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GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il)
Reynolds number: 50,000
Max Cl/Cd: 26.2 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe303-il-50000.txt
Download as CSV file: xf-goe303-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2809   0.12274   0.11570  -0.0337   1.0000   0.1337
  -9.250  -0.2950   0.12336   0.11647  -0.0339   1.0000   0.1355
  -9.000  -0.3146   0.12450   0.11778  -0.0334   1.0000   0.1361
  -8.750  -0.2794   0.11506   0.10827  -0.0315   1.0000   0.1419
  -8.500  -0.2809   0.11308   0.10638  -0.0303   1.0000   0.1464
  -8.250  -0.2924   0.11247   0.10590  -0.0289   1.0000   0.1499
  -8.000  -0.3139   0.11308   0.10667  -0.0268   1.0000   0.1515
  -7.750  -0.3376   0.11389   0.10765  -0.0251   1.0000   0.1522
  -7.500  -0.3217   0.10790   0.10167  -0.0226   1.0000   0.1557
  -7.250  -0.3212   0.10532   0.09916  -0.0203   1.0000   0.1598
  -7.000  -0.3311   0.10404   0.09799  -0.0183   1.0000   0.1634
  -6.750  -0.3462   0.10356   0.09764  -0.0180   1.0000   0.1668
  -6.500  -0.3645   0.10444   0.09863  -0.0215   1.0000   0.1687
  -6.250  -0.3579   0.09929   0.09356  -0.0161   1.0000   0.1717
  -6.000  -0.3580   0.09682   0.09115  -0.0136   1.0000   0.1763
  -5.750  -0.3639   0.09553   0.08992  -0.0145   1.0000   0.1822
  -5.500  -0.3674   0.09386   0.08831  -0.0176   1.0000   0.1860
  -5.250  -0.3659   0.09071   0.08524  -0.0130   1.0000   0.1915
  -5.000  -0.3621   0.08984   0.08434  -0.0200   1.0000   0.2011
  -4.750  -0.3622   0.08622   0.08082  -0.0142   1.0000   0.2060
  -4.500  -0.3534   0.08442   0.07898  -0.0191   1.0000   0.2176
  -4.250  -0.3513   0.08151   0.07613  -0.0154   1.0000   0.2241
  -4.000  -0.3410   0.07907   0.07368  -0.0181   1.0000   0.2358
  -3.500  -0.3171   0.07447   0.06904  -0.0216   1.0000   0.2664
  -3.250  -0.3071   0.07205   0.06664  -0.0215   1.0000   0.2835
  -3.000  -0.2991   0.06972   0.06434  -0.0201   1.0000   0.3031
  -2.750  -0.2746   0.06762   0.06220  -0.0232   0.9961   0.3485
  -1.750  -0.2139   0.05691   0.05182  -0.0107   0.9631   0.5809
  -1.500  -0.1997   0.05445   0.04942  -0.0070   0.9552   0.6328
  -1.250  -0.1790   0.05211   0.04710  -0.0059   0.9466   0.6790
  -1.000   0.1441   0.04812   0.03976  -0.0906   0.9305   0.2124
  -0.750   0.1863   0.04681   0.03795  -0.0940   0.9208   0.1964
  -0.500   0.2440   0.04557   0.03600  -0.0995   0.9128   0.1834
  -0.250   0.2737   0.04489   0.03508  -0.1006   0.9025   0.1808
   0.000   0.3145   0.04442   0.03421  -0.1032   0.8932   0.1829
   0.250   0.3536   0.04391   0.03353  -0.1057   0.8839   0.1903
   0.500   0.3832   0.04388   0.03325  -0.1064   0.8736   0.1969
   0.750   0.4347   0.04340   0.03250  -0.1100   0.8654   0.2185
   1.000   0.4560   0.04349   0.03261  -0.1095   0.8541   0.2405
   1.250   0.4922   0.04303   0.03244  -0.1111   0.8445   0.3074
   1.500   0.5292   0.04118   0.03187  -0.1116   0.8352   1.0000
   1.750   0.5508   0.04217   0.03248  -0.1110   0.8226   1.0000
   2.000   0.5782   0.04301   0.03306  -0.1113   0.8099   1.0000
   2.250   0.6104   0.04361   0.03346  -0.1120   0.7963   1.0000
   2.500   0.6446   0.04402   0.03369  -0.1126   0.7820   1.0000
   2.750   0.6811   0.04423   0.03377  -0.1134   0.7678   1.0000
   3.000   0.7273   0.04391   0.03335  -0.1150   0.7550   1.0000
   3.250   0.7520   0.04448   0.03385  -0.1143   0.7403   1.0000
   3.500   0.7763   0.04509   0.03442  -0.1135   0.7257   1.0000
   3.750   0.8011   0.04567   0.03499  -0.1128   0.7111   1.0000
   4.000   0.8266   0.04621   0.03551  -0.1121   0.6966   1.0000
   4.250   0.8541   0.04659   0.03589  -0.1114   0.6822   1.0000
   4.500   0.8857   0.04662   0.03593  -0.1109   0.6684   1.0000
   4.750   0.9471   0.04447   0.03381  -0.1125   0.6596   1.0000
   5.000   0.9727   0.04472   0.03409  -0.1112   0.6443   1.0000
   5.250   0.9990   0.04491   0.03433  -0.1100   0.6290   1.0000
   5.500   1.0243   0.04522   0.03469  -0.1088   0.6138   1.0000
   5.750   1.0485   0.04567   0.03519  -0.1075   0.5986   1.0000
   6.000   1.0721   0.04617   0.03576  -0.1061   0.5835   1.0000
   6.250   1.0942   0.04682   0.03647  -0.1047   0.5687   1.0000
   6.500   1.1144   0.04773   0.03744  -0.1033   0.5546   1.0000
   6.750   1.1802   0.04505   0.03481  -0.1050   0.5467   1.0000
   7.000   1.1824   0.04750   0.03735  -0.1025   0.5322   1.0000
   7.250   1.1732   0.05103   0.04098  -0.0995   0.5181   1.0000
   7.500   1.1438   0.05653   0.04655  -0.0958   0.5047   1.0000
   7.750   1.1561   0.05858   0.04867  -0.0945   0.4956   1.0000
   8.000   1.1372   0.06388   0.05402  -0.0927   0.4851   1.0000
   8.250   1.0390   0.07965   0.06970  -0.0933   0.4728   1.0000
   8.500   1.1135   0.07446   0.06471  -0.0914   0.4673   1.0000
   8.750   1.0116   0.09099   0.08113  -0.0936   0.4614   1.0000
   9.000   1.0022   0.09613   0.08633  -0.0939   0.4566   1.0000
   9.250   0.8774   0.11788   0.10809  -0.1036   0.5388   1.0000
   9.500   0.8971   0.11964   0.10992  -0.1027   0.5195   1.0000
   9.750   0.9200   0.12311   0.11348  -0.1033   0.5139   1.0000
  10.000   1.0176   0.11127   0.10178  -0.0940   0.4352   1.0000
  10.250   0.9973   0.11782   0.10838  -0.0953   0.4342   1.0000
  10.500   0.9826   0.12360   0.11422  -0.0964   0.4332   1.0000
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