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GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il)
Reynolds number: 1,000,000
Max Cl/Cd: 104.55 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe315-il-1000000.txt
Download as CSV file: xf-goe315-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 315 (HANSA-BRANDENBURG III.5) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3849   0.09639   0.09474  -0.0159   1.0000   0.0156
  -8.750  -0.3842   0.09283   0.09121  -0.0181   1.0000   0.0156
  -8.500  -0.3837   0.08946   0.08786  -0.0200   1.0000   0.0156
  -8.250  -0.3805   0.08578   0.08419  -0.0194   1.0000   0.0159
  -8.000  -0.3789   0.08312   0.08156  -0.0197   1.0000   0.0159
  -7.750  -0.3789   0.08084   0.07931  -0.0197   1.0000   0.0160
  -7.500  -0.3755   0.07816   0.07664  -0.0209   1.0000   0.0162
  -7.250  -0.3700   0.07535   0.07385  -0.0225   1.0000   0.0164
  -7.000  -0.3520   0.07178   0.07028  -0.0273   0.9965   0.0168
  -6.750  -0.3263   0.06729   0.06575  -0.0343   0.9756   0.0176
  -6.500  -0.2589   0.05659   0.05479  -0.0567   0.9436   0.0190
  -5.750  -0.2018   0.04666   0.04413  -0.0630   0.7924   0.0197
  -5.500  -0.1840   0.04444   0.04177  -0.0634   0.7749   0.0200
  -5.250  -0.1645   0.04212   0.03931  -0.0639   0.7615   0.0206
  -5.000  -0.1359   0.03843   0.03532  -0.0647   0.7509   0.0229
  -4.750  -0.1136   0.03539   0.03206  -0.0646   0.7408   0.0230
  -4.500  -0.0976   0.03051   0.02693  -0.0647   0.7321   0.0233
  -4.250  -0.0765   0.02888   0.02518  -0.0645   0.7226   0.0236
  -4.000  -0.0539   0.02754   0.02376  -0.0643   0.7134   0.0239
  -3.750  -0.0306   0.02616   0.02226  -0.0641   0.7043   0.0244
  -3.500  -0.0065   0.02473   0.02070  -0.0637   0.6943   0.0252
  -3.250   0.0234   0.02330   0.01892  -0.0625   0.6835   0.0277
  -3.000   0.0476   0.02153   0.01689  -0.0617   0.6709   0.0278
  -2.750   0.0678   0.01805   0.01315  -0.0611   0.6574   0.0286
  -2.500   0.0927   0.01719   0.01218  -0.0607   0.6411   0.0290
  -2.250   0.1180   0.01643   0.01129  -0.0603   0.6224   0.0296
  -2.000   0.1434   0.01572   0.01041  -0.0598   0.6008   0.0306
  -1.750   0.1711   0.01589   0.01035  -0.0591   0.5789   0.0335
  -1.500   0.1976   0.01548   0.00970  -0.0585   0.5631   0.0338
  -1.250   0.2211   0.01298   0.00701  -0.0579   0.5529   0.0356
  -1.000   0.2477   0.01250   0.00647  -0.0577   0.5441   0.0365
  -0.750   0.2744   0.01210   0.00598  -0.0573   0.5361   0.0380
  -0.500   0.3018   0.01186   0.00566  -0.0570   0.5289   0.0400
  -0.250   0.3296   0.01248   0.00618  -0.0566   0.5212   0.0415
   0.000   0.3555   0.00992   0.00345  -0.0557   0.5155   0.0327
   0.250   0.3819   0.00946   0.00293  -0.0552   0.5082   0.0324
   0.500   0.4086   0.00917   0.00261  -0.0548   0.5011   0.0328
   0.750   0.4352   0.00897   0.00238  -0.0544   0.4931   0.0331
   1.000   0.4619   0.00879   0.00218  -0.0541   0.4862   0.0333
   1.250   0.4884   0.00867   0.00202  -0.0537   0.4758   0.0335
   1.500   0.5155   0.00857   0.00192  -0.0534   0.4679   0.0338
   1.750   0.5415   0.00832   0.00161  -0.0529   0.4588   0.0352
   2.000   0.5684   0.00823   0.00150  -0.0526   0.4467   0.0362
   2.250   0.5952   0.00821   0.00145  -0.0523   0.4329   0.0376
   2.500   0.6220   0.00824   0.00143  -0.0520   0.4162   0.0392
   2.750   0.6483   0.00833   0.00143  -0.0517   0.3923   0.0408
   3.000   0.6741   0.00848   0.00146  -0.0513   0.3626   0.0441
   3.250   0.6981   0.00840   0.00162  -0.0507   0.3304   0.2477
   3.500   0.7517   0.00719   0.00193  -0.0572   0.2839   1.0000
   3.750   0.7755   0.00749   0.00209  -0.0565   0.2583   1.0000
   4.000   0.7993   0.00779   0.00225  -0.0557   0.2359   1.0000
   4.250   0.8234   0.00807   0.00242  -0.0550   0.2162   1.0000
   4.500   0.8477   0.00832   0.00259  -0.0543   0.1992   1.0000
   4.750   0.8710   0.00867   0.00278  -0.0535   0.1732   1.0000
   5.000   0.8875   0.00974   0.00337  -0.0517   0.0828   1.0000
   5.250   0.9083   0.01039   0.00381  -0.0505   0.0417   1.0000
   5.500   0.9322   0.01070   0.00408  -0.0498   0.0361   1.0000
   5.750   0.9567   0.01095   0.00433  -0.0491   0.0341   1.0000
   6.000   0.9810   0.01121   0.00461  -0.0485   0.0333   1.0000
   6.250   1.0051   0.01149   0.00493  -0.0478   0.0323   1.0000
   6.500   1.0289   0.01182   0.00528  -0.0471   0.0313   1.0000
   6.750   1.0523   0.01217   0.00565  -0.0463   0.0304   1.0000
   7.000   1.0753   0.01257   0.00608  -0.0455   0.0295   1.0000
   7.250   1.0974   0.01305   0.00661  -0.0446   0.0285   1.0000
   7.500   1.1181   0.01367   0.00730  -0.0435   0.0275   1.0000
   7.750   1.1411   0.01402   0.00768  -0.0427   0.0272   1.0000
   8.000   1.1635   0.01443   0.00812  -0.0419   0.0267   1.0000
   8.250   1.1853   0.01487   0.00861  -0.0410   0.0262   1.0000
   8.500   1.2066   0.01534   0.00912  -0.0400   0.0254   1.0000
   8.750   1.2274   0.01584   0.00966  -0.0390   0.0247   1.0000
   9.000   1.2472   0.01640   0.01026  -0.0379   0.0240   1.0000
   9.250   1.2657   0.01703   0.01093  -0.0366   0.0233   1.0000
   9.500   1.2798   0.01798   0.01192  -0.0347   0.0225   1.0000
   9.750   1.2887   0.01925   0.01328  -0.0322   0.0217   1.0000
  10.000   1.3088   0.01963   0.01370  -0.0311   0.0214   1.0000
  10.250   1.3271   0.02010   0.01423  -0.0299   0.0209   1.0000
  10.500   1.3437   0.02065   0.01483  -0.0284   0.0203   1.0000
  10.750   1.3587   0.02117   0.01539  -0.0266   0.0197   1.0000
  11.000   1.3696   0.02180   0.01606  -0.0242   0.0192   1.0000
  11.250   1.3820   0.02237   0.01666  -0.0222   0.0187   1.0000
  11.500   1.3920   0.02310   0.01744  -0.0201   0.0182   1.0000
  11.750   1.3966   0.02422   0.01860  -0.0176   0.0178   1.0000
  12.000   1.3839   0.02672   0.02121  -0.0141   0.0172   1.0000
  12.250   1.3963   0.02760   0.02216  -0.0131   0.0170   1.0000
  12.500   1.4081   0.02862   0.02325  -0.0123   0.0167   1.0000
  12.750   1.4175   0.02992   0.02462  -0.0116   0.0163   1.0000
  13.000   1.4274   0.03127   0.02606  -0.0111   0.0158   1.0000
  13.250   1.4397   0.03247   0.02731  -0.0108   0.0153   1.0000
  13.500   1.4492   0.03398   0.02888  -0.0106   0.0149   1.0000
  13.750   1.4580   0.03562   0.03057  -0.0105   0.0146   1.0000
  14.000   1.4621   0.03780   0.03281  -0.0104   0.0144   1.0000
  14.250   1.4667   0.04001   0.03508  -0.0105   0.0140   1.0000
  14.500   1.4605   0.04346   0.03861  -0.0108   0.0137   1.0000
  14.750   1.4484   0.04765   0.04293  -0.0111   0.0135   1.0000
  15.000   1.4531   0.05011   0.04547  -0.0116   0.0133   1.0000
  15.250   1.4557   0.05285   0.04830  -0.0122   0.0130   1.0000
  15.500   1.4518   0.05637   0.05193  -0.0129   0.0129   1.0000
  15.750   1.4508   0.05962   0.05527  -0.0138   0.0126   1.0000
  16.000   1.4492   0.06304   0.05878  -0.0147   0.0123   1.0000
  16.250   1.4454   0.06685   0.06268  -0.0159   0.0122   1.0000
  16.500   1.4424   0.07065   0.06656  -0.0171   0.0119   1.0000
  16.750   1.4409   0.07435   0.07034  -0.0185   0.0117   1.0000
  17.000   1.4344   0.07879   0.07488  -0.0201   0.0116   1.0000
  17.250   1.4349   0.08245   0.07859  -0.0216   0.0113   1.0000
  17.500   1.4251   0.08751   0.08375  -0.0235   0.0113   1.0000
  17.750   1.4180   0.09238   0.08870  -0.0255   0.0111   1.0000
  18.000   1.4105   0.09744   0.09382  -0.0277   0.0109   1.0000
  18.250   1.4004   0.10288   0.09934  -0.0301   0.0107   1.0000
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