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GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.32 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe173-il-1000000-n5.txt
Download as CSV file: xf-goe173-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.1886   0.08641   0.08417  -0.0453   0.7896   0.0041
  -7.500  -0.1805   0.08334   0.08102  -0.0472   0.7697   0.0041
  -7.250  -0.1719   0.08024   0.07786  -0.0496   0.7538   0.0042
  -7.000  -0.1582   0.07667   0.07424  -0.0534   0.7409   0.0043
  -6.750  -0.1420   0.07237   0.06989  -0.0585   0.7303   0.0045
  -6.250  -0.1024   0.06437   0.06179  -0.0690   0.7096   0.0046
  -6.000  -0.0787   0.06005   0.05741  -0.0750   0.7001   0.0046
  -5.750  -0.0515   0.05506   0.05234  -0.0819   0.6911   0.0046
  -5.500  -0.0206   0.04964   0.04684  -0.0895   0.6823   0.0048
  -5.250   0.0089   0.04623   0.04333  -0.0943   0.6729   0.0050
  -4.750   0.1046   0.01456   0.00986  -0.1193   0.6637   0.0078
  -4.500   0.1323   0.01193   0.00675  -0.1198   0.6538   0.0088
  -4.250   0.1597   0.01023   0.00464  -0.1201   0.6439   0.0098
  -4.000   0.1877   0.01027   0.00465  -0.1199   0.6310   0.0111
  -3.750   0.2155   0.01040   0.00473  -0.1198   0.6179   0.0122
  -3.500   0.2432   0.00992   0.00408  -0.1198   0.6054   0.0139
  -3.250   0.2712   0.01030   0.00446  -0.1197   0.5927   0.0147
  -3.000   0.2989   0.01050   0.00460  -0.1196   0.5783   0.0156
  -2.750   0.3266   0.01038   0.00436  -0.1195   0.5644   0.0172
  -2.500   0.3545   0.01029   0.00413  -0.1194   0.5520   0.0188
  -2.250   0.3823   0.01034   0.00409  -0.1193   0.5408   0.0193
  -1.750   0.4378   0.00988   0.00349  -0.1194   0.5192   0.0213
  -1.500   0.4656   0.00976   0.00330  -0.1194   0.5081   0.0222
  -1.250   0.4934   0.00967   0.00313  -0.1193   0.4961   0.0232
  -1.000   0.5210   0.00954   0.00291  -0.1193   0.4827   0.0239
  -0.750   0.5485   0.00941   0.00267  -0.1192   0.4661   0.0244
  -0.500   0.5757   0.00934   0.00248  -0.1191   0.4433   0.0247
  -0.250   0.6026   0.00935   0.00233  -0.1189   0.4137   0.0250
   0.000   0.6290   0.00945   0.00227  -0.1187   0.3809   0.0255
   0.250   0.6559   0.00948   0.00216  -0.1186   0.3566   0.0256
   0.750   0.7103   0.00953   0.00204  -0.1184   0.3276   0.0262
   1.000   0.7377   0.00956   0.00203  -0.1183   0.3186   0.0266
   1.500   0.7927   0.00961   0.00198  -0.1183   0.3042   0.0285
   1.750   0.8201   0.00966   0.00199  -0.1182   0.2978   0.0298
   2.000   0.8476   0.00971   0.00203  -0.1182   0.2929   0.0307
   2.250   0.8750   0.00977   0.00207  -0.1181   0.2879   0.0314
   2.500   0.9022   0.00986   0.00214  -0.1180   0.2828   0.0321
   2.750   0.9295   0.00994   0.00222  -0.1180   0.2788   0.0332
   3.000   0.9567   0.01001   0.00229  -0.1179   0.2748   0.0345
   3.250   0.9838   0.01012   0.00239  -0.1179   0.2702   0.0354
   3.750   1.0333   0.00879   0.00288  -0.1172   0.2630   1.0000
   4.000   1.0604   0.00892   0.00300  -0.1172   0.2598   1.0000
   4.250   1.0873   0.00907   0.00313  -0.1171   0.2566   1.0000
   4.500   1.1141   0.00923   0.00327  -0.1170   0.2533   1.0000
   4.750   1.1407   0.00939   0.00343  -0.1168   0.2486   1.0000
   5.000   1.1672   0.00957   0.00358  -0.1167   0.2413   1.0000
   5.250   1.1933   0.00977   0.00375  -0.1165   0.2345   1.0000
   5.500   1.2195   0.00997   0.00393  -0.1163   0.2268   1.0000
   5.750   1.2451   0.01021   0.00413  -0.1161   0.2166   1.0000
   6.000   1.2699   0.01054   0.00437  -0.1157   0.1998   1.0000
   6.250   1.2928   0.01104   0.00470  -0.1151   0.1707   1.0000
   6.500   1.3009   0.01314   0.00610  -0.1123   0.0554   1.0000
   6.750   1.3192   0.01415   0.00692  -0.1109   0.0137   1.0000
   7.000   1.3431   0.01450   0.00730  -0.1104   0.0104   1.0000
   7.250   1.3667   0.01487   0.00770  -0.1098   0.0089   1.0000
   7.500   1.3892   0.01534   0.00820  -0.1091   0.0071   1.0000
   7.750   1.4122   0.01572   0.00863  -0.1084   0.0064   1.0000
   8.000   1.4345   0.01616   0.00910  -0.1077   0.0057   1.0000
   8.250   1.4557   0.01669   0.00966  -0.1068   0.0050   1.0000
   8.500   1.4766   0.01722   0.01024  -0.1059   0.0046   1.0000
   8.750   1.4975   0.01771   0.01077  -0.1049   0.0041   1.0000
   9.000   1.5177   0.01822   0.01132  -0.1039   0.0037   1.0000
   9.250   1.5368   0.01881   0.01196  -0.1028   0.0034   1.0000
   9.500   1.5527   0.01962   0.01285  -0.1011   0.0031   1.0000
   9.750   1.5699   0.02026   0.01356  -0.0996   0.0030   1.0000
  10.000   1.5854   0.02098   0.01434  -0.0979   0.0028   1.0000
  10.250   1.5973   0.02173   0.01518  -0.0956   0.0027   1.0000
  10.500   1.6076   0.02256   0.01608  -0.0931   0.0025   1.0000
  10.750   1.6170   0.02347   0.01707  -0.0906   0.0024   1.0000
  11.000   1.6254   0.02447   0.01816  -0.0881   0.0023   1.0000
  11.250   1.6328   0.02558   0.01936  -0.0857   0.0022   1.0000
  11.500   1.6396   0.02680   0.02066  -0.0835   0.0021   1.0000
  11.750   1.6445   0.02826   0.02221  -0.0813   0.0020   1.0000
  12.000   1.6459   0.03013   0.02417  -0.0792   0.0019   1.0000
  12.250   1.6410   0.03276   0.02694  -0.0772   0.0018   1.0000
  12.500   1.6438   0.03489   0.02917  -0.0760   0.0018   1.0000
  12.750   1.6450   0.03733   0.03172  -0.0751   0.0018   1.0000
  13.000   1.6449   0.04002   0.03452  -0.0744   0.0017   1.0000
  13.250   1.6419   0.04317   0.03780  -0.0739   0.0017   1.0000
  13.500   1.6370   0.04666   0.04141  -0.0736   0.0016   1.0000
  13.750   1.6301   0.05050   0.04538  -0.0734   0.0016   1.0000
  14.000   1.6215   0.05469   0.04969  -0.0735   0.0016   1.0000
  14.250   1.6115   0.05915   0.05430  -0.0739   0.0015   1.0000
  14.500   1.6004   0.06395   0.05923  -0.0744   0.0015   1.0000
  14.750   1.5887   0.06899   0.06439  -0.0752   0.0015   1.0000
  15.000   1.5759   0.07431   0.06984  -0.0762   0.0015   1.0000
  15.250   1.5625   0.07990   0.07554  -0.0774   0.0015   1.0000
  15.500   1.5500   0.08548   0.08125  -0.0787   0.0014   1.0000
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