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GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il)
Reynolds number: 200,000
Max Cl/Cd: 81.18 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe346-il-200000.txt
Download as CSV file: xf-goe346-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4224   0.10679   0.10313  -0.0121   1.0000   0.0285
  -8.500  -0.4215   0.10508   0.10147  -0.0162   1.0000   0.0287
  -8.250  -0.4184   0.10291   0.09934  -0.0216   1.0000   0.0288
  -7.750  -0.4044   0.09357   0.09005  -0.0222   1.0000   0.0294
  -7.500  -0.3968   0.08965   0.08614  -0.0207   1.0000   0.0298
  -7.250  -0.3889   0.08630   0.08281  -0.0215   1.0000   0.0303
  -7.000  -0.3806   0.08313   0.07966  -0.0231   1.0000   0.0309
  -6.750  -0.3723   0.08005   0.07660  -0.0249   1.0000   0.0316
  -6.500  -0.3643   0.07707   0.07364  -0.0266   1.0000   0.0323
  -6.250  -0.3564   0.07418   0.07076  -0.0281   1.0000   0.0332
  -6.000  -0.3482   0.07143   0.06801  -0.0296   1.0000   0.0343
  -5.750  -0.3225   0.07001   0.06641  -0.0369   1.0000   0.0364
  -5.500  -0.3050   0.06799   0.06421  -0.0394   1.0000   0.0367
  -5.250  -0.2992   0.06335   0.05957  -0.0390   1.0000   0.0370
  -5.000  -0.2968   0.05956   0.05585  -0.0371   1.0000   0.0375
  -4.750  -0.2902   0.05673   0.05305  -0.0358   1.0000   0.0381
  -4.500  -0.2797   0.05418   0.05049  -0.0354   1.0000   0.0389
  -4.250  -0.2656   0.05171   0.04797  -0.0356   1.0000   0.0401
  -4.000  -0.2242   0.04818   0.04427  -0.0412   0.9965   0.0431
  -3.750  -0.1584   0.04629   0.04168  -0.0492   0.9924   0.0468
  -3.500  -0.1324   0.04079   0.03631  -0.0526   0.9886   0.0481
  -3.250  -0.0974   0.03783   0.03329  -0.0562   0.9852   0.0502
  -3.000  -0.0583   0.03537   0.03064  -0.0598   0.9816   0.0538
  -2.750  -0.0136   0.03328   0.02807  -0.0631   0.9766   0.0594
  -2.500   0.0210   0.03046   0.02527  -0.0663   0.9732   0.0619
  -2.250   0.0623   0.02865   0.02328  -0.0697   0.9706   0.0675
  -2.000   0.0983   0.02680   0.02112  -0.0716   0.9644   0.0739
  -1.750   0.1357   0.02508   0.01935  -0.0743   0.9604   0.0803
  -1.500   0.1772   0.02339   0.01747  -0.0776   0.9578   0.0913
  -1.250   0.2140   0.02207   0.01602  -0.0799   0.9529   0.1062
  -1.000   0.2515   0.02100   0.01483  -0.0822   0.9478   0.1251
  -0.750   0.2909   0.01989   0.01361  -0.0850   0.9441   0.1553
  -0.500   0.3245   0.01807   0.01186  -0.0870   0.9373   0.1919
  -0.250   0.3613   0.01691   0.01065  -0.0885   0.9293   0.2287
   0.000   0.3934   0.01595   0.00959  -0.0886   0.9180   0.2450
   0.250   0.4346   0.01550   0.00838  -0.0864   0.9082   0.1017
   0.500   0.4637   0.01470   0.00747  -0.0852   0.8961   0.0839
   0.750   0.4897   0.01373   0.00644  -0.0838   0.8824   0.0765
   1.000   0.5155   0.01345   0.00605  -0.0825   0.8684   0.0720
   1.250   0.5410   0.01298   0.00560  -0.0814   0.8550   0.0709
   1.500   0.5666   0.01248   0.00515  -0.0805   0.8416   0.0707
   1.750   0.5923   0.01210   0.00480  -0.0796   0.8275   0.0712
   2.000   0.6179   0.01161   0.00439  -0.0788   0.8121   0.0762
   2.250   0.6439   0.01138   0.00415  -0.0779   0.7954   0.0798
   2.500   0.6700   0.01123   0.00396  -0.0771   0.7778   0.0835
   2.750   0.6962   0.01112   0.00383  -0.0763   0.7578   0.0930
   3.000   0.7195   0.00931   0.00380  -0.0749   0.7378   1.0000
   3.250   0.7450   0.00943   0.00372  -0.0739   0.7108   1.0000
   3.500   0.7698   0.00959   0.00371  -0.0728   0.6768   1.0000
   3.750   0.7944   0.00979   0.00375  -0.0718   0.6351   1.0000
   4.000   0.8183   0.01008   0.00381  -0.0707   0.5861   1.0000
   4.250   0.8412   0.01054   0.00396  -0.0696   0.5272   1.0000
   4.500   0.8633   0.01112   0.00423  -0.0685   0.4590   1.0000
   4.750   0.8852   0.01179   0.00454  -0.0675   0.3898   1.0000
   5.000   0.9077   0.01245   0.00493  -0.0667   0.3392   1.0000
   5.250   0.9308   0.01308   0.00536  -0.0660   0.3027   1.0000
   5.500   0.9545   0.01362   0.00581  -0.0654   0.2723   1.0000
   5.750   0.9782   0.01415   0.00622  -0.0648   0.2421   1.0000
   6.000   1.0021   0.01466   0.00666  -0.0643   0.2134   1.0000
   6.250   1.0250   0.01532   0.00715  -0.0636   0.1699   1.0000
   6.500   1.0427   0.01681   0.00802  -0.0624   0.0809   1.0000
   6.750   1.0634   0.01791   0.00905  -0.0612   0.0642   1.0000
   7.000   1.0843   0.01889   0.01003  -0.0601   0.0563   1.0000
   7.250   1.1050   0.01986   0.01108  -0.0590   0.0520   1.0000
   7.500   1.1250   0.02091   0.01218  -0.0578   0.0486   1.0000
   7.750   1.1414   0.02252   0.01380  -0.0561   0.0452   1.0000
   8.000   1.1610   0.02382   0.01519  -0.0548   0.0429   1.0000
   8.250   1.1811   0.02523   0.01670  -0.0536   0.0411   1.0000
   8.500   1.2015   0.02679   0.01835  -0.0524   0.0393   1.0000
   8.750   1.2215   0.02849   0.02009  -0.0514   0.0371   1.0000
   9.000   1.2415   0.03219   0.02391  -0.0506   0.0349   1.0000
   9.250   1.2607   0.03437   0.02638  -0.0493   0.0343   1.0000
   9.500   1.2782   0.03661   0.02895  -0.0478   0.0338   1.0000
   9.750   1.2930   0.03924   0.03195  -0.0461   0.0333   1.0000
  10.000   1.3045   0.04178   0.03487  -0.0440   0.0325   1.0000
  10.250   1.3127   0.04448   0.03793  -0.0418   0.0316   1.0000
  10.500   1.3157   0.04797   0.04185  -0.0392   0.0315   1.0000
  10.750   1.3128   0.05200   0.04628  -0.0363   0.0319   1.0000
  11.000   1.3043   0.05625   0.05090  -0.0332   0.0325   1.0000
  11.250   1.2897   0.06037   0.05530  -0.0298   0.0331   1.0000
  11.500   1.2712   0.06470   0.05986  -0.0268   0.0337   1.0000
  11.750   1.1553   0.05891   0.05433  -0.0139   0.0332   1.0000
  12.000   1.1293   0.06403   0.05964  -0.0128   0.0334   1.0000
  12.250   1.1023   0.06971   0.06549  -0.0127   0.0337   1.0000
  12.500   1.0742   0.07602   0.07196  -0.0135   0.0340   1.0000
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