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GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il)
Reynolds number: 200,000
Max Cl/Cd: 74.82 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe323-il-200000-n5.txt
Download as CSV file: xf-goe323-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 323 (HANSA-BRANDENBURG V.1) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3087   0.09442   0.08979  -0.0075   0.6445   0.0372
  -7.750  -0.3076   0.09060   0.08601  -0.0143   0.6413   0.0387
  -7.500  -0.3015   0.08603   0.08142  -0.0235   0.6381   0.0389
  -7.250  -0.2890   0.08160   0.07694  -0.0288   0.6349   0.0390
  -7.000  -0.2781   0.07866   0.07400  -0.0274   0.6316   0.0393
  -6.750  -0.2653   0.07586   0.07115  -0.0276   0.6287   0.0396
  -6.500  -0.2507   0.07286   0.06815  -0.0293   0.6251   0.0401
  -6.250  -0.2345   0.06969   0.06495  -0.0320   0.6214   0.0408
  -6.000  -0.2166   0.06636   0.06155  -0.0354   0.6181   0.0416
  -5.750  -0.1855   0.06106   0.05595  -0.0454   0.6154   0.0449
  -5.500  -0.1596   0.05650   0.05106  -0.0503   0.6131   0.0452
  -5.250  -0.1433   0.05334   0.04793  -0.0505   0.6104   0.0455
  -5.000  -0.1242   0.05083   0.04542  -0.0511   0.6072   0.0459
  -4.750  -0.1030   0.04841   0.04294  -0.0520   0.6040   0.0465
  -4.500  -0.0797   0.04594   0.04036  -0.0532   0.6009   0.0472
  -4.250  -0.0550   0.04337   0.03763  -0.0545   0.5981   0.0480
  -3.750   0.0046   0.03326   0.02641  -0.0577   0.5935   0.0389
  -3.500   0.0295   0.03147   0.02456  -0.0580   0.5904   0.0385
  -3.250   0.0556   0.02949   0.02240  -0.0583   0.5875   0.0382
  -3.000   0.0824   0.02749   0.02014  -0.0584   0.5846   0.0380
  -2.750   0.1096   0.02561   0.01796  -0.0584   0.5818   0.0379
  -2.500   0.1377   0.02377   0.01564  -0.0582   0.5793   0.0386
  -2.250   0.1655   0.02244   0.01398  -0.0580   0.5769   0.0391
  -2.000   0.1934   0.02129   0.01265  -0.0580   0.5735   0.0392
  -1.750   0.2212   0.02029   0.01148  -0.0579   0.5692   0.0393
  -1.500   0.2489   0.01942   0.01046  -0.0577   0.5645   0.0396
  -1.250   0.2766   0.01872   0.00960  -0.0574   0.5603   0.0400
  -1.000   0.3048   0.01809   0.00892  -0.0574   0.5552   0.0405
  -0.750   0.3328   0.01753   0.00829  -0.0572   0.5511   0.0411
  -0.500   0.3609   0.01709   0.00777  -0.0570   0.5475   0.0423
  -0.250   0.3889   0.01671   0.00726  -0.0568   0.5443   0.0439
   0.000   0.4170   0.01633   0.00682  -0.0566   0.5403   0.0447
   0.250   0.4449   0.01593   0.00642  -0.0565   0.5360   0.0454
   0.500   0.4724   0.01551   0.00604  -0.0563   0.5318   0.0463
   0.750   0.5000   0.01522   0.00574  -0.0561   0.5282   0.0475
   1.000   0.5277   0.01498   0.00554  -0.0559   0.5239   0.0490
   1.250   0.5555   0.01482   0.00540  -0.0558   0.5188   0.0516
   1.500   0.5831   0.01458   0.00519  -0.0557   0.5141   0.0542
   1.750   0.6107   0.01443   0.00500  -0.0555   0.5098   0.0568
   2.000   0.6386   0.01432   0.00494  -0.0554   0.5038   0.0600
   2.250   0.6663   0.01419   0.00482  -0.0553   0.4979   0.0654
   2.500   0.6940   0.01409   0.00472  -0.0551   0.4924   0.0769
   2.750   0.7159   0.01272   0.00486  -0.0545   0.4855   0.6377
   3.750   0.8364   0.01237   0.00493  -0.0555   0.4531   1.0000
   4.000   0.8634   0.01249   0.00497  -0.0552   0.4445   1.0000
   4.250   0.8905   0.01262   0.00508  -0.0551   0.4339   1.0000
   4.500   0.9173   0.01277   0.00519  -0.0549   0.4224   1.0000
   4.750   0.9438   0.01293   0.00529  -0.0546   0.4094   1.0000
   5.000   0.9701   0.01314   0.00542  -0.0544   0.3952   1.0000
   5.250   0.9959   0.01338   0.00559  -0.0541   0.3809   1.0000
   5.500   1.0214   0.01367   0.00579  -0.0538   0.3676   1.0000
   5.750   1.0467   0.01399   0.00605  -0.0536   0.3548   1.0000
   6.000   1.0718   0.01435   0.00635  -0.0533   0.3429   1.0000
   6.250   1.0965   0.01474   0.00668  -0.0529   0.3316   1.0000
   6.500   1.1205   0.01518   0.00704  -0.0526   0.3205   1.0000
   6.750   1.1449   0.01559   0.00744  -0.0523   0.3095   1.0000
   7.000   1.1689   0.01604   0.00785  -0.0519   0.2995   1.0000
   7.250   1.1924   0.01652   0.00828  -0.0515   0.2903   1.0000
   7.500   1.2164   0.01693   0.00873  -0.0512   0.2825   1.0000
   7.750   1.2398   0.01740   0.00919  -0.0508   0.2754   1.0000
   8.000   1.2631   0.01786   0.00967  -0.0504   0.2692   1.0000
   8.250   1.2863   0.01832   0.01016  -0.0500   0.2627   1.0000
   8.500   1.3079   0.01889   0.01072  -0.0495   0.2566   1.0000
   8.750   1.3308   0.01934   0.01124  -0.0491   0.2501   1.0000
   9.000   1.3518   0.01991   0.01183  -0.0485   0.2436   1.0000
   9.250   1.3728   0.02047   0.01244  -0.0480   0.2376   1.0000
   9.500   1.3934   0.02105   0.01307  -0.0474   0.2315   1.0000
  10.000   1.4313   0.02235   0.01446  -0.0459   0.2199   1.0000
  10.250   1.4479   0.02310   0.01526  -0.0451   0.2136   1.0000
  10.500   1.4636   0.02390   0.01610  -0.0442   0.2072   1.0000
  10.750   1.4762   0.02477   0.01703  -0.0429   0.2003   1.0000
  11.000   1.4860   0.02589   0.01817  -0.0417   0.1945   1.0000
  11.250   1.4975   0.02701   0.01941  -0.0410   0.1883   1.0000
  11.500   1.5053   0.02856   0.02098  -0.0404   0.1827   1.0000
  11.750   1.5154   0.03004   0.02255  -0.0401   0.1768   1.0000
  12.000   1.5229   0.03185   0.02442  -0.0400   0.1704   1.0000
  12.250   1.5294   0.03379   0.02642  -0.0399   0.1646   1.0000
  12.500   1.5367   0.03568   0.02840  -0.0398   0.1584   1.0000
  12.750   1.5391   0.03803   0.03078  -0.0397   0.1529   1.0000
  13.000   1.5458   0.03995   0.03281  -0.0395   0.1470   1.0000
  13.250   1.5468   0.04246   0.03537  -0.0394   0.1405   1.0000
  13.500   1.5489   0.04487   0.03785  -0.0393   0.1332   1.0000
  13.750   1.5464   0.04779   0.04080  -0.0392   0.1262   1.0000
  14.000   1.5466   0.05044   0.04353  -0.0392   0.1189   1.0000
  14.250   1.5424   0.05358   0.04670  -0.0392   0.1124   1.0000
  14.500   1.5384   0.05676   0.04994  -0.0393   0.1059   1.0000
  14.750   1.5319   0.06029   0.05352  -0.0395   0.1002   1.0000
  15.000   1.5244   0.06416   0.05742  -0.0400   0.0943   1.0000
  15.250   1.5162   0.06825   0.06155  -0.0406   0.0893   1.0000
  15.500   1.5091   0.07227   0.06564  -0.0413   0.0848   1.0000
  15.750   1.4984   0.07691   0.07034  -0.0422   0.0809   1.0000
  16.000   1.4922   0.08101   0.07455  -0.0431   0.0761   1.0000
  16.250   1.4802   0.08602   0.07964  -0.0443   0.0709   1.0000
  16.500   1.4721   0.09058   0.08431  -0.0455   0.0643   1.0000
  16.750   1.4592   0.09598   0.08978  -0.0471   0.0543   1.0000
  17.000   1.4353   0.10321   0.09700  -0.0495   0.0421   1.0000
  17.250   1.4112   0.11072   0.10450  -0.0522   0.0345   1.0000
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