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GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il)
Reynolds number: 1,000,000
Max Cl/Cd: 117.55 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe174-il-1000000-n5.txt
Download as CSV file: xf-goe174-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 174 (ALBATROS 5020) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3282   0.12025   0.11858  -0.0218   1.0000   0.0048
 -10.500  -0.3228   0.11734   0.11568  -0.0226   1.0000   0.0049
 -10.250  -0.3180   0.11425   0.11261  -0.0234   1.0000   0.0050
  -7.750  -0.2292   0.07570   0.07362  -0.0524   0.8357   0.0068
  -6.250  -0.0949   0.01790   0.01396  -0.1134   0.7587   0.0144
  -6.000  -0.0689   0.01782   0.01372  -0.1131   0.7234   0.0146
  -5.750  -0.0438   0.01786   0.01351  -0.1126   0.6711   0.0148
  -5.500  -0.0179   0.01795   0.01343  -0.1123   0.6390   0.0151
  -5.250   0.0088   0.01765   0.01298  -0.1123   0.6221   0.0156
  -5.000   0.0357   0.01554   0.01044  -0.1127   0.6127   0.0171
  -4.750   0.0628   0.01378   0.00825  -0.1128   0.6047   0.0183
  -4.500   0.0905   0.01355   0.00796  -0.1129   0.5970   0.0186
  -4.250   0.1182   0.01333   0.00766  -0.1129   0.5899   0.0189
  -4.000   0.1461   0.01303   0.00727  -0.1129   0.5842   0.0193
  -3.750   0.1740   0.01276   0.00692  -0.1129   0.5774   0.0197
  -3.500   0.2018   0.01241   0.00646  -0.1129   0.5706   0.0203
  -3.250   0.2299   0.01190   0.00581  -0.1129   0.5636   0.0208
  -2.750   0.2861   0.01112   0.00480  -0.1129   0.5508   0.0219
  -2.500   0.3141   0.01095   0.00453  -0.1128   0.5431   0.0224
  -2.250   0.3422   0.01073   0.00423  -0.1128   0.5346   0.0227
  -2.000   0.3701   0.01058   0.00398  -0.1127   0.5227   0.0228
  -1.750   0.3975   0.01005   0.00335  -0.1126   0.5077   0.0232
  -1.500   0.4251   0.00975   0.00296  -0.1126   0.4920   0.0235
  -1.250   0.4527   0.00956   0.00271  -0.1125   0.4777   0.0238
  -1.000   0.4802   0.00943   0.00251  -0.1124   0.4621   0.0240
  -0.750   0.5077   0.00936   0.00236  -0.1123   0.4441   0.0244
  -0.500   0.5350   0.00934   0.00225  -0.1121   0.4253   0.0248
  -0.250   0.5623   0.00932   0.00214  -0.1120   0.4081   0.0251
   0.000   0.5897   0.00930   0.00205  -0.1119   0.3926   0.0255
   0.250   0.6172   0.00930   0.00198  -0.1118   0.3785   0.0259
   0.500   0.6446   0.00932   0.00194  -0.1117   0.3655   0.0265
   0.750   0.6721   0.00935   0.00191  -0.1116   0.3540   0.0271
   1.000   0.6994   0.00941   0.00191  -0.1115   0.3433   0.0277
   1.250   0.7270   0.00945   0.00191  -0.1114   0.3346   0.0281
   1.500   0.7544   0.00950   0.00193  -0.1113   0.3272   0.0285
   1.750   0.7818   0.00956   0.00196  -0.1112   0.3187   0.0288
   2.000   0.8092   0.00963   0.00200  -0.1111   0.3124   0.0290
   2.250   0.8367   0.00968   0.00203  -0.1110   0.3054   0.0303
   2.500   0.8638   0.00979   0.00208  -0.1109   0.2964   0.0317
   3.000   0.9182   0.00997   0.00224  -0.1107   0.2833   0.0360
   3.250   0.9456   0.00988   0.00239  -0.1107   0.2764   0.1868
   3.500   0.9724   0.00998   0.00252  -0.1106   0.2685   0.2213
   3.750   0.9997   0.00954   0.00277  -0.1110   0.2632   0.5658
   4.250   1.0496   0.00901   0.00306  -0.1098   0.2512   1.0000
   4.500   1.0763   0.00918   0.00320  -0.1097   0.2438   1.0000
   4.750   1.1026   0.00938   0.00336  -0.1095   0.2342   1.0000
   5.000   1.1286   0.00962   0.00353  -0.1092   0.2236   1.0000
   5.250   1.1544   0.00987   0.00373  -0.1089   0.2114   1.0000
   5.500   1.1796   0.01017   0.00395  -0.1086   0.1967   1.0000
   5.750   1.2039   0.01056   0.00424  -0.1081   0.1756   1.0000
   6.000   1.2228   0.01153   0.00489  -0.1068   0.1219   1.0000
   6.250   1.2470   0.01191   0.00521  -0.1063   0.1105   1.0000
   6.500   1.2715   0.01225   0.00551  -0.1058   0.1036   1.0000
   6.750   1.2961   0.01255   0.00580  -0.1054   0.0961   1.0000
   7.000   1.3154   0.01341   0.00644  -0.1042   0.0560   1.0000
   7.250   1.3390   0.01379   0.00681  -0.1036   0.0510   1.0000
   7.500   1.3625   0.01417   0.00720  -0.1030   0.0455   1.0000
   7.750   1.3864   0.01448   0.00754  -0.1024   0.0426   1.0000
   8.000   1.4086   0.01496   0.00800  -0.1017   0.0355   1.0000
   8.250   1.4272   0.01575   0.00865  -0.1003   0.0156   1.0000
   8.500   1.4485   0.01625   0.00917  -0.0994   0.0120   1.0000
   8.750   1.4702   0.01669   0.00964  -0.0986   0.0107   1.0000
   9.000   1.4909   0.01719   0.01017  -0.0976   0.0095   1.0000
   9.250   1.5110   0.01772   0.01074  -0.0965   0.0084   1.0000
   9.500   1.5312   0.01820   0.01126  -0.0955   0.0078   1.0000
   9.750   1.5504   0.01873   0.01182  -0.0943   0.0071   1.0000
  10.000   1.5682   0.01933   0.01245  -0.0929   0.0065   1.0000
  10.250   1.5843   0.02000   0.01319  -0.0912   0.0060   1.0000
  10.500   1.6004   0.02059   0.01383  -0.0896   0.0057   1.0000
  10.750   1.6134   0.02122   0.01452  -0.0873   0.0054   1.0000
  11.000   1.6254   0.02192   0.01527  -0.0851   0.0052   1.0000
  11.250   1.6365   0.02269   0.01610  -0.0828   0.0049   1.0000
  11.500   1.6463   0.02357   0.01705  -0.0805   0.0047   1.0000
  11.750   1.6547   0.02458   0.01813  -0.0781   0.0044   1.0000
  12.000   1.6607   0.02583   0.01945  -0.0758   0.0042   1.0000
  12.250   1.6662   0.02722   0.02092  -0.0736   0.0041   1.0000
  12.500   1.6732   0.02858   0.02237  -0.0719   0.0040   1.0000
  12.750   1.6795   0.03009   0.02397  -0.0704   0.0038   1.0000
  13.000   1.6846   0.03182   0.02579  -0.0690   0.0037   1.0000
  13.250   1.6881   0.03379   0.02785  -0.0678   0.0036   1.0000
  13.500   1.6906   0.03597   0.03012  -0.0668   0.0035   1.0000
  13.750   1.6914   0.03845   0.03270  -0.0659   0.0034   1.0000
  14.000   1.6909   0.04119   0.03554  -0.0653   0.0033   1.0000
  14.250   1.6892   0.04425   0.03871  -0.0651   0.0032   1.0000
  14.500   1.6861   0.04762   0.04218  -0.0650   0.0031   1.0000
  14.750   1.6808   0.05138   0.04605  -0.0652   0.0031   1.0000
  15.000   1.6739   0.05543   0.05021  -0.0656   0.0030   1.0000
  15.250   1.6649   0.05980   0.05469  -0.0660   0.0030   1.0000
  15.500   1.6540   0.06449   0.05949  -0.0667   0.0029   1.0000
  15.750   1.6412   0.06962   0.06474  -0.0675   0.0029   1.0000
  16.000   1.6273   0.07501   0.07025  -0.0686   0.0028   1.0000
  16.250   1.6123   0.08069   0.07604  -0.0699   0.0028   1.0000
  16.500   1.5961   0.08671   0.08218  -0.0714   0.0028   1.0000
  16.750   1.5807   0.09270   0.08830  -0.0730   0.0027   1.0000
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