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GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il)
Reynolds number: 50,000
Max Cl/Cd: 19.02 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe301-il-50000.txt
Download as CSV file: xf-goe301-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2574   0.12765   0.12067  -0.0340   1.0000   0.1080
  -9.500  -0.2690   0.12836   0.12152  -0.0344   1.0000   0.1090
  -9.250  -0.2842   0.12933   0.12266  -0.0342   1.0000   0.1094
  -9.000  -0.2510   0.11912   0.11239  -0.0324   1.0000   0.1131
  -8.750  -0.2478   0.11644   0.10979  -0.0313   1.0000   0.1162
  -8.500  -0.2501   0.11467   0.10811  -0.0303   1.0000   0.1193
  -8.250  -0.2586   0.11382   0.10739  -0.0291   1.0000   0.1221
  -8.000  -0.2756   0.11415   0.10788  -0.0272   1.0000   0.1237
  -7.750  -0.2969   0.11489   0.10880  -0.0250   1.0000   0.1244
  -7.500  -0.3154   0.11567   0.10975  -0.0250   1.0000   0.1249
  -7.250  -0.2957   0.10826   0.10235  -0.0204   1.0000   0.1292
  -7.000  -0.3014   0.10655   0.10074  -0.0180   1.0000   0.1325
  -6.750  -0.3127   0.10562   0.09994  -0.0160   1.0000   0.1353
  -6.500  -0.3265   0.10514   0.09958  -0.0149   1.0000   0.1379
  -6.250  -0.3411   0.10540   0.09995  -0.0161   1.0000   0.1401
  -6.000  -0.3500   0.10633   0.10095  -0.0219   1.0000   0.1413
  -5.750  -0.3497   0.10087   0.09557  -0.0142   1.0000   0.1438
  -5.500  -0.3508   0.09848   0.09324  -0.0118   1.0000   0.1474
  -5.250  -0.3515   0.09672   0.09152  -0.0122   1.0000   0.1523
  -5.000  -0.3426   0.09634   0.09109  -0.0220   1.0000   0.1579
  -4.750  -0.3451   0.09236   0.08721  -0.0164   1.0000   0.1606
  -4.500  -0.3418   0.08999   0.08487  -0.0152   1.0000   0.1663
  -4.000  -0.2901   0.08438   0.07913  -0.0295   0.9921   0.1912
  -3.750  -0.2535   0.08041   0.07509  -0.0354   0.9822   0.2081
  -3.500  -0.2182   0.07666   0.07131  -0.0403   0.9724   0.2263
  -3.250  -0.1763   0.07375   0.06827  -0.0486   0.9609   0.2558
  -3.000  -0.1502   0.07083   0.06533  -0.0506   0.9503   0.2855
  -2.750  -0.1260   0.06774   0.06228  -0.0519   0.9401   0.3237
  -1.500  -0.0762   0.05590   0.05089  -0.0291   0.8902   0.6276
  -1.250  -0.0667   0.05363   0.04870  -0.0239   0.8809   0.6807
  -1.000  -0.0490   0.05144   0.04652  -0.0218   0.8709   0.7252
  -0.750  -0.0255   0.04956   0.04463  -0.0226   0.8594   0.7490
  -0.500   0.3472   0.04758   0.03941  -0.1176   0.8400   0.2647
  -0.250   0.3952   0.04700   0.03809  -0.1211   0.8285   0.2208
   0.000   0.4542   0.04536   0.03596  -0.1256   0.8205   0.2035
   0.250   0.4801   0.04522   0.03562  -0.1259   0.8078   0.2013
   0.500   0.5112   0.04502   0.03515  -0.1267   0.7962   0.1978
   0.750   0.5664   0.04372   0.03349  -0.1299   0.7888   0.1953
   1.000   0.5857   0.04429   0.03388  -0.1290   0.7760   0.2000
   1.250   0.6112   0.04473   0.03406  -0.1287   0.7644   0.2056
   1.500   0.6639   0.04341   0.03264  -0.1311   0.7574   0.2175
   1.750   0.6772   0.04441   0.03365  -0.1296   0.7445   0.2290
   2.000   0.7015   0.04488   0.03413  -0.1292   0.7337   0.2463
   2.250   0.7512   0.04357   0.03321  -0.1316   0.7259   0.3190
   2.500   0.7539   0.04395   0.03483  -0.1284   0.7135   1.0000
   2.750   0.8136   0.04287   0.03297  -0.1301   0.7075   1.0000
   3.000   0.8128   0.04530   0.03530  -0.1275   0.6936   1.0000
   3.250   0.8175   0.04757   0.03747  -0.1256   0.6809   1.0000
   3.500   0.8769   0.04611   0.03576  -0.1274   0.6747   1.0000
   3.750   0.8682   0.04929   0.03892  -0.1246   0.6607   1.0000
   4.000   0.8676   0.05212   0.04172  -0.1226   0.6481   1.0000
   4.250   0.9264   0.05041   0.03988  -0.1239   0.6417   1.0000
   4.500   0.9094   0.05458   0.04408  -0.1211   0.6279   1.0000
   4.750   0.9045   0.05794   0.04744  -0.1193   0.6159   1.0000
   5.000   0.9567   0.05660   0.04603  -0.1198   0.6090   1.0000
   5.250   0.9328   0.06172   0.05118  -0.1175   0.5957   1.0000
   5.500   0.9319   0.06493   0.05442  -0.1162   0.5849   1.0000
   5.750   0.9684   0.06497   0.05445  -0.1159   0.5768   1.0000
   6.000   0.9408   0.07068   0.06019  -0.1143   0.5656   1.0000
   6.250   0.9750   0.07101   0.06052  -0.1139   0.5574   1.0000
   6.500   0.9559   0.07605   0.06560  -0.1127   0.5472   1.0000
   6.750   0.9607   0.07919   0.06877  -0.1120   0.5392   1.0000
   7.000   0.9589   0.08285   0.07247  -0.1114   0.5309   1.0000
   7.250   0.9616   0.08619   0.07586  -0.1108   0.5229   1.0000
   7.500   0.9587   0.09005   0.07977  -0.1104   0.5155   1.0000
   7.750   0.9653   0.09305   0.08280  -0.1098   0.5072   1.0000
   8.000   1.0081   0.09228   0.08207  -0.1086   0.4948   1.0000
   8.250   0.9675   0.09958   0.08942  -0.1086   0.4878   1.0000
   8.500   0.9864   0.10098   0.09086  -0.1075   0.4752   1.0000
   8.750   1.0194   0.10091   0.09086  -0.1060   0.4622   1.0000
   9.000   0.9901   0.10742   0.09743  -0.1064   0.4546   1.0000
   9.250   0.9026   0.12455   0.11471  -0.1140   0.5170   1.0000
   9.500   1.0028   0.11350   0.10362  -0.1055   0.4358   1.0000
   9.750   1.0060   0.11718   0.10736  -0.1054   0.4279   1.0000
  10.000   0.9905   0.12295   0.11319  -0.1063   0.4238   1.0000
  10.250   1.0094   0.12490   0.11520  -0.1055   0.4127   1.0000
  10.500   0.9938   0.13097   0.12133  -0.1069   0.4110   1.0000
  10.750   0.9942   0.13644   0.12688  -0.1083   0.4135   1.0000
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