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GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il)
Reynolds number: 500,000
Max Cl/Cd: 95.53 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe346-il-500000.txt
Download as CSV file: xf-goe346-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3326   0.09111   0.08893  -0.0226   1.0000   0.0185
  -8.500  -0.3334   0.08768   0.08551  -0.0246   1.0000   0.0185
  -8.000  -0.4139   0.09395   0.09169  -0.0200   1.0000   0.0185
  -7.750  -0.4035   0.08997   0.08772  -0.0256   1.0000   0.0185
  -7.500  -0.3978   0.08548   0.08325  -0.0250   1.0000   0.0187
  -7.250  -0.3908   0.08221   0.08000  -0.0239   1.0000   0.0189
  -7.000  -0.3828   0.07928   0.07708  -0.0247   1.0000   0.0192
  -6.750  -0.3758   0.07654   0.07436  -0.0258   1.0000   0.0195
  -6.500  -0.3717   0.07414   0.07198  -0.0261   1.0000   0.0199
  -6.250  -0.3728   0.07212   0.06998  -0.0251   1.0000   0.0204
  -6.000  -0.3522   0.06842   0.06625  -0.0296   0.9983   0.0214
  -5.750  -0.2944   0.06278   0.06039  -0.0444   0.9951   0.0229
  -5.500  -0.2557   0.05800   0.05545  -0.0513   0.9922   0.0230
  -5.250  -0.2323   0.05210   0.04950  -0.0554   0.9890   0.0235
  -5.000  -0.2059   0.04894   0.04633  -0.0583   0.9865   0.0239
  -4.750  -0.1715   0.04568   0.04300  -0.0627   0.9844   0.0247
  -4.500  -0.1353   0.04239   0.03958  -0.0670   0.9810   0.0260
  -4.250  -0.0860   0.03975   0.03663  -0.0716   0.9771   0.0286
  -4.000  -0.0468   0.03706   0.03368  -0.0746   0.9737   0.0289
  -3.750  -0.0169   0.03154   0.02801  -0.0781   0.9706   0.0296
  -3.500   0.0090   0.02941   0.02583  -0.0793   0.9639   0.0302
  -3.250   0.0384   0.02752   0.02385  -0.0806   0.9586   0.0310
  -3.000   0.0669   0.02578   0.02199  -0.0814   0.9519   0.0321
  -2.750   0.0957   0.02418   0.02022  -0.0816   0.9447   0.0340
  -2.500   0.1287   0.02425   0.01996  -0.0807   0.9374   0.0365
  -2.250   0.1553   0.02111   0.01649  -0.0808   0.9297   0.0372
  -2.000   0.1797   0.01906   0.01440  -0.0810   0.9215   0.0383
  -1.750   0.2050   0.01797   0.01323  -0.0807   0.9133   0.0394
  -1.500   0.2309   0.01703   0.01218  -0.0803   0.9030   0.0410
  -1.250   0.2574   0.01624   0.01123  -0.0796   0.8923   0.0436
  -1.000   0.2852   0.01708   0.01181  -0.0783   0.8802   0.0465
  -0.750   0.3106   0.01433   0.00889  -0.0782   0.8675   0.0489
  -0.500   0.3366   0.01357   0.00806  -0.0778   0.8526   0.0507
  -0.250   0.3634   0.01302   0.00739  -0.0773   0.8378   0.0540
   0.000   0.3915   0.01386   0.00806  -0.0766   0.8243   0.0582
   1.250   0.5289   0.00967   0.00339  -0.0748   0.7546   0.0477
   1.500   0.5561   0.00940   0.00310  -0.0745   0.7386   0.0458
   1.750   0.5831   0.00906   0.00272  -0.0742   0.7220   0.0453
   2.000   0.6101   0.00889   0.00250  -0.0739   0.7025   0.0457
   2.250   0.6367   0.00885   0.00237  -0.0735   0.6745   0.0465
   2.500   0.6632   0.00872   0.00215  -0.0731   0.6395   0.0479
   2.750   0.6890   0.00880   0.00206  -0.0727   0.5913   0.0513
   3.000   0.7143   0.00905   0.00207  -0.0722   0.5378   0.0543
   3.250   0.7399   0.00931   0.00213  -0.0718   0.4921   0.0578
   3.500   0.7656   0.00905   0.00234  -0.0718   0.4419   0.4310
   3.750   0.7862   0.00823   0.00250  -0.0704   0.3859   1.0000
   4.000   0.8108   0.00876   0.00272  -0.0700   0.3299   1.0000
   4.250   0.8358   0.00925   0.00297  -0.0696   0.2847   1.0000
   4.500   0.8612   0.00966   0.00322  -0.0693   0.2506   1.0000
   4.750   0.8868   0.01004   0.00347  -0.0691   0.2223   1.0000
   5.000   0.9123   0.01041   0.00372  -0.0688   0.1980   1.0000
   5.250   0.9376   0.01082   0.00400  -0.0684   0.1723   1.0000
   5.500   0.9621   0.01134   0.00434  -0.0680   0.1326   1.0000
   5.750   0.9828   0.01247   0.00499  -0.0672   0.0544   1.0000
   6.000   1.0071   0.01304   0.00549  -0.0666   0.0430   1.0000
   6.250   1.0315   0.01357   0.00604  -0.0661   0.0390   1.0000
   6.500   1.0550   0.01425   0.00679  -0.0654   0.0355   1.0000
   6.750   1.0789   0.01482   0.00743  -0.0647   0.0337   1.0000
   7.000   1.1025   0.01540   0.00807  -0.0641   0.0316   1.0000
   7.250   1.1249   0.01613   0.00886  -0.0633   0.0297   1.0000
   7.500   1.1451   0.01718   0.00997  -0.0622   0.0277   1.0000
   7.750   1.1630   0.01855   0.01144  -0.0607   0.0259   1.0000
   8.000   1.1862   0.01906   0.01203  -0.0601   0.0246   1.0000
   8.250   1.2076   0.01987   0.01290  -0.0591   0.0232   1.0000
   8.500   1.2282   0.02073   0.01382  -0.0581   0.0220   1.0000
   8.750   1.2474   0.02178   0.01491  -0.0570   0.0209   1.0000
   9.000   1.2604   0.02439   0.01759  -0.0551   0.0195   1.0000
   9.250   1.2826   0.02470   0.01802  -0.0543   0.0188   1.0000
   9.500   1.3025   0.02559   0.01902  -0.0532   0.0179   1.0000
   9.750   1.3211   0.02670   0.02024  -0.0520   0.0171   1.0000
  10.000   1.3389   0.02779   0.02145  -0.0508   0.0164   1.0000
  10.250   1.3557   0.02890   0.02264  -0.0495   0.0158   1.0000
  10.500   1.3706   0.03044   0.02424  -0.0481   0.0153   1.0000
  10.750   1.3792   0.03427   0.02829  -0.0461   0.0146   1.0000
  11.000   1.3914   0.03523   0.02947  -0.0441   0.0143   1.0000
  11.250   1.4010   0.03669   0.03115  -0.0419   0.0138   1.0000
  11.500   1.4068   0.03851   0.03321  -0.0394   0.0133   1.0000
  11.750   1.4065   0.04059   0.03550  -0.0362   0.0130   1.0000
  12.000   1.4036   0.04285   0.03796  -0.0330   0.0127   1.0000
  12.250   1.3986   0.04533   0.04064  -0.0302   0.0125   1.0000
  12.500   1.3926   0.04796   0.04346  -0.0280   0.0123   1.0000
  12.750   1.3846   0.05095   0.04664  -0.0262   0.0122   1.0000
  13.000   1.3749   0.05434   0.05022  -0.0251   0.0121   1.0000
  13.250   1.3646   0.05800   0.05405  -0.0246   0.0120   1.0000
  13.500   1.3502   0.06258   0.05882  -0.0249   0.0119   1.0000
  13.750   1.3334   0.06787   0.06431  -0.0262   0.0119   1.0000
  14.000   1.3100   0.07478   0.07146  -0.0288   0.0119   1.0000
  14.250   1.2712   0.08544   0.08244  -0.0344   0.0121   1.0000
  14.500   1.2329   0.09743   0.09471  -0.0420   0.0124   1.0000
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