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GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il)
Reynolds number: 500,000
Max Cl/Cd: 108.5 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe301-il-500000-n5.txt
Download as CSV file: xf-goe301-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.2706   0.13207   0.12968  -0.0326   1.0000   0.0106
 -11.500  -0.2671   0.12947   0.12710  -0.0327   1.0000   0.0108
 -11.250  -0.2648   0.12667   0.12432  -0.0328   1.0000   0.0109
 -11.000  -0.2550   0.12297   0.12062  -0.0352   0.9990   0.0109
 -10.750  -0.2426   0.11903   0.11669  -0.0383   0.9974   0.0111
 -10.500  -0.2301   0.11511   0.11277  -0.0415   0.9957   0.0113
 -10.250  -0.2181   0.11116   0.10881  -0.0447   0.9939   0.0115
 -10.000  -0.2077   0.10713   0.10477  -0.0477   0.9909   0.0119
  -9.750  -0.1977   0.10267   0.10032  -0.0512   0.9878   0.0126
  -9.250  -0.1694   0.09700   0.09466  -0.0564   0.9789   0.0132
  -9.000  -0.1567   0.09356   0.09123  -0.0594   0.9722   0.0135
  -8.500  -0.1284   0.08588   0.08353  -0.0669   0.9510   0.0143
  -8.250  -0.1158   0.08015   0.07776  -0.0732   0.9343   0.0154
  -8.000  -0.0934   0.07778   0.07532  -0.0767   0.9139   0.0157
  -7.750  -0.0793   0.07530   0.07273  -0.0791   0.8898   0.0161
  -7.500  -0.0676   0.07241   0.06976  -0.0819   0.8641   0.0165
  -7.250  -0.0546   0.06912   0.06635  -0.0855   0.8353   0.0170
  -7.000  -0.0404   0.06205   0.05912  -0.0952   0.8028   0.0184
  -6.750  -0.0230   0.06065   0.05754  -0.0964   0.7694   0.0187
  -6.250   0.0168   0.05620   0.05281  -0.1021   0.7280   0.0197
  -6.000   0.0407   0.05253   0.04902  -0.1072   0.7148   0.0204
  -5.750   0.0739   0.04490   0.04117  -0.1181   0.7049   0.0222
  -5.500   0.0971   0.04363   0.03981  -0.1193   0.6944   0.0225
  -5.250   0.1230   0.04148   0.03756  -0.1217   0.6849   0.0230
  -5.000   0.1511   0.03854   0.03446  -0.1249   0.6771   0.0236
  -4.750   0.1820   0.03473   0.03045  -0.1287   0.6698   0.0246
  -4.500   0.2184   0.02643   0.02159  -0.1346   0.6639   0.0263
  -4.250   0.2456   0.02475   0.01973  -0.1355   0.6568   0.0267
  -4.000   0.2725   0.02372   0.01858  -0.1359   0.6492   0.0272
  -3.750   0.3000   0.02230   0.01698  -0.1365   0.6427   0.0279
  -3.500   0.3296   0.01884   0.01307  -0.1376   0.6367   0.0288
  -3.250   0.3584   0.01431   0.00771  -0.1384   0.6311   0.0304
  -3.000   0.3862   0.01342   0.00655  -0.1385   0.6248   0.0310
  -2.750   0.4138   0.01278   0.00578  -0.1385   0.6177   0.0316
  -2.500   0.4413   0.01244   0.00533  -0.1383   0.6108   0.0321
  -2.250   0.4692   0.01213   0.00495  -0.1383   0.6041   0.0326
  -2.000   0.4968   0.01186   0.00459  -0.1382   0.5973   0.0331
  -1.750   0.5245   0.01159   0.00425  -0.1380   0.5905   0.0337
  -1.500   0.5521   0.01134   0.00393  -0.1379   0.5824   0.0344
  -1.250   0.5796   0.01113   0.00365  -0.1377   0.5748   0.0352
  -1.000   0.6071   0.01098   0.00343  -0.1376   0.5665   0.0361
  -0.750   0.6346   0.01083   0.00323  -0.1374   0.5583   0.0370
  -0.500   0.6618   0.01069   0.00306  -0.1373   0.5486   0.0381
  -0.250   0.6892   0.01063   0.00297  -0.1371   0.5384   0.0392
   0.000   0.7162   0.01060   0.00289  -0.1369   0.5261   0.0405
   0.250   0.7427   0.01060   0.00281  -0.1365   0.5102   0.0420
   0.500   0.7692   0.01064   0.00275  -0.1362   0.4941   0.0435
   0.750   0.7957   0.01067   0.00275  -0.1359   0.4811   0.0463
   1.000   0.8225   0.01073   0.00278  -0.1357   0.4702   0.0497
   1.250   0.8491   0.01080   0.00279  -0.1354   0.4588   0.0531
   1.500   0.8754   0.01090   0.00286  -0.1351   0.4467   0.0573
   2.000   0.9282   0.01110   0.00299  -0.1345   0.4257   0.0667
   2.250   0.9544   0.01124   0.00308  -0.1342   0.4177   0.0720
   2.500   0.9812   0.01130   0.00315  -0.1340   0.4103   0.0795
   2.750   1.0075   0.01142   0.00325  -0.1337   0.4036   0.0873
   3.000   1.0342   0.01148   0.00336  -0.1335   0.3975   0.1059
   3.500   1.0829   0.01029   0.00382  -0.1326   0.3845   1.0000
   3.750   1.1094   0.01044   0.00394  -0.1324   0.3781   1.0000
   4.000   1.1352   0.01064   0.00409  -0.1320   0.3715   1.0000
   4.250   1.1612   0.01082   0.00423  -0.1317   0.3643   1.0000
   4.500   1.1867   0.01103   0.00440  -0.1313   0.3564   1.0000
   4.750   1.2124   0.01122   0.00456  -0.1310   0.3501   1.0000
   5.000   1.2379   0.01142   0.00474  -0.1306   0.3428   1.0000
   5.250   1.2629   0.01164   0.00494  -0.1301   0.3357   1.0000
   5.500   1.2878   0.01187   0.00514  -0.1297   0.3269   1.0000
   5.750   1.3123   0.01212   0.00535  -0.1291   0.3177   1.0000
   6.000   1.3361   0.01241   0.00560  -0.1285   0.3073   1.0000
   6.250   1.3601   0.01267   0.00584  -0.1279   0.2976   1.0000
   6.500   1.3836   0.01297   0.00611  -0.1273   0.2885   1.0000
   7.000   1.4293   0.01360   0.00670  -0.1257   0.2693   1.0000
   7.250   1.4514   0.01396   0.00703  -0.1249   0.2609   1.0000
   7.500   1.4736   0.01429   0.00735  -0.1240   0.2526   1.0000
   7.750   1.4949   0.01466   0.00772  -0.1230   0.2451   1.0000
   8.000   1.5163   0.01501   0.00808  -0.1221   0.2377   1.0000
   8.250   1.5364   0.01542   0.00848  -0.1209   0.2308   1.0000
   8.500   1.5569   0.01578   0.00887  -0.1197   0.2239   1.0000
   8.750   1.5741   0.01627   0.00934  -0.1181   0.2145   1.0000
   9.000   1.5888   0.01685   0.00986  -0.1160   0.2016   1.0000
   9.250   1.6035   0.01744   0.01041  -0.1140   0.1876   1.0000
   9.500   1.6174   0.01808   0.01102  -0.1119   0.1735   1.0000
   9.750   1.6297   0.01883   0.01170  -0.1096   0.1580   1.0000
  10.000   1.6403   0.01968   0.01248  -0.1071   0.1434   1.0000
  10.250   1.6503   0.02058   0.01334  -0.1047   0.1329   1.0000
  10.500   1.6620   0.02139   0.01416  -0.1026   0.1257   1.0000
  10.750   1.6719   0.02233   0.01511  -0.1003   0.1195   1.0000
  11.000   1.6848   0.02312   0.01596  -0.0985   0.1158   1.0000
  11.250   1.6954   0.02407   0.01694  -0.0966   0.1111   1.0000
  11.500   1.7033   0.02525   0.01814  -0.0944   0.1058   1.0000
  11.750   1.7147   0.02622   0.01918  -0.0928   0.1011   1.0000
  12.000   1.7216   0.02756   0.02054  -0.0908   0.0936   1.0000
  12.250   1.7279   0.02901   0.02200  -0.0889   0.0821   1.0000
  12.500   1.7146   0.03214   0.02493  -0.0857   0.0557   1.0000
  12.750   1.7084   0.03491   0.02770  -0.0835   0.0447   1.0000
  13.000   1.7033   0.03777   0.03058  -0.0818   0.0358   1.0000
  13.250   1.6964   0.04099   0.03381  -0.0803   0.0261   1.0000
  13.750   1.6856   0.04752   0.04044  -0.0784   0.0176   1.0000
  14.000   1.6818   0.05076   0.04377  -0.0777   0.0160   1.0000
  14.250   1.6795   0.05391   0.04703  -0.0773   0.0150   1.0000
  14.500   1.6753   0.05733   0.05055  -0.0769   0.0141   1.0000
  14.750   1.6695   0.06105   0.05437  -0.0766   0.0134   1.0000
  15.000   1.6629   0.06494   0.05836  -0.0765   0.0128   1.0000
  15.250   1.6585   0.06863   0.06217  -0.0765   0.0124   1.0000
  15.500   1.6525   0.07258   0.06624  -0.0767   0.0119   1.0000
  15.750   1.6453   0.07679   0.07056  -0.0770   0.0115   1.0000
  16.000   1.6370   0.08126   0.07515  -0.0775   0.0111   1.0000
  16.250   1.6278   0.08593   0.07992  -0.0782   0.0108   1.0000
  16.500   1.6177   0.09080   0.08491  -0.0789   0.0105   1.0000
  16.750   1.6064   0.09593   0.09015  -0.0799   0.0102   1.0000
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