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GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il)
Reynolds number: 1,000,000
Max Cl/Cd: 137.28 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe303-il-1000000.txt
Download as CSV file: xf-goe303-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2377   0.09512   0.09346  -0.0534   0.9923   0.0185
  -9.000  -0.2254   0.09066   0.08901  -0.0577   0.9887   0.0185
  -8.750  -0.2133   0.08642   0.08476  -0.0605   0.9857   0.0188
  -8.500  -0.1970   0.08387   0.08222  -0.0626   0.9809   0.0190
  -8.250  -0.1819   0.08123   0.07957  -0.0650   0.9735   0.0192
  -8.000  -0.1693   0.07852   0.07686  -0.0674   0.9630   0.0196
  -7.750  -0.1593   0.07574   0.07406  -0.0696   0.9503   0.0202
  -7.000  -0.0808   0.04680   0.04497  -0.0826   0.8891   0.0228
  -6.750  -0.0669   0.04423   0.04236  -0.0845   0.8807   0.0231
  -6.500  -0.0515   0.04124   0.03934  -0.0874   0.8716   0.0237
  -6.250  -0.0346   0.03770   0.03573  -0.0912   0.8628   0.0247
  -6.000  -0.0126   0.02488   0.02266  -0.1067   0.8556   0.0268
  -5.750   0.0070   0.02309   0.02080  -0.1075   0.8458   0.0271
  -5.500   0.0284   0.02127   0.01889  -0.1086   0.8344   0.0275
  -5.250   0.0508   0.01940   0.01692  -0.1098   0.8216   0.0281
  -5.000   0.0748   0.01686   0.01424  -0.1117   0.8089   0.0294
  -4.500   0.1240   0.01472   0.01037  -0.1227   0.8194   0.0292
  -4.250   0.1505   0.01321   0.00852  -0.1225   0.8048   0.0295
  -4.000   0.1773   0.01219   0.00723  -0.1223   0.7884   0.0296
  -3.750   0.2042   0.01147   0.00628  -0.1220   0.7712   0.0299
  -3.500   0.2314   0.01094   0.00556  -0.1218   0.7545   0.0303
  -3.250   0.2587   0.01055   0.00501  -0.1215   0.7382   0.0307
  -3.000   0.2862   0.01041   0.00473  -0.1213   0.7211   0.0312
  -2.750   0.3137   0.01027   0.00446  -0.1211   0.7053   0.0315
  -2.250   0.3682   0.00913   0.00311  -0.1207   0.6792   0.0325
  -2.000   0.3958   0.00889   0.00282  -0.1206   0.6669   0.0331
  -1.750   0.4234   0.00874   0.00261  -0.1205   0.6546   0.0337
  -1.500   0.4510   0.00863   0.00243  -0.1203   0.6423   0.0344
  -1.250   0.4790   0.00852   0.00227  -0.1202   0.6304   0.0352
  -1.000   0.5069   0.00844   0.00215  -0.1201   0.6193   0.0363
  -0.750   0.5346   0.00840   0.00204  -0.1200   0.6080   0.0371
  -0.500   0.5623   0.00832   0.00190  -0.1199   0.5963   0.0380
  -0.250   0.5904   0.00822   0.00177  -0.1198   0.5861   0.0400
   0.000   0.6181   0.00821   0.00172  -0.1197   0.5771   0.0421
   0.250   0.6462   0.00819   0.00168  -0.1197   0.5683   0.0448
   0.500   0.6740   0.00814   0.00166  -0.1196   0.5596   0.0598
   0.750   0.7018   0.00809   0.00169  -0.1196   0.5503   0.0958
   1.000   0.7296   0.00808   0.00172  -0.1196   0.5419   0.1226
   1.250   0.7573   0.00806   0.00178  -0.1195   0.5333   0.1654
   1.500   0.7850   0.00802   0.00183  -0.1195   0.5256   0.2193
   1.750   0.8043   0.00664   0.00208  -0.1182   0.5179   0.8862
   2.000   0.8388   0.00660   0.00211  -0.1196   0.5096   1.0000
   2.250   0.8661   0.00673   0.00216  -0.1194   0.5009   1.0000
   2.500   0.8937   0.00683   0.00222  -0.1193   0.4928   1.0000
   3.000   0.9483   0.00707   0.00236  -0.1191   0.4745   1.0000
   3.250   0.9752   0.00722   0.00245  -0.1189   0.4642   1.0000
   3.500   1.0020   0.00738   0.00255  -0.1187   0.4524   1.0000
   3.750   1.0289   0.00752   0.00264  -0.1185   0.4404   1.0000
   4.000   1.0555   0.00769   0.00276  -0.1183   0.4277   1.0000
   4.250   1.0818   0.00788   0.00289  -0.1180   0.4132   1.0000
   4.500   1.1076   0.00810   0.00303  -0.1177   0.3965   1.0000
   4.750   1.1330   0.00836   0.00319  -0.1173   0.3770   1.0000
   5.000   1.1575   0.00868   0.00340  -0.1167   0.3525   1.0000
   5.250   1.1808   0.00911   0.00366  -0.1160   0.3212   1.0000
   5.500   1.2039   0.00955   0.00393  -0.1153   0.2938   1.0000
   5.750   1.2279   0.00989   0.00419  -0.1147   0.2756   1.0000
   6.000   1.2522   0.01021   0.00444  -0.1141   0.2627   1.0000
   6.250   1.2765   0.01051   0.00469  -0.1136   0.2527   1.0000
   6.500   1.3013   0.01076   0.00492  -0.1132   0.2453   1.0000
   6.750   1.3254   0.01105   0.00518  -0.1126   0.2379   1.0000
   7.000   1.3502   0.01128   0.00542  -0.1122   0.2325   1.0000
   7.250   1.3745   0.01154   0.00566  -0.1116   0.2269   1.0000
   7.500   1.3978   0.01186   0.00596  -0.1110   0.2202   1.0000
   7.750   1.4225   0.01206   0.00618  -0.1105   0.2154   1.0000
   8.000   1.4459   0.01235   0.00646  -0.1099   0.2097   1.0000
   8.250   1.4690   0.01264   0.00675  -0.1092   0.2043   1.0000
   8.500   1.4928   0.01287   0.00700  -0.1086   0.1982   1.0000
   8.750   1.5144   0.01324   0.00734  -0.1077   0.1908   1.0000
   9.000   1.5379   0.01346   0.00760  -0.1071   0.1853   1.0000
   9.250   1.5587   0.01384   0.00795  -0.1060   0.1758   1.0000
   9.500   1.5786   0.01426   0.00831  -0.1049   0.1623   1.0000
   9.750   1.5930   0.01497   0.00886  -0.1028   0.1361   1.0000
  10.000   1.6000   0.01595   0.00966  -0.0994   0.1075   1.0000
  10.250   1.6086   0.01682   0.01043  -0.0964   0.0912   1.0000
  10.500   1.6198   0.01758   0.01115  -0.0938   0.0811   1.0000
  10.750   1.6320   0.01831   0.01187  -0.0915   0.0736   1.0000
  11.000   1.6445   0.01904   0.01259  -0.0894   0.0676   1.0000
  11.250   1.6574   0.01976   0.01333  -0.0874   0.0621   1.0000
  11.500   1.6684   0.02063   0.01418  -0.0852   0.0560   1.0000
  11.750   1.6797   0.02150   0.01506  -0.0832   0.0499   1.0000
  12.000   1.6874   0.02264   0.01616  -0.0808   0.0413   1.0000
  12.250   1.6893   0.02423   0.01767  -0.0779   0.0290   1.0000
  12.500   1.6899   0.02598   0.01938  -0.0751   0.0208   1.0000
  12.750   1.6938   0.02759   0.02101  -0.0729   0.0178   1.0000
  13.000   1.7005   0.02903   0.02252  -0.0711   0.0164   1.0000
  13.250   1.7050   0.03070   0.02425  -0.0692   0.0154   1.0000
  13.500   1.7069   0.03267   0.02628  -0.0674   0.0143   1.0000
  13.750   1.7124   0.03441   0.02810  -0.0660   0.0138   1.0000
  14.000   1.7168   0.03631   0.03009  -0.0646   0.0134   1.0000
  14.250   1.7196   0.03842   0.03229  -0.0634   0.0129   1.0000
  14.500   1.7206   0.04081   0.03476  -0.0623   0.0124   1.0000
  14.750   1.7190   0.04356   0.03759  -0.0613   0.0120   1.0000
  15.000   1.7137   0.04683   0.04097  -0.0604   0.0116   1.0000
  15.250   1.7082   0.05028   0.04453  -0.0598   0.0113   1.0000
  15.500   1.7085   0.05313   0.04748  -0.0595   0.0111   1.0000
  15.750   1.7069   0.05627   0.05072  -0.0592   0.0109   1.0000
  16.000   1.7036   0.05968   0.05423  -0.0591   0.0107   1.0000
  16.250   1.6991   0.06334   0.05799  -0.0592   0.0104   1.0000
  16.500   1.6933   0.06725   0.06200  -0.0594   0.0102   1.0000
  16.750   1.6861   0.07140   0.06624  -0.0597   0.0100   1.0000
  17.000   1.6773   0.07585   0.07081  -0.0602   0.0098   1.0000
  17.250   1.6666   0.08069   0.07575  -0.0610   0.0097   1.0000
  17.500   1.6544   0.08583   0.08100  -0.0619   0.0095   1.0000
  17.750   1.6402   0.09132   0.08660  -0.0630   0.0094   1.0000
  18.000   1.6239   0.09729   0.09269  -0.0645   0.0093   1.0000
  18.250   1.6067   0.10350   0.09902  -0.0662   0.0092   1.0000
  18.500   1.5886   0.10998   0.10562  -0.0681   0.0091   1.0000
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