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GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il)
Reynolds number: 500,000
Max Cl/Cd: 112.74 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe301-il-500000.txt
Download as CSV file: xf-goe301-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.1368   0.08358   0.08139  -0.0689   0.9739   0.0262
  -7.500  -0.1195   0.07922   0.07702  -0.0709   0.9682   0.0264
  -7.250  -0.0990   0.07613   0.07393  -0.0723   0.9628   0.0268
  -7.000  -0.0781   0.07301   0.07080  -0.0759   0.9546   0.0273
  -6.750  -0.0522   0.06946   0.06722  -0.0815   0.9461   0.0281
  -6.500  -0.0098   0.06336   0.06101  -0.0983   0.9315   0.0306
  -6.250   0.0173   0.05799   0.05556  -0.1054   0.9175   0.0310
  -6.000   0.0358   0.05580   0.05331  -0.1053   0.9021   0.0314
  -5.750   0.0570   0.05346   0.05089  -0.1072   0.8832   0.0319
  -5.500   0.0800   0.05086   0.04818  -0.1100   0.8604   0.0329
  -5.250   0.1317   0.04491   0.04181  -0.1229   0.8359   0.0360
  -5.000   0.1474   0.04155   0.03835  -0.1236   0.8088   0.0365
  -4.750   0.1662   0.04004   0.03669  -0.1234   0.7834   0.0370
  -4.500   0.1842   0.02262   0.01918  -0.1158   0.7284   0.0381
  -4.250   0.2098   0.02033   0.01674  -0.1180   0.7184   0.0398
  -4.000   0.2473   0.01570   0.01166  -0.1237   0.7112   0.0427
  -3.750   0.2686   0.01445   0.01037  -0.1239   0.7026   0.0433
  -3.500   0.2920   0.01334   0.00917  -0.1243   0.6943   0.0443
  -3.250   0.3179   0.01209   0.00778  -0.1252   0.6868   0.0459
  -3.000   0.3528   0.00968   0.00479  -0.1271   0.6803   0.0502
  -2.750   0.3768   0.00868   0.00374  -0.1276   0.6731   0.0509
  -2.500   0.4024   0.00797   0.00298  -0.1279   0.6655   0.0519
  -2.250   0.4285   0.00742   0.00229  -0.1281   0.6586   0.0538
  -2.000   0.4595   0.00750   0.00198  -0.1276   0.6509   0.0585
  -1.750   0.4860   0.00583   0.00013  -0.1288   0.6447   0.0602
  -1.500   0.5320   0.01518   0.00882  -0.1347   0.6476   0.0482
  -1.250   0.5600   0.01407   0.00744  -0.1346   0.6403   0.0474
  -1.000   0.5882   0.01321   0.00641  -0.1344   0.6324   0.0477
  -0.750   0.6158   0.01255   0.00556  -0.1342   0.6248   0.0480
  -0.500   0.6436   0.01206   0.00498  -0.1340   0.6162   0.0487
  -0.250   0.6709   0.01184   0.00463  -0.1337   0.6078   0.0495
   0.000   0.6980   0.01122   0.00400  -0.1335   0.5976   0.0513
   0.250   0.7249   0.01112   0.00387  -0.1332   0.5866   0.0535
   0.500   0.7516   0.01099   0.00368  -0.1329   0.5755   0.0556
   0.750   0.7790   0.01086   0.00353  -0.1326   0.5648   0.0579
   1.000   0.8059   0.01062   0.00326  -0.1324   0.5545   0.0611
   1.250   0.8325   0.01061   0.00322  -0.1321   0.5432   0.0655
   1.500   0.8594   0.01055   0.00313  -0.1318   0.5306   0.0706
   1.750   0.8861   0.01050   0.00307  -0.1316   0.5180   0.0772
   2.000   0.9126   0.01050   0.00302  -0.1312   0.5051   0.0850
   2.250   0.9388   0.01056   0.00303  -0.1309   0.4925   0.0940
   2.500   0.9651   0.01061   0.00306  -0.1306   0.4810   0.1088
   2.750   0.9880   0.00909   0.00336  -0.1300   0.4716   1.0000
   3.000   1.0140   0.00930   0.00344  -0.1296   0.4622   1.0000
   3.250   1.0404   0.00948   0.00354  -0.1293   0.4530   1.0000
   3.500   1.0664   0.00968   0.00367  -0.1289   0.4447   1.0000
   3.750   1.0927   0.00986   0.00380  -0.1286   0.4368   1.0000
   4.000   1.1185   0.01008   0.00396  -0.1282   0.4295   1.0000
   4.250   1.1446   0.01026   0.00411  -0.1279   0.4215   1.0000
   4.500   1.1700   0.01050   0.00429  -0.1275   0.4141   1.0000
   4.750   1.1962   0.01067   0.00445  -0.1272   0.4071   1.0000
   5.000   1.2212   0.01092   0.00465  -0.1267   0.4000   1.0000
   5.250   1.2472   0.01108   0.00483  -0.1264   0.3928   1.0000
   5.500   1.2720   0.01133   0.00503  -0.1259   0.3851   1.0000
   5.750   1.2976   0.01151   0.00523  -0.1255   0.3774   1.0000
   6.000   1.3221   0.01176   0.00545  -0.1250   0.3695   1.0000
   6.250   1.3472   0.01196   0.00567  -0.1246   0.3618   1.0000
   6.500   1.3712   0.01222   0.00590  -0.1240   0.3535   1.0000
   6.750   1.3959   0.01244   0.00613  -0.1235   0.3455   1.0000
   7.000   1.4191   0.01274   0.00641  -0.1228   0.3367   1.0000
   7.250   1.4434   0.01296   0.00666  -0.1222   0.3275   1.0000
   7.500   1.4661   0.01327   0.00695  -0.1214   0.3182   1.0000
   7.750   1.4887   0.01358   0.00726  -0.1206   0.3082   1.0000
   8.000   1.5113   0.01389   0.00757  -0.1198   0.2987   1.0000
   8.250   1.5322   0.01427   0.00793  -0.1188   0.2880   1.0000
   8.500   1.5524   0.01469   0.00831  -0.1176   0.2761   1.0000
   8.750   1.5727   0.01509   0.00871  -0.1164   0.2645   1.0000
   9.000   1.5915   0.01555   0.00915  -0.1151   0.2521   1.0000
   9.250   1.6090   0.01606   0.00962  -0.1135   0.2398   1.0000
   9.500   1.6241   0.01660   0.01013  -0.1114   0.2292   1.0000
   9.750   1.6399   0.01712   0.01065  -0.1095   0.2187   1.0000
  10.000   1.6549   0.01768   0.01121  -0.1076   0.2071   1.0000
  10.250   1.6687   0.01832   0.01183  -0.1055   0.1956   1.0000
  10.500   1.6814   0.01902   0.01251  -0.1033   0.1837   1.0000
  10.750   1.6928   0.01982   0.01327  -0.1010   0.1696   1.0000
  11.000   1.7027   0.02072   0.01412  -0.0986   0.1561   1.0000
  11.250   1.7114   0.02171   0.01508  -0.0962   0.1455   1.0000
  11.500   1.7214   0.02266   0.01604  -0.0940   0.1375   1.0000
  11.750   1.7292   0.02377   0.01717  -0.0917   0.1305   1.0000
  12.000   1.7373   0.02492   0.01835  -0.0895   0.1239   1.0000
  12.250   1.7436   0.02625   0.01971  -0.0874   0.1172   1.0000
  12.500   1.7487   0.02772   0.02120  -0.0853   0.1093   1.0000
  12.750   1.7536   0.02929   0.02279  -0.0833   0.0989   1.0000
  13.000   1.7490   0.03172   0.02511  -0.0809   0.0736   1.0000
  13.250   1.7283   0.03582   0.02901  -0.0779   0.0493   1.0000
  13.500   1.7140   0.03967   0.03286  -0.0760   0.0378   1.0000
  13.750   1.7039   0.04336   0.03658  -0.0747   0.0303   1.0000
  14.000   1.6956   0.04700   0.04028  -0.0738   0.0263   1.0000
  14.250   1.6897   0.05048   0.04385  -0.0731   0.0242   1.0000
  14.500   1.6827   0.05422   0.04768  -0.0726   0.0227   1.0000
  14.750   1.6726   0.05840   0.05196  -0.0723   0.0215   1.0000
  15.000   1.6642   0.06250   0.05617  -0.0722   0.0207   1.0000
  15.250   1.6568   0.06657   0.06037  -0.0723   0.0200   1.0000
  15.500   1.6480   0.07092   0.06484  -0.0725   0.0194   1.0000
  15.750   1.6374   0.07560   0.06963  -0.0729   0.0188   1.0000
  16.000   1.6247   0.08072   0.07486  -0.0736   0.0184   1.0000
  16.250   1.6108   0.08614   0.08040  -0.0745   0.0179   1.0000
  16.500   1.5948   0.09198   0.08636  -0.0756   0.0176   1.0000
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