -0.1187   0.6126   0.0212
  -2.000   0.4061   0.01286   0.00616  -0.1187   0.6020   0.0230
  -1.750   0.4340   0.01238   0.00548  -0.1186   0.5907   0.0245
  -1.500   0.4618   0.01207   0.00500  -0.1185   0.5787   0.0259
  -1.250   0.4894   0.01206   0.00485  -0.1183   0.5665   0.0269
  -1.000   0.5170   0.01144   0.00406  -0.1182   0.5552   0.0277
  -0.750   0.5444   0.01098   0.00350  -0.1182   0.5437   0.0284
  -0.500   0.5718   0.01070   0.00314  -0.1181   0.5315   0.0291
  -0.250   0.5991   0.01052   0.00291  -0.1180   0.5188   0.0302
   0.000   0.6265   0.01038   0.00268  -0.1179   0.5052   0.0304
   0.250   0.6537   0.01027   0.00249  -0.1178   0.4900   0.0306
   0.500   0.6808   0.01023   0.00236  -0.1176   0.4719   0.0310
   0.750   0.7076   0.01024   0.00226  -0.1175   0.4492   0.0317
   1.000   0.7339   0.01034   0.00221  -0.1172   0.4203   0.0327
   1.250   0.7599   0.01052   0.00222  -0.1169   0.3891   0.0339
   1.500   0.7859   0.01070   0.00226  -0.1167   0.3656   0.0350
   1.750   0.8123   0.01086   0.00232  -0.1165   0.3487   0.0359
   2.000   0.8388   0.01102   0.00239  -0.1163   0.3362   0.0365
   2.250   0.8653   0.01117   0.00248  -0.1161   0.3261   0.0388
   2.500   0.8921   0.01129   0.00257  -0.1159   0.3183   0.0422
   2.750   0.9186   0.01144   0.00270  -0.1157   0.3111   0.0459
   3.000   0.9462   0.01058   0.00307  -0.1165   0.3054   0.6593
   3.500   0.9927   0.01031   0.00334  -0.1145   0.2951   1.0000
   3.750   1.0195   0.01047   0.00349  -0.1143   0.2908   1.0000
   4.000   1.0459   0.01065   0.00366  -0.1141   0.2862   1.0000
   4.250   1.0720   0.01087   0.00385  -0.1139   0.2818   1.0000
   4.500   1.0983   0.01106   0.00403  -0.1137   0.2781   1.0000
   4.750   1.1246   0.01124   0.00423  -0.1135   0.2743   1.0000
   5.000   1.1507   0.01144   0.00444  -0.1133   0.2707   1.0000
   5.250   1.1762   0.01169   0.00468  -0.1130   0.2667   1.0000
   5.500   1.2022   0.01188   0.00488  -0.1128   0.2601   1.0000
   5.750   1.2275   0.01213   0.00513  -0.1125   0.2529   1.0000
   6.000   1.2530   0.01235   0.00535  -0.1122   0.2445   1.0000
   6.250   1.2777   0.01265   0.00561  -0.1118   0.2345   1.0000
   6.500   1.3022   0.01296   0.00588  -0.1114   0.2217   1.0000
   6.750   1.3257   0.01335   0.00620  -0.1109   0.1996   1.0000
   7.000   1.3354   0.01515   0.00733  -0.1085   0.0989   1.0000
   7.250   1.3434   0.01714   0.00885  -0.1057   0.0163   1.0000
   7.500   1.3642   0.01775   0.00952  -0.1047   0.0116   1.0000
   7.750   1.3856   0.01827   0.01013  -0.1038   0.0101   1.0000
   8.000   1.4062   0.01883   0.01079  -0.1028   0.0089   1.0000
   8.250   1.4253   0.01950   0.01154  -0.1016   0.0078   1.0000
   8.500   1.4426   0.02029   0.01244  -0.1001   0.0069   1.0000
   8.750   1.4604   0.02098   0.01323  -0.0987   0.0064   1.0000
   9.000   1.4764   0.02177   0.01412  -0.0970   0.0060   1.0000
   9.250   1.4904   0.02264   0.01507  -0.0951   0.0056   1.0000
   9.500   1.5007   0.02355   0.01609  -0.0926   0.0052   1.0000
   9.750   1.5070   0.02473   0.01736  -0.0897   0.0049   1.0000
  10.000   1.5133   0.02594   0.01868  -0.0869   0.0046   1.0000
  10.250   1.5210   0.02709   0.01994  -0.0845   0.0043   1.0000
  10.500   1.5253   0.02855   0.02152  -0.0820   0.0041   1.0000
  10.750   1.5279   0.03026   0.02335  -0.0797   0.0040   1.0000
  11.000   1.5293   0.03222   0.02543  -0.0777   0.0038   1.0000
  11.250   1.5297   0.03445   0.02778  -0.0760   0.0037   1.0000
  11.500   1.5298   0.03691   0.03036  -0.0748   0.0036   1.0000
  11.750   1.5283   0.03970   0.03327  -0.0739   0.0035   1.0000
  12.000   1.5256   0.04279   0.03647  -0.0733   0.0034   1.0000
  12.250   1.5212   0.04620   0.04003  -0.0729   0.0033   1.0000
  12.500   1.5145   0.04999   0.04394  -0.0727   0.0032   1.0000
  12.750   1.5055   0.05421   0.04828  -0.0727   0.0032   1.0000
  13.000   1.4944   0.05878   0.05298  -0.0729   0.0031   1.0000
  13.250   1.4817   0.06365   0.05798  -0.0732   0.0031   1.0000
  13.500   1.4722   0.06824   0.06269  -0.0736   0.0031   1.0000
  13.750   1.4640   0.07273   0.06731  -0.0741   0.0030   1.0000
  14.000   1.4561   0.07728   0.07198  -0.0747   0.0030   1.0000
  14.250   1.4488   0.08182   0.07664  -0.0754   0.0030   1.0000
  14.500   1.4418   0.08632   0.08126  -0.0760   0.0029   1.0000
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