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GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il)
Reynolds number: 500,000
Max Cl/Cd: 95.15 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe315-il-500000.txt
Download as CSV file: xf-goe315-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3593   0.08690   0.08467  -0.0185   1.0000   0.0215
  -7.750  -0.3588   0.08414   0.08194  -0.0194   1.0000   0.0220
  -7.500  -0.3624   0.08141   0.07926  -0.0208   1.0000   0.0225
  -7.250  -0.3590   0.07734   0.07519  -0.0279   1.0000   0.0228
  -7.000  -0.3506   0.07305   0.07087  -0.0329   1.0000   0.0229
  -6.750  -0.3432   0.06855   0.06633  -0.0356   1.0000   0.0231
  -6.500  -0.3405   0.06554   0.06338  -0.0336   1.0000   0.0233
  -5.750  -0.2545   0.05436   0.05206  -0.0473   0.9668   0.0251
  -5.500  -0.1968   0.04854   0.04587  -0.0584   0.9431   0.0277
  -4.750  -0.1158   0.03783   0.03448  -0.0663   0.8333   0.0290
  -4.500  -0.0957   0.03594   0.03239  -0.0661   0.8111   0.0298
  -4.250  -0.0740   0.03392   0.03016  -0.0659   0.7940   0.0308
  -4.000  -0.0422   0.03251   0.02826  -0.0650   0.7801   0.0337
  -3.750  -0.0241   0.02841   0.02389  -0.0648   0.7679   0.0344
  -3.500  -0.0028   0.02671   0.02210  -0.0645   0.7554   0.0350
  -3.250   0.0201   0.02536   0.02064  -0.0642   0.7433   0.0358
  -3.000   0.0440   0.02405   0.01918  -0.0638   0.7320   0.0370
  -2.750   0.0696   0.02282   0.01772  -0.0631   0.7208   0.0394
  -2.500   0.0960   0.02111   0.01551  -0.0619   0.7092   0.0423
  -2.250   0.1196   0.01965   0.01403  -0.0617   0.6960   0.0434
  -2.000   0.1443   0.01876   0.01304  -0.0613   0.6815   0.0450
  -1.750   0.1700   0.01796   0.01208  -0.0607   0.6664   0.0476
  -1.500   0.1966   0.01704   0.01077  -0.0598   0.6514   0.0528
  -1.250   0.2215   0.01598   0.00969  -0.0594   0.6352   0.0547
  -1.000   0.2473   0.01539   0.00898  -0.0590   0.6186   0.0578
  -0.750   0.2738   0.01489   0.00821  -0.0583   0.6040   0.0655
  -0.500   0.2996   0.01412   0.00743  -0.0581   0.5915   0.0687
  -0.250   0.3278   0.01540   0.00854  -0.0575   0.5803   0.0771
   0.000   0.3550   0.01221   0.00505  -0.0564   0.5717   0.0536
   0.250   0.3819   0.01120   0.00391  -0.0556   0.5632   0.0442
   0.500   0.4083   0.01081   0.00344  -0.0550   0.5547   0.0432
   0.750   0.4346   0.01050   0.00310  -0.0545   0.5465   0.0432
   1.000   0.4605   0.01026   0.00282  -0.0540   0.5383   0.0436
   1.250   0.4869   0.01007   0.00264  -0.0536   0.5300   0.0452
   1.750   0.5394   0.00980   0.00232  -0.0527   0.5118   0.0468
   2.000   0.5658   0.00973   0.00222  -0.0523   0.5018   0.0482
   2.250   0.5922   0.00970   0.00215  -0.0518   0.4909   0.0500
   2.500   0.6189   0.00965   0.00208  -0.0515   0.4792   0.0527
   2.750   0.6455   0.00963   0.00206  -0.0511   0.4674   0.0616
   3.000   0.6997   0.00769   0.00221  -0.0575   0.4511   1.0000
   3.250   0.7250   0.00780   0.00225  -0.0569   0.4361   1.0000
   3.500   0.7500   0.00795   0.00230  -0.0562   0.4162   1.0000
   3.750   0.7745   0.00814   0.00238  -0.0555   0.3912   1.0000
   4.000   0.7985   0.00840   0.00250  -0.0547   0.3625   1.0000
   4.250   0.8220   0.00872   0.00266  -0.0539   0.3315   1.0000
   4.500   0.8451   0.00910   0.00288  -0.0531   0.2998   1.0000
   4.750   0.8683   0.00948   0.00311  -0.0523   0.2737   1.0000
   5.000   0.8920   0.00981   0.00334  -0.0516   0.2536   1.0000
   5.250   0.9157   0.01016   0.00359  -0.0509   0.2353   1.0000
   5.500   0.9394   0.01050   0.00384  -0.0502   0.2168   1.0000
   5.750   0.9633   0.01083   0.00410  -0.0495   0.1984   1.0000
   6.000   0.9863   0.01124   0.00438  -0.0487   0.1735   1.0000
   6.250   1.0023   0.01240   0.00506  -0.0471   0.0888   1.0000
   6.500   1.0216   0.01323   0.00570  -0.0458   0.0502   1.0000
   6.750   1.0437   0.01374   0.00614  -0.0449   0.0428   1.0000
   7.000   1.0665   0.01416   0.00661  -0.0441   0.0405   1.0000
   7.250   1.0888   0.01463   0.00713  -0.0432   0.0389   1.0000
   7.500   1.1104   0.01516   0.00771  -0.0422   0.0375   1.0000
   7.750   1.1310   0.01577   0.00837  -0.0411   0.0362   1.0000
   8.000   1.1497   0.01654   0.00922  -0.0397   0.0347   1.0000
   8.250   1.1692   0.01719   0.00995  -0.0385   0.0340   1.0000
   8.500   1.1883   0.01784   0.01067  -0.0373   0.0334   1.0000
   8.750   1.2061   0.01857   0.01147  -0.0358   0.0327   1.0000
   9.000   1.2227   0.01935   0.01231  -0.0343   0.0317   1.0000
   9.250   1.2379   0.02020   0.01323  -0.0326   0.0308   1.0000
   9.500   1.2508   0.02115   0.01425  -0.0306   0.0299   1.0000
   9.750   1.2608   0.02226   0.01541  -0.0283   0.0291   1.0000
  10.000   1.2649   0.02360   0.01680  -0.0252   0.0284   1.0000
  10.250   1.2618   0.02563   0.01888  -0.0212   0.0276   1.0000
  10.500   1.2741   0.02627   0.01961  -0.0193   0.0270   1.0000
  10.750   1.2842   0.02721   0.02065  -0.0174   0.0265   1.0000
  11.000   1.2932   0.02832   0.02184  -0.0156   0.0258   1.0000
  11.250   1.3015   0.02959   0.02319  -0.0139   0.0252   1.0000
  11.500   1.3096   0.03096   0.02463  -0.0124   0.0246   1.0000
  11.750   1.3173   0.03242   0.02613  -0.0112   0.0239   1.0000
  12.000   1.3244   0.03401   0.02776  -0.0100   0.0231   1.0000
  12.250   1.3337   0.03582   0.02958  -0.0089   0.0225   1.0000
  12.500   1.3452   0.03811   0.03193  -0.0077   0.0216   1.0000
  12.750   1.3482   0.03976   0.03374  -0.0068   0.0212   1.0000
  13.000   1.3528   0.04163   0.03574  -0.0061   0.0207   1.0000
  13.250   1.3567   0.04364   0.03789  -0.0056   0.0202   1.0000
  13.500   1.3608   0.04581   0.04018  -0.0051   0.0197   1.0000
  13.750   1.3644   0.04801   0.04248  -0.0048   0.0192   1.0000
  14.000   1.3681   0.05022   0.04477  -0.0047   0.0188   1.0000
  14.250   1.3702   0.05262   0.04725  -0.0048   0.0184   1.0000
  14.500   1.3712   0.05516   0.04985  -0.0051   0.0180   1.0000
  14.750   1.3742   0.05778   0.05254  -0.0050   0.0177   1.0000
  15.000   1.3739   0.06141   0.05628  -0.0046   0.0171   1.0000
  15.250   1.3651   0.06520   0.06026  -0.0059   0.0169   1.0000
  15.500   1.3576   0.06923   0.06446  -0.0071   0.0168   1.0000
  15.750   1.3481   0.07368   0.06910  -0.0088   0.0165   1.0000
  16.000   1.3375   0.07858   0.07420  -0.0108   0.0163   1.0000
  16.250   1.3273   0.08366   0.07946  -0.0129   0.0161   1.0000
  16.500   1.3151   0.08926   0.08523  -0.0155   0.0159   1.0000
  16.750   1.3019   0.09527   0.09142  -0.0185   0.0157   1.0000
  17.000   1.2874   0.10178   0.09810  -0.0220   0.0156   1.0000
  17.250   1.2704   0.10904   0.10555  -0.0260   0.0155   1.0000
  17.500   1.2543   0.11643   0.11311  -0.0304   0.0155   1.0000
  17.750   1.2346   0.12498   0.12183  -0.0356   0.0154   1.0000
  18.000   1.2123   0.13454   0.13158  -0.0416   0.0155   1.0000
  18.250   1.1860   0.14554   0.14275  -0.0487   0.0157   1.0000
  18.500   1.1551   0.15854   0.15594  -0.0572   0.0159   1.0000
  18.750   1.1186   0.17418   0.17174  -0.0672   0.0164   1.0000
  19.000   1.0585   0.20133   0.19901  -0.0823   0.0175   1.0000
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