Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il)
Reynolds number: 50,000
Max Cl/Cd: 39.54 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe303-il-50000-n5.txt
Download as CSV file: xf-goe303-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3119   0.10687   0.10064  -0.0238   1.0000   0.1026
  -7.250  -0.3235   0.10567   0.09955  -0.0217   1.0000   0.1041
  -7.000  -0.3334   0.10434   0.09833  -0.0206   1.0000   0.1060
  -6.750  -0.3343   0.10292   0.09697  -0.0258   0.9961   0.1091
  -6.500  -0.3101   0.09832   0.09235  -0.0348   0.9870   0.1113
  -6.250  -0.2911   0.09373   0.08777  -0.0327   0.9824   0.1159
  -6.000  -0.2649   0.09004   0.08399  -0.0400   0.9734   0.1232
  -5.750  -0.2321   0.08597   0.07980  -0.0530   0.9627   0.1273
  -5.500  -0.2160   0.08183   0.07569  -0.0518   0.9547   0.1300
  -5.250  -0.1899   0.07819   0.07199  -0.0555   0.9470   0.1358
  -5.000  -0.1583   0.07435   0.06803  -0.0640   0.9373   0.1454
  -4.750  -0.1208   0.07191   0.06529  -0.0736   0.9263   0.1593
  -4.500  -0.0637   0.06268   0.05544  -0.0857   0.9205   0.0944
  -4.250  -0.0482   0.05954   0.05245  -0.0844   0.9113   0.0909
  -4.000  -0.0089   0.05558   0.04826  -0.0899   0.9051   0.0887
  -3.750   0.0233   0.05228   0.04472  -0.0937   0.8955   0.0875
  -3.500   0.0685   0.04804   0.04002  -0.0998   0.8895   0.0831
  -3.250   0.1109   0.04426   0.03543  -0.1045   0.8809   0.0792
  -3.000   0.1494   0.04152   0.03235  -0.1077   0.8744   0.0796
  -2.750   0.1790   0.03983   0.03063  -0.1091   0.8658   0.0821
  -2.500   0.2156   0.03792   0.02840  -0.1113   0.8586   0.0840
  -2.250   0.2493   0.03611   0.02620  -0.1128   0.8503   0.0843
  -2.000   0.2854   0.03442   0.02412  -0.1145   0.8428   0.0850
  -1.750   0.3174   0.03311   0.02248  -0.1152   0.8341   0.0864
  -1.500   0.3529   0.03193   0.02095  -0.1164   0.8268   0.0905
  -1.250   0.3833   0.03109   0.01970  -0.1166   0.8175   0.0944
  -1.000   0.4176   0.03003   0.01855  -0.1176   0.8106   0.0980
  -0.750   0.4457   0.02947   0.01782  -0.1174   0.8009   0.1022
  -0.250   0.5093   0.02834   0.01639  -0.1180   0.7844   0.1213
   0.000   0.5452   0.02761   0.01559  -0.1189   0.7783   0.1384
   0.250   0.5707   0.02738   0.01540  -0.1184   0.7679   0.1650
   0.500   0.6066   0.02653   0.01475  -0.1195   0.7621   0.2274
   0.750   0.6285   0.02457   0.01473  -0.1185   0.7517   1.0000
   1.000   0.6617   0.02459   0.01427  -0.1187   0.7447   1.0000
   1.500   0.7150   0.02513   0.01434  -0.1178   0.7256   1.0000
   1.750   0.7443   0.02527   0.01429  -0.1177   0.7169   1.0000
   2.000   0.7693   0.02561   0.01450  -0.1170   0.7065   1.0000
   2.250   0.8029   0.02547   0.01418  -0.1173   0.6983   1.0000
   2.500   0.8265   0.02571   0.01431  -0.1162   0.6849   1.0000
   2.750   0.8516   0.02585   0.01435  -0.1152   0.6716   1.0000
   3.000   0.8779   0.02594   0.01434  -0.1144   0.6587   1.0000
   3.250   0.9064   0.02595   0.01423  -0.1139   0.6470   1.0000
   3.500   0.9320   0.02614   0.01436  -0.1131   0.6351   1.0000
   3.750   0.9544   0.02653   0.01475  -0.1121   0.6228   1.0000
   4.000   0.9793   0.02682   0.01501  -0.1113   0.6116   1.0000
   4.250   1.0080   0.02692   0.01504  -0.1110   0.6013   1.0000
   4.500   1.0287   0.02739   0.01556  -0.1097   0.5885   1.0000
   4.750   1.0509   0.02781   0.01599  -0.1087   0.5761   1.0000
   5.000   1.0750   0.02812   0.01630  -0.1078   0.5642   1.0000
   5.250   1.1014   0.02830   0.01648  -0.1072   0.5526   1.0000
   5.500   1.1220   0.02877   0.01700  -0.1059   0.5391   1.0000
   5.750   1.1424   0.02928   0.01756  -0.1046   0.5256   1.0000
   6.000   1.1633   0.02976   0.01809  -0.1033   0.5123   1.0000
   6.250   1.1847   0.03021   0.01860  -0.1022   0.4990   1.0000
   6.500   1.2064   0.03065   0.01906  -0.1010   0.4856   1.0000
   6.750   1.2285   0.03107   0.01950  -0.0999   0.4724   1.0000
   7.000   1.2476   0.03168   0.02020  -0.0985   0.4587   1.0000
   7.250   1.2652   0.03242   0.02103  -0.0969   0.4454   1.0000
   7.500   1.2834   0.03315   0.02184  -0.0955   0.4326   1.0000
   7.750   1.3028   0.03384   0.02257  -0.0942   0.4208   1.0000
   8.000   1.3253   0.03437   0.02313  -0.0933   0.4101   1.0000
   8.250   1.3397   0.03540   0.02431  -0.0915   0.3986   1.0000
   8.500   1.3571   0.03631   0.02533  -0.0902   0.3886   1.0000
   8.750   1.3798   0.03694   0.02598  -0.0893   0.3796   1.0000
   9.000   1.3911   0.03820   0.02745  -0.0874   0.3698   1.0000
   9.250   1.4108   0.03902   0.02834  -0.0863   0.3613   1.0000
   9.500   1.4234   0.04009   0.02954  -0.0844   0.3517   1.0000
   9.750   1.4315   0.04121   0.03079  -0.0819   0.3414   1.0000
  10.000   1.4435   0.04199   0.03162  -0.0797   0.3308   1.0000
  10.250   1.4499   0.04307   0.03279  -0.0770   0.3201   1.0000
  10.500   1.4512   0.04461   0.03449  -0.0742   0.3102   1.0000
  10.750   1.4630   0.04559   0.03551  -0.0723   0.3008   1.0000
  11.000   1.4639   0.04736   0.03748  -0.0698   0.2921   1.0000
  11.250   1.4703   0.04884   0.03907  -0.0678   0.2835   1.0000
  11.500   1.4750   0.05045   0.04086  -0.0658   0.2748   1.0000
  11.750   1.4743   0.05257   0.04315  -0.0637   0.2665   1.0000
  12.000   1.4828   0.05389   0.04455  -0.0620   0.2574   1.0000
  12.250   1.4726   0.05700   0.04791  -0.0600   0.2495   1.0000
  12.500   1.4850   0.05801   0.04892  -0.0585   0.2402   1.0000
  12.750   1.4653   0.06231   0.05354  -0.0569   0.2326   1.0000
  13.000   1.4726   0.06381   0.05508  -0.0556   0.2234   1.0000
  13.250   1.4512   0.06877   0.06032  -0.0548   0.2158   1.0000
  13.500   1.4546   0.07084   0.06248  -0.0537   0.2071   1.0000
  13.750   1.4303   0.07671   0.06862  -0.0538   0.1999   1.0000
  14.000   1.4296   0.07942   0.07140  -0.0532   0.1917   1.0000
  14.250   1.3984   0.08696   0.07919  -0.0546   0.1851   1.0000
  14.500   1.3986   0.08969   0.08199  -0.0543   0.1774   1.0000
  14.750   1.3489   0.10142   0.09395  -0.0583   0.1721   1.0000
  15.000   1.3675   0.10099   0.09355  -0.0568   0.1644   1.0000
  15.250   1.2650   0.12512   0.11777  -0.0683   0.1594   1.0000
  15.500   1.2789   0.12556   0.11833  -0.0674   0.1535   1.0000
<< Back to GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il)

Polar data table (+)

Polar graphs


<< Back to GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il)