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GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il)
Reynolds number: 1,000,000
Max Cl/Cd: 138.2 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe301-il-1000000.txt
Download as CSV file: xf-goe301-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.1478   0.08678   0.08513  -0.0657   0.9831   0.0187
  -8.250  -0.1367   0.08251   0.08087  -0.0684   0.9752   0.0189
  -8.000  -0.1203   0.07993   0.07829  -0.0700   0.9664   0.0190
  -7.750  -0.1018   0.07719   0.07554  -0.0731   0.9543   0.0193
  -7.500  -0.0817   0.07428   0.07258  -0.0771   0.9364   0.0197
  -7.250  -0.0634   0.07134   0.06955  -0.0810   0.9140   0.0204
  -6.750  -0.0232   0.05985   0.05781  -0.0997   0.8684   0.0224
  -6.500  -0.0075   0.05792   0.05578  -0.1001   0.8427   0.0226
  -6.250   0.0100   0.05602   0.05373  -0.1014   0.8071   0.0229
  -6.000   0.0293   0.05397   0.05149  -0.1035   0.7694   0.0233
  -5.750   0.0514   0.05154   0.04890  -0.1065   0.7429   0.0240
  -5.500   0.0958   0.04430   0.04138  -0.1187   0.7263   0.0262
  -5.250   0.1156   0.04062   0.03758  -0.1213   0.7127   0.0267
  -5.000   0.1385   0.03913   0.03601  -0.1223   0.7012   0.0270
  -4.500   0.1906   0.03537   0.03204  -0.1256   0.6828   0.0286
  -4.250   0.2298   0.02807   0.02431  -0.1313   0.6760   0.0312
  -4.000   0.2551   0.02690   0.02307  -0.1319   0.6684   0.0316
  -3.750   0.2809   0.02584   0.02191  -0.1324   0.6605   0.0320
  -3.500   0.3146   0.01488   0.00979  -0.1353   0.6560   0.0310
  -3.250   0.3420   0.01305   0.00767  -0.1356   0.6493   0.0316
  -3.000   0.3695   0.01311   0.00770  -0.1355   0.6424   0.0322
  -2.750   0.3976   0.01245   0.00693  -0.1355   0.6362   0.0327
  -2.500   0.4255   0.01148   0.00574  -0.1355   0.6294   0.0331
  -2.250   0.4532   0.01085   0.00496  -0.1354   0.6227   0.0336
  -2.000   0.4814   0.01035   0.00435  -0.1354   0.6160   0.0341
  -1.750   0.5091   0.01000   0.00389  -0.1353   0.6091   0.0348
  -1.500   0.5373   0.00974   0.00358  -0.1352   0.6024   0.0355
  -1.250   0.5651   0.00968   0.00345  -0.1351   0.5946   0.0360
  -1.000   0.5927   0.00910   0.00281  -0.1350   0.5864   0.0372
  -0.750   0.6202   0.00899   0.00265  -0.1348   0.5761   0.0381
  -0.500   0.6481   0.00889   0.00253  -0.1347   0.5649   0.0390
  -0.250   0.6757   0.00883   0.00242  -0.1346   0.5540   0.0402
   0.000   0.7031   0.00879   0.00232  -0.1344   0.5426   0.0414
   0.250   0.7306   0.00872   0.00219  -0.1342   0.5291   0.0429
   0.500   0.7579   0.00870   0.00213  -0.1341   0.5146   0.0453
   0.750   0.7852   0.00874   0.00213  -0.1339   0.5006   0.0477
   1.000   0.8123   0.00881   0.00214  -0.1337   0.4873   0.0497
   1.250   0.8394   0.00882   0.00211  -0.1335   0.4741   0.0544
   1.500   0.8662   0.00893   0.00217  -0.1332   0.4617   0.0581
   1.750   0.8934   0.00897   0.00219  -0.1331   0.4511   0.0644
   2.000   0.9205   0.00907   0.00226  -0.1329   0.4419   0.0689
   2.250   0.9474   0.00913   0.00229  -0.1327   0.4328   0.0759
   2.500   0.9747   0.00919   0.00234  -0.1326   0.4256   0.0811
   2.750   1.0016   0.00926   0.00241  -0.1324   0.4182   0.0921
   3.000   1.0291   0.00877   0.00265  -0.1328   0.4119   0.4819
   3.250   1.0522   0.00792   0.00283  -0.1319   0.4057   1.0000
   3.500   1.0788   0.00809   0.00294  -0.1316   0.3989   1.0000
   3.750   1.1060   0.00821   0.00303  -0.1315   0.3925   1.0000
   4.000   1.1324   0.00838   0.00315  -0.1312   0.3853   1.0000
   4.250   1.1594   0.00851   0.00326  -0.1311   0.3795   1.0000
   4.500   1.1859   0.00866   0.00338  -0.1309   0.3725   1.0000
   4.750   1.2122   0.00884   0.00352  -0.1306   0.3656   1.0000
   5.000   1.2388   0.00898   0.00364  -0.1304   0.3586   1.0000
   5.250   1.2646   0.00918   0.00380  -0.1301   0.3509   1.0000
   5.500   1.2908   0.00934   0.00394  -0.1298   0.3426   1.0000
   5.750   1.3163   0.00955   0.00411  -0.1295   0.3341   1.0000
   6.000   1.3418   0.00975   0.00429  -0.1291   0.3241   1.0000
   6.250   1.3672   0.00996   0.00447  -0.1288   0.3150   1.0000
   6.500   1.3918   0.01022   0.00468  -0.1283   0.3050   1.0000
   6.750   1.4167   0.01045   0.00489  -0.1278   0.2950   1.0000
   7.000   1.4410   0.01071   0.00512  -0.1273   0.2851   1.0000
   7.250   1.4646   0.01102   0.00538  -0.1267   0.2744   1.0000
   7.500   1.4877   0.01135   0.00565  -0.1260   0.2621   1.0000
   7.750   1.5106   0.01168   0.00595  -0.1252   0.2499   1.0000
   8.000   1.5331   0.01203   0.00626  -0.1245   0.2389   1.0000
   8.250   1.5547   0.01243   0.00660  -0.1235   0.2264   1.0000
   8.500   1.5756   0.01286   0.00697  -0.1225   0.2138   1.0000
   8.750   1.5966   0.01326   0.00733  -0.1215   0.2030   1.0000
   9.000   1.6175   0.01364   0.00769  -0.1204   0.1919   1.0000
   9.250   1.6366   0.01413   0.00811  -0.1191   0.1780   1.0000
   9.500   1.6522   0.01479   0.00866  -0.1172   0.1585   1.0000
   9.750   1.6667   0.01543   0.00922  -0.1151   0.1424   1.0000
  10.000   1.6799   0.01605   0.00978  -0.1127   0.1318   1.0000
  10.250   1.6946   0.01660   0.01031  -0.1107   0.1251   1.0000
  10.500   1.7084   0.01720   0.01091  -0.1085   0.1186   1.0000
  10.750   1.7240   0.01771   0.01144  -0.1067   0.1144   1.0000
  11.000   1.7366   0.01839   0.01212  -0.1045   0.1087   1.0000
  11.250   1.7514   0.01896   0.01272  -0.1027   0.1039   1.0000
  11.500   1.7629   0.01973   0.01348  -0.1005   0.0966   1.0000
  11.750   1.7721   0.02065   0.01437  -0.0980   0.0840   1.0000
  12.000   1.7596   0.02298   0.01645  -0.0930   0.0520   1.0000
  12.250   1.7539   0.02507   0.01848  -0.0893   0.0376   1.0000
  12.500   1.7487   0.02728   0.02063  -0.0861   0.0253   1.0000
  12.750   1.7487   0.02925   0.02262  -0.0837   0.0201   1.0000
  13.000   1.7499   0.03123   0.02464  -0.0817   0.0177   1.0000
  13.250   1.7538   0.03308   0.02657  -0.0801   0.0164   1.0000
  13.500   1.7564   0.03517   0.02873  -0.0787   0.0155   1.0000
  13.750   1.7563   0.03761   0.03124  -0.0774   0.0146   1.0000
  14.000   1.7546   0.04035   0.03407  -0.0763   0.0139   1.0000
  14.250   1.7567   0.04278   0.03659  -0.0755   0.0135   1.0000
  14.500   1.7572   0.04544   0.03935  -0.0748   0.0131   1.0000
  14.750   1.7558   0.04838   0.04238  -0.0742   0.0127   1.0000
  15.000   1.7525   0.05161   0.04571  -0.0738   0.0124   1.0000
  15.250   1.7477   0.05511   0.04929  -0.0734   0.0120   1.0000
  15.500   1.7392   0.05910   0.05339  -0.0732   0.0117   1.0000
  15.750   1.7278   0.06359   0.05799  -0.0731   0.0114   1.0000
  16.000   1.7135   0.06860   0.06312  -0.0733   0.0111   1.0000
  16.250   1.7079   0.07251   0.06714  -0.0735   0.0110   1.0000
  16.500   1.7008   0.07671   0.07144  -0.0739   0.0108   1.0000
  16.750   1.6925   0.08115   0.07599  -0.0745   0.0107   1.0000
  17.000   1.6830   0.08586   0.08080  -0.0752   0.0105   1.0000
  17.250   1.6731   0.09066   0.08571  -0.0760   0.0103   1.0000
  17.500   1.6625   0.09563   0.09079  -0.0770   0.0101   1.0000
  17.750   1.6506   0.10087   0.09613  -0.0781   0.0100   1.0000
  18.000   1.6391   0.10612   0.10148  -0.0794   0.0098   1.0000
  18.250   1.6273   0.11142   0.10688  -0.0808   0.0097   1.0000
  18.500   1.6146   0.11692   0.11248  -0.0824   0.0096   1.0000
  18.750   1.6020   0.12248   0.11814  -0.0842   0.0094   1.0000
  19.000   1.5893   0.12816   0.12392  -0.0862   0.0093   1.0000
  19.250   1.5764   0.13395   0.12980  -0.0884   0.0092   1.0000
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