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GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il)
Reynolds number: 100,000
Max Cl/Cd: 55.73 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe301-il-100000.txt
Download as CSV file: xf-goe301-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2858   0.10484   0.10059  -0.0206   1.0000   0.0627
  -7.250  -0.3045   0.10465   0.10052  -0.0168   1.0000   0.0632
  -7.000  -0.3261   0.10479   0.10079  -0.0129   1.0000   0.0635
  -6.750  -0.2976   0.10076   0.09673  -0.0220   0.9920   0.0668
  -6.500  -0.2414   0.09716   0.09299  -0.0503   0.9750   0.0693
  -6.250  -0.2268   0.09080   0.08668  -0.0451   0.9726   0.0704
  -6.000  -0.2031   0.08650   0.08237  -0.0469   0.9638   0.0725
  -5.750  -0.1711   0.08237   0.07819  -0.0534   0.9545   0.0760
  -5.500  -0.1119   0.07810   0.07366  -0.0752   0.9411   0.0817
  -5.250  -0.0941   0.07324   0.06887  -0.0733   0.9350   0.0834
  -5.000  -0.0657   0.06956   0.06516  -0.0764   0.9269   0.0867
  -4.500   0.0156   0.06145   0.05678  -0.0928   0.9095   0.0974
  -4.250   0.0662   0.05831   0.05343  -0.1014   0.9035   0.1081
  -4.000   0.0997   0.05408   0.04913  -0.1058   0.8960   0.1122
  -3.750   0.1362   0.05097   0.04596  -0.1094   0.8891   0.1199
  -3.500   0.1859   0.04715   0.04195  -0.1165   0.8853   0.1306
  -3.250   0.2182   0.04487   0.03948  -0.1197   0.8739   0.1445
  -3.000   0.2628   0.04184   0.03631  -0.1245   0.8693   0.1612
  -2.750   0.2911   0.03987   0.03422  -0.1260   0.8579   0.1772
  -2.500   0.3316   0.03725   0.03152  -0.1292   0.8526   0.1992
  -2.250   0.3574   0.03554   0.02972  -0.1299   0.8406   0.2266
  -1.750   0.4106   0.03173   0.02594  -0.1301   0.8225   0.3252
  -1.500   0.4308   0.03010   0.02438  -0.1286   0.8113   0.3767
  -1.250   0.4593   0.02821   0.02249  -0.1281   0.8033   0.4318
  -1.000   0.4866   0.02669   0.02092  -0.1278   0.7918   0.4649
  -0.750   0.5844   0.02514   0.01716  -0.1393   0.7816   0.1516
  -0.500   0.6223   0.02364   0.01517  -0.1398   0.7728   0.1321
  -0.250   0.6517   0.02315   0.01425  -0.1390   0.7603   0.1245
   0.000   0.6806   0.02248   0.01337  -0.1386   0.7487   0.1247
   0.250   0.7115   0.02156   0.01232  -0.1387   0.7386   0.1280
   0.500   0.7390   0.02108   0.01174  -0.1381   0.7265   0.1300
   0.750   0.7654   0.02078   0.01139  -0.1374   0.7142   0.1343
   1.000   0.7931   0.02051   0.01104  -0.1369   0.7032   0.1430
   1.250   0.8202   0.02019   0.01071  -0.1362   0.6922   0.1525
   1.500   0.8452   0.02014   0.01066  -0.1353   0.6797   0.1688
   1.750   0.8723   0.02005   0.01057  -0.1349   0.6686   0.1955
   2.000   0.8990   0.01840   0.01039  -0.1340   0.6587   1.0000
   2.250   0.9234   0.01877   0.01050  -0.1330   0.6463   1.0000
   2.500   0.9493   0.01910   0.01063  -0.1323   0.6355   1.0000
   2.750   0.9770   0.01934   0.01067  -0.1319   0.6256   1.0000
   3.000   1.0005   0.01974   0.01103  -0.1311   0.6141   1.0000
   3.250   1.0272   0.02005   0.01120  -0.1306   0.6049   1.0000
   3.500   1.0525   0.02038   0.01146  -0.1300   0.5948   1.0000
   3.750   1.0768   0.02079   0.01185  -0.1294   0.5849   1.0000
   4.000   1.1044   0.02103   0.01197  -0.1291   0.5765   1.0000
   4.250   1.1270   0.02149   0.01245  -0.1282   0.5660   1.0000
   4.500   1.1551   0.02172   0.01258  -0.1280   0.5581   1.0000
   4.750   1.1774   0.02218   0.01310  -0.1270   0.5478   1.0000
   5.000   1.2028   0.02254   0.01343  -0.1265   0.5391   1.0000
   5.250   1.2281   0.02281   0.01366  -0.1259   0.5294   1.0000
   5.500   1.2507   0.02321   0.01412  -0.1250   0.5190   1.0000
   5.750   1.2787   0.02337   0.01416  -0.1247   0.5101   1.0000
   6.000   1.3000   0.02378   0.01464  -0.1236   0.4991   1.0000
   6.250   1.3231   0.02415   0.01503  -0.1227   0.4885   1.0000
   6.500   1.3509   0.02429   0.01505  -0.1224   0.4789   1.0000
   6.750   1.3709   0.02472   0.01556  -0.1210   0.4671   1.0000
   7.000   1.3928   0.02516   0.01604  -0.1200   0.4561   1.0000
   7.250   1.4195   0.02547   0.01626  -0.1197   0.4465   1.0000
   7.500   1.4388   0.02604   0.01696  -0.1183   0.4357   1.0000
   7.750   1.4606   0.02664   0.01761  -0.1173   0.4259   1.0000
   8.000   1.4862   0.02708   0.01801  -0.1169   0.4166   1.0000
   8.250   1.5030   0.02783   0.01894  -0.1153   0.4062   1.0000
   8.500   1.5272   0.02838   0.01947  -0.1147   0.3970   1.0000
   8.750   1.5460   0.02902   0.02022  -0.1133   0.3869   1.0000
   9.000   1.5641   0.02977   0.02110  -0.1119   0.3771   1.0000
   9.250   1.5902   0.03022   0.02147  -0.1116   0.3679   1.0000
   9.500   1.6015   0.03110   0.02261  -0.1091   0.3575   1.0000
   9.750   1.6214   0.03177   0.02332  -0.1079   0.3481   1.0000
  10.000   1.6407   0.03234   0.02394  -0.1066   0.3381   1.0000
  10.250   1.6515   0.03326   0.02506  -0.1042   0.3278   1.0000
  10.500   1.6714   0.03390   0.02569  -0.1030   0.3182   1.0000
  10.750   1.6849   0.03473   0.02664  -0.1009   0.3084   1.0000
  11.000   1.6954   0.03579   0.02788  -0.0985   0.2990   1.0000
  11.250   1.7152   0.03631   0.02831  -0.0974   0.2891   1.0000
  11.500   1.7173   0.03721   0.02939  -0.0937   0.2792   1.0000
  11.750   1.7204   0.03802   0.03029  -0.0903   0.2695   1.0000
  12.000   1.7278   0.03842   0.03060  -0.0874   0.2592   1.0000
  12.250   1.7183   0.03964   0.03204  -0.0825   0.2507   1.0000
  12.500   1.7181   0.04066   0.03308  -0.0792   0.2419   1.0000
  12.750   1.7150   0.04193   0.03443  -0.0759   0.2334   1.0000
  13.000   1.7112   0.04356   0.03620  -0.0729   0.2259   1.0000
  13.250   1.7096   0.04513   0.03786  -0.0703   0.2185   1.0000
  13.500   1.7051   0.04712   0.04000  -0.0679   0.2117   1.0000
  13.750   1.6995   0.04923   0.04226  -0.0658   0.2046   1.0000
  14.000   1.6935   0.05158   0.04475  -0.0639   0.1978   1.0000
  14.250   1.6832   0.05445   0.04781  -0.0624   0.1907   1.0000
  14.500   1.6743   0.05738   0.05086  -0.0612   0.1837   1.0000
  14.750   1.6602   0.06111   0.05479  -0.0605   0.1764   1.0000
  15.000   1.6457   0.06510   0.05892  -0.0602   0.1687   1.0000
  15.250   1.6297   0.06955   0.06348  -0.0603   0.1604   1.0000
  15.500   1.6097   0.07500   0.06913  -0.0611   0.1519   1.0000
  15.750   1.5899   0.08059   0.07477  -0.0621   0.1423   1.0000
  16.000   1.5686   0.08662   0.08076  -0.0635   0.1319   1.0000
  16.250   1.5439   0.09368   0.08795  -0.0655   0.1217   1.0000
  16.500   1.5197   0.10083   0.09514  -0.0676   0.1108   1.0000
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