Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il)
Reynolds number: 500,000
Max Cl/Cd: 82.97 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe346-il-500000-n5.txt
Download as CSV file: xf-goe346-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4290   0.09856   0.09624  -0.0118   1.0000   0.0099
  -8.500  -0.4270   0.09430   0.09201  -0.0140   1.0000   0.0102
  -8.250  -0.4243   0.09063   0.08836  -0.0160   1.0000   0.0104
  -8.000  -0.4182   0.08822   0.08598  -0.0171   1.0000   0.0105
  -7.750  -0.4105   0.08561   0.08339  -0.0190   1.0000   0.0108
  -7.500  -0.4008   0.08293   0.08073  -0.0213   1.0000   0.0112
  -7.250  -0.3921   0.07994   0.07775  -0.0238   1.0000   0.0117
  -7.000  -0.3840   0.07650   0.07432  -0.0265   0.9994   0.0123
  -6.750  -0.3575   0.07071   0.06849  -0.0351   0.9938   0.0128
  -6.500  -0.3271   0.06368   0.06137  -0.0453   0.9867   0.0136
  -6.250  -0.3015   0.06122   0.05887  -0.0489   0.9810   0.0139
  -6.000  -0.2729   0.05826   0.05586  -0.0535   0.9758   0.0148
  -5.750  -0.2430   0.05402   0.05153  -0.0589   0.9684   0.0158
  -5.500  -0.2022   0.04603   0.04325  -0.0681   0.9608   0.0173
  -5.250  -0.1787   0.04470   0.04191  -0.0693   0.9536   0.0178
  -5.000  -0.1530   0.04303   0.04018  -0.0709   0.9458   0.0186
  -4.750  -0.1248   0.04026   0.03727  -0.0731   0.9366   0.0195
  -4.500  -0.0966   0.03706   0.03388  -0.0750   0.9260   0.0201
  -4.250  -0.0599   0.03239   0.02880  -0.0770   0.9168   0.0224
  -4.000  -0.0381   0.03070   0.02704  -0.0776   0.9075   0.0231
  -3.750  -0.0136   0.02941   0.02567  -0.0780   0.8998   0.0238
  -3.500   0.0133   0.02746   0.02354  -0.0785   0.8926   0.0243
  -3.250   0.0410   0.02548   0.02138  -0.0789   0.8854   0.0246
  -3.000   0.0689   0.02352   0.01921  -0.0792   0.8782   0.0248
  -2.750   0.0966   0.02207   0.01759  -0.0793   0.8709   0.0259
  -2.500   0.1249   0.02023   0.01552  -0.0794   0.8634   0.0260
  -2.250   0.1534   0.01853   0.01359  -0.0794   0.8557   0.0261
  -2.000   0.1816   0.01710   0.01193  -0.0793   0.8481   0.0265
  -1.750   0.2098   0.01585   0.01048  -0.0792   0.8394   0.0267
  -1.500   0.2376   0.01478   0.00922  -0.0790   0.8289   0.0270
  -1.250   0.2652   0.01400   0.00825  -0.0787   0.8154   0.0277
  -1.000   0.2926   0.01310   0.00715  -0.0784   0.7979   0.0276
  -0.750   0.3196   0.01231   0.00614  -0.0780   0.7763   0.0275
  -0.500   0.3466   0.01168   0.00530  -0.0776   0.7525   0.0276
  -0.250   0.3735   0.01120   0.00462  -0.0772   0.7297   0.0280
   0.000   0.4007   0.01083   0.00411  -0.0769   0.7096   0.0285
   0.250   0.4280   0.01057   0.00375  -0.0767   0.6916   0.0289
   0.500   0.4552   0.01039   0.00349  -0.0765   0.6738   0.0293
   0.750   0.4825   0.01020   0.00323  -0.0764   0.6559   0.0296
   1.000   0.5095   0.00974   0.00269  -0.0762   0.6358   0.0302
   1.250   0.5364   0.00950   0.00239  -0.0760   0.6114   0.0315
   1.500   0.5632   0.00944   0.00225  -0.0758   0.5833   0.0322
   1.750   0.5893   0.00951   0.00214  -0.0755   0.5409   0.0324
   2.000   0.6149   0.00968   0.00209  -0.0752   0.4919   0.0326
   2.250   0.6408   0.00988   0.00208  -0.0749   0.4405   0.0331
   2.500   0.6665   0.01013   0.00212  -0.0747   0.3865   0.0339
   2.750   0.6922   0.01043   0.00221  -0.0744   0.3371   0.0351
   3.000   0.7182   0.01069   0.00231  -0.0742   0.3014   0.0369
   3.250   0.7441   0.01098   0.00245  -0.0740   0.2658   0.0388
   3.500   0.7701   0.01126   0.00259  -0.0738   0.2344   0.0404
   3.750   0.7964   0.01149   0.00273  -0.0736   0.2111   0.0475
   4.000   0.8183   0.00997   0.00304  -0.0729   0.1939   1.0000
   4.500   0.8707   0.01052   0.00342  -0.0724   0.1638   1.0000
   4.750   0.8968   0.01081   0.00364  -0.0722   0.1482   1.0000
   5.000   0.9226   0.01112   0.00389  -0.0719   0.1304   1.0000
   5.250   0.9470   0.01165   0.00421  -0.0715   0.0938   1.0000
   5.750   0.9947   0.01287   0.00511  -0.0705   0.0389   1.0000
   6.000   1.0201   0.01321   0.00549  -0.0702   0.0359   1.0000
   6.250   1.0452   0.01359   0.00590  -0.0698   0.0335   1.0000
   6.500   1.0699   0.01403   0.00637  -0.0693   0.0312   1.0000
   6.750   1.0939   0.01455   0.00695  -0.0688   0.0286   1.0000
   7.000   1.1185   0.01496   0.00741  -0.0683   0.0275   1.0000
   7.250   1.1432   0.01532   0.00782  -0.0679   0.0261   1.0000
   7.500   1.1675   0.01574   0.00830  -0.0675   0.0244   1.0000
   7.750   1.1912   0.01620   0.00882  -0.0669   0.0225   1.0000
   8.000   1.2132   0.01692   0.00957  -0.0662   0.0201   1.0000
   8.250   1.2373   0.01728   0.00999  -0.0657   0.0190   1.0000
   8.500   1.2606   0.01774   0.01051  -0.0651   0.0174   1.0000
   8.750   1.2836   0.01822   0.01101  -0.0645   0.0158   1.0000
   9.000   1.3050   0.01888   0.01170  -0.0637   0.0141   1.0000
   9.250   1.3270   0.01943   0.01234  -0.0630   0.0131   1.0000
   9.500   1.3484   0.02003   0.01299  -0.0622   0.0120   1.0000
   9.750   1.3689   0.02069   0.01370  -0.0613   0.0111   1.0000
  10.000   1.3869   0.02163   0.01470  -0.0600   0.0102   1.0000
  10.250   1.4052   0.02247   0.01567  -0.0588   0.0098   1.0000
  10.500   1.4230   0.02331   0.01662  -0.0575   0.0092   1.0000
  10.750   1.4402   0.02415   0.01756  -0.0562   0.0087   1.0000
  11.000   1.4568   0.02499   0.01848  -0.0548   0.0082   1.0000
  11.250   1.4715   0.02594   0.01951  -0.0533   0.0077   1.0000
  11.500   1.4812   0.02725   0.02093  -0.0510   0.0073   1.0000
  11.750   1.4883   0.02848   0.02229  -0.0483   0.0071   1.0000
  12.000   1.4951   0.02971   0.02368  -0.0457   0.0069   1.0000
  12.250   1.5004   0.03110   0.02522  -0.0432   0.0067   1.0000
  12.500   1.5046   0.03265   0.02692  -0.0409   0.0065   1.0000
  12.750   1.5076   0.03438   0.02880  -0.0387   0.0063   1.0000
  13.000   1.5096   0.03630   0.03086  -0.0368   0.0062   1.0000
  13.250   1.5106   0.03842   0.03313  -0.0352   0.0060   1.0000
  13.500   1.5103   0.04079   0.03565  -0.0338   0.0059   1.0000
  13.750   1.5092   0.04338   0.03838  -0.0329   0.0058   1.0000
  14.000   1.5060   0.04639   0.04155  -0.0323   0.0057   1.0000
  14.250   1.5018   0.04970   0.04501  -0.0321   0.0056   1.0000
  14.500   1.4961   0.05342   0.04888  -0.0324   0.0055   1.0000
  14.750   1.4881   0.05771   0.05332  -0.0333   0.0054   1.0000
  15.000   1.4781   0.06255   0.05832  -0.0347   0.0053   1.0000
  15.250   1.4652   0.06817   0.06410  -0.0368   0.0053   1.0000
  15.500   1.4504   0.07444   0.07054  -0.0395   0.0053   1.0000
  15.750   1.4335   0.08140   0.07766  -0.0427   0.0052   1.0000
  16.000   1.4151   0.08899   0.08542  -0.0464   0.0052   1.0000
  16.250   1.3955   0.09702   0.09360  -0.0504   0.0052   1.0000
  16.500   1.3752   0.10544   0.10218  -0.0546   0.0052   1.0000
  16.750   1.3541   0.11417   0.11106  -0.0590   0.0053   1.0000
  17.000   1.3327   0.12306   0.12009  -0.0635   0.0053   1.0000
  17.250   1.3115   0.13219   0.12937  -0.0683   0.0053   1.0000
  17.500   1.2900   0.14168   0.13899  -0.0734   0.0053   1.0000
  17.750   1.2691   0.15135   0.14880  -0.0788   0.0054   1.0000
<< Back to GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il)

Polar data table (+)

Polar graphs


<< Back to GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il)