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GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il)
Reynolds number: 1,000,000
Max Cl/Cd: 117.18 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe304-il-1000000-n5.txt
Download as CSV file: xf-goe304-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 304 (FRIEDRICHSHAFEN G02) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1930   0.09230   0.09028  -0.0580   0.9034   0.0156
  -9.000  -0.1833   0.09035   0.08827  -0.0587   0.8856   0.0157
  -8.750  -0.1733   0.08839   0.08624  -0.0595   0.8687   0.0159
  -8.500  -0.1632   0.08631   0.08410  -0.0605   0.8533   0.0161
  -8.250  -0.1531   0.08409   0.08182  -0.0618   0.8391   0.0163
  -8.000  -0.1439   0.08156   0.07923  -0.0633   0.8254   0.0165
  -7.750  -0.1348   0.07888   0.07650  -0.0652   0.8121   0.0167
  -7.500  -0.1248   0.07609   0.07367  -0.0677   0.8001   0.0170
  -7.250  -0.1109   0.07289   0.07041  -0.0714   0.7894   0.0172
  -7.000  -0.0965   0.06631   0.06376  -0.0803   0.7783   0.0184
  -6.750  -0.0773   0.06407   0.06147  -0.0831   0.7681   0.0185
  -6.500  -0.0570   0.06171   0.05906  -0.0863   0.7578   0.0186
  -6.250  -0.0352   0.05919   0.05649  -0.0898   0.7472   0.0188
  -6.000  -0.0122   0.05648   0.05372  -0.0936   0.7371   0.0190
  -5.750   0.0122   0.05356   0.05071  -0.0978   0.7264   0.0192
  -5.500   0.0385   0.05040   0.04748  -0.1023   0.7168   0.0194
  -5.000   0.0960   0.04346   0.04034  -0.1118   0.6989   0.0202
  -4.000   0.2266   0.01197   0.00654  -0.1340   0.6723   0.0244
  -3.750   0.2544   0.01123   0.00560  -0.1340   0.6649   0.0246
  -3.500   0.2819   0.01059   0.00479  -0.1340   0.6575   0.0249
  -3.250   0.3100   0.01026   0.00438  -0.1340   0.6508   0.0252
  -3.000   0.3381   0.01009   0.00416  -0.1339   0.6436   0.0255
  -2.750   0.3661   0.00995   0.00397  -0.1338   0.6372   0.0258
  -2.500   0.3943   0.00978   0.00376  -0.1338   0.6306   0.0262
  -2.250   0.4223   0.00958   0.00348  -0.1337   0.6238   0.0265
  -2.000   0.4504   0.00937   0.00321  -0.1336   0.6182   0.0269
  -1.750   0.4786   0.00917   0.00296  -0.1335   0.6115   0.0273
  -1.250   0.5347   0.00887   0.00255  -0.1334   0.5994   0.0280
  -1.000   0.5628   0.00876   0.00240  -0.1333   0.5928   0.0283
  -0.750   0.5906   0.00862   0.00222  -0.1332   0.5863   0.0288
  -0.500   0.6188   0.00854   0.00214  -0.1331   0.5798   0.0294
  -0.250   0.6467   0.00851   0.00208  -0.1330   0.5724   0.0299
   0.000   0.6744   0.00849   0.00204  -0.1328   0.5604   0.0306
   0.250   0.7011   0.00856   0.00200  -0.1325   0.5388   0.0315
   0.500   0.7278   0.00864   0.00198  -0.1322   0.5155   0.0321
   0.750   0.7548   0.00868   0.00194  -0.1320   0.4981   0.0329
   1.000   0.7821   0.00872   0.00195  -0.1318   0.4858   0.0338
   1.250   0.8092   0.00879   0.00197  -0.1316   0.4719   0.0348
   1.500   0.8360   0.00889   0.00201  -0.1313   0.4549   0.0360
   1.750   0.8625   0.00902   0.00206  -0.1310   0.4373   0.0372
   2.000   0.8894   0.00912   0.00213  -0.1307   0.4232   0.0390
   2.250   0.9163   0.00922   0.00219  -0.1305   0.4114   0.0410
   2.500   0.9430   0.00933   0.00227  -0.1303   0.3994   0.0429
   2.750   0.9695   0.00946   0.00236  -0.1300   0.3866   0.0451
   3.000   0.9961   0.00959   0.00245  -0.1297   0.3734   0.0473
   3.250   1.0224   0.00973   0.00256  -0.1294   0.3596   0.0504
   3.500   1.0484   0.00991   0.00268  -0.1290   0.3438   0.0536
   3.750   1.0732   0.01018   0.00285  -0.1285   0.3211   0.0578
   4.000   1.0980   0.01045   0.00304  -0.1280   0.2978   0.0660
   4.250   1.1224   0.01066   0.00331  -0.1275   0.2745   0.1609
   4.750   1.1683   0.00997   0.00397  -0.1262   0.2389   1.0000
   5.000   1.1928   0.01028   0.00419  -0.1256   0.2245   1.0000
   5.250   1.2175   0.01056   0.00440  -0.1251   0.2124   1.0000
   5.500   1.2423   0.01083   0.00461  -0.1245   0.2028   1.0000
   5.750   1.2666   0.01112   0.00485  -0.1240   0.1932   1.0000
   6.000   1.2912   0.01138   0.00507  -0.1234   0.1851   1.0000
   6.250   1.3151   0.01168   0.00532  -0.1228   0.1763   1.0000
   6.500   1.3385   0.01202   0.00559  -0.1221   0.1657   1.0000
   6.750   1.3624   0.01230   0.00584  -0.1215   0.1588   1.0000
   7.000   1.3857   0.01261   0.00612  -0.1207   0.1513   1.0000
   7.250   1.4089   0.01291   0.00640  -0.1200   0.1442   1.0000
   7.500   1.4304   0.01333   0.00674  -0.1190   0.1323   1.0000
   7.750   1.4504   0.01383   0.00714  -0.1178   0.1156   1.0000
   8.000   1.4688   0.01441   0.00761  -0.1163   0.0993   1.0000
   8.250   1.4890   0.01484   0.00801  -0.1152   0.0931   1.0000
   8.500   1.5095   0.01523   0.00839  -0.1140   0.0899   1.0000
   8.750   1.5290   0.01563   0.00879  -0.1127   0.0866   1.0000
   9.000   1.5475   0.01600   0.00917  -0.1112   0.0840   1.0000
   9.250   1.5656   0.01638   0.00958  -0.1096   0.0821   1.0000
   9.500   1.5828   0.01682   0.01003  -0.1080   0.0800   1.0000
   9.750   1.5996   0.01730   0.01051  -0.1063   0.0781   1.0000
  10.000   1.6160   0.01780   0.01103  -0.1046   0.0761   1.0000
  10.250   1.6318   0.01834   0.01160  -0.1029   0.0740   1.0000
  10.500   1.6492   0.01880   0.01210  -0.1014   0.0729   1.0000
  10.750   1.6662   0.01928   0.01262  -0.1000   0.0718   1.0000
  11.000   1.6824   0.01982   0.01321  -0.0985   0.0700   1.0000
  11.250   1.6972   0.02047   0.01388  -0.0969   0.0676   1.0000
  11.500   1.7104   0.02123   0.01464  -0.0951   0.0648   1.0000
  11.750   1.7246   0.02195   0.01540  -0.0936   0.0625   1.0000
  12.000   1.7384   0.02272   0.01620  -0.0920   0.0586   1.0000
  12.250   1.7480   0.02379   0.01723  -0.0901   0.0513   1.0000
  12.500   1.7512   0.02539   0.01873  -0.0877   0.0397   1.0000
  12.750   1.7563   0.02690   0.02024  -0.0856   0.0341   1.0000
  13.000   1.7623   0.02841   0.02177  -0.0837   0.0307   1.0000
  13.250   1.7698   0.02984   0.02325  -0.0821   0.0285   1.0000
  13.500   1.7759   0.03144   0.02489  -0.0805   0.0265   1.0000
  13.750   1.7820   0.03308   0.02657  -0.0790   0.0249   1.0000
  14.000   1.7888   0.03470   0.02825  -0.0777   0.0235   1.0000
  14.250   1.7936   0.03655   0.03015  -0.0764   0.0222   1.0000
  14.500   1.7977   0.03849   0.03214  -0.0751   0.0210   1.0000
  14.750   1.8028   0.04039   0.03411  -0.0740   0.0200   1.0000
  15.000   1.8063   0.04250   0.03629  -0.0730   0.0190   1.0000
  15.250   1.8081   0.04485   0.03869  -0.0720   0.0179   1.0000
  15.500   1.8105   0.04718   0.04109  -0.0712   0.0171   1.0000
  15.750   1.8125   0.04963   0.04361  -0.0705   0.0164   1.0000
  16.000   1.8127   0.05233   0.04637  -0.0698   0.0155   1.0000
  16.250   1.8119   0.05521   0.04932  -0.0692   0.0149   1.0000
  16.500   1.8110   0.05813   0.05231  -0.0688   0.0143   1.0000
  16.750   1.8104   0.06109   0.05536  -0.0685   0.0139   1.0000
  17.000   1.8087   0.06423   0.05859  -0.0682   0.0134   1.0000
  17.250   1.8058   0.06759   0.06203  -0.0681   0.0130   1.0000
  17.500   1.8015   0.07117   0.06569  -0.0681   0.0126   1.0000
  17.750   1.7959   0.07497   0.06957  -0.0683   0.0122   1.0000
  18.000   1.7892   0.07900   0.07369  -0.0685   0.0119   1.0000
  18.250   1.7832   0.08301   0.07780  -0.0690   0.0116   1.0000
  18.500   1.7769   0.08711   0.08199  -0.0695   0.0114   1.0000
  18.750   1.7694   0.09141   0.08640  -0.0702   0.0112   1.0000
  19.000   1.7610   0.09592   0.09102  -0.0710   0.0110   1.0000
  19.250   1.7518   0.10062   0.09581  -0.0720   0.0107   1.0000
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