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GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il)
Reynolds number: 200,000
Max Cl/Cd: 81.12 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe301-il-200000-n5.txt
Download as CSV file: xf-goe301-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1632   0.09549   0.09205  -0.0565   0.9729   0.0308
  -8.000  -0.1507   0.09175   0.08832  -0.0618   0.9636   0.0309
  -7.750  -0.1367   0.08778   0.08436  -0.0654   0.9530   0.0310
  -7.500  -0.1195   0.08440   0.08098  -0.0644   0.9476   0.0315
  -7.250  -0.0992   0.08107   0.07764  -0.0677   0.9387   0.0324
  -7.000  -0.0780   0.07779   0.07434  -0.0722   0.9273   0.0346
  -6.750  -0.0425   0.07242   0.06886  -0.0890   0.9115   0.0366
  -6.500  -0.0115   0.06747   0.06380  -0.0976   0.8975   0.0367
  -6.250   0.0065   0.06399   0.06029  -0.0977   0.8836   0.0371
  -6.000   0.0258   0.06156   0.05781  -0.0980   0.8677   0.0381
  -5.750   0.0496   0.05896   0.05513  -0.1012   0.8500   0.0407
  -5.500   0.0979   0.05364   0.04948  -0.1157   0.8299   0.0435
  -5.250   0.1271   0.04979   0.04541  -0.1201   0.8110   0.0436
  -4.750   0.1636   0.04498   0.04044  -0.1205   0.7749   0.0453
  -4.500   0.2037   0.04034   0.03536  -0.1268   0.7603   0.0433
  -4.250   0.2231   0.03842   0.03337  -0.1269   0.7463   0.0418
  -4.000   0.2519   0.03546   0.03017  -0.1293   0.7342   0.0404
  -3.750   0.2827   0.03276   0.02716  -0.1315   0.7234   0.0415
  -3.500   0.3125   0.03015   0.02425  -0.1332   0.7133   0.0411
  -3.250   0.3423   0.02762   0.02141  -0.1345   0.7039   0.0405
  -2.750   0.4017   0.02335   0.01644  -0.1362   0.6867   0.0415
  -2.250   0.4600   0.01993   0.01227  -0.1369   0.6702   0.0424
  -2.000   0.4886   0.01864   0.01060  -0.1370   0.6626   0.0429
  -1.750   0.5169   0.01760   0.00924  -0.1370   0.6546   0.0435
  -1.500   0.5441   0.01701   0.00851  -0.1369   0.6466   0.0446
  -1.250   0.5712   0.01669   0.00813  -0.1368   0.6382   0.0460
  -1.000   0.5986   0.01625   0.00753  -0.1366   0.6302   0.0472
  -0.750   0.6261   0.01575   0.00689  -0.1364   0.6223   0.0482
  -0.500   0.6533   0.01534   0.00634  -0.1361   0.6141   0.0494
  -0.250   0.6804   0.01498   0.00587  -0.1358   0.6056   0.0508
   0.000   0.7072   0.01470   0.00553  -0.1355   0.5971   0.0527
   0.250   0.7340   0.01457   0.00541  -0.1352   0.5882   0.0554
   0.500   0.7606   0.01442   0.00521  -0.1349   0.5795   0.0581
   0.750   0.7873   0.01426   0.00501  -0.1346   0.5696   0.0608
   1.000   0.8136   0.01411   0.00486  -0.1342   0.5602   0.0639
   1.250   0.8398   0.01406   0.00480  -0.1339   0.5490   0.0693
   1.500   0.8659   0.01399   0.00472  -0.1335   0.5369   0.0752
   1.750   0.8918   0.01399   0.00467  -0.1331   0.5249   0.0820
   2.000   0.9175   0.01400   0.00464  -0.1327   0.5136   0.0911
   2.250   0.9436   0.01403   0.00466  -0.1323   0.5028   0.1030
   2.500   0.9695   0.01405   0.00474  -0.1320   0.4934   0.1326
   3.000   1.0171   0.01290   0.00504  -0.1304   0.4746   1.0000
   3.250   1.0422   0.01314   0.00515  -0.1298   0.4646   1.0000
   3.500   1.0672   0.01338   0.00530  -0.1293   0.4545   1.0000
   3.750   1.0923   0.01363   0.00548  -0.1288   0.4455   1.0000
   4.000   1.1171   0.01390   0.00566  -0.1282   0.4371   1.0000
   4.250   1.1422   0.01415   0.00587  -0.1278   0.4297   1.0000
   4.500   1.1669   0.01443   0.00610  -0.1272   0.4219   1.0000
   4.750   1.1914   0.01470   0.00634  -0.1267   0.4142   1.0000
   5.000   1.2154   0.01500   0.00659  -0.1260   0.4054   1.0000
   5.250   1.2395   0.01528   0.00687  -0.1254   0.3968   1.0000
   5.500   1.2630   0.01559   0.00714  -0.1247   0.3885   1.0000
   5.750   1.2870   0.01588   0.00744  -0.1241   0.3811   1.0000
   6.000   1.3105   0.01618   0.00776  -0.1234   0.3739   1.0000
   6.250   1.3336   0.01650   0.00808  -0.1227   0.3663   1.0000
   6.500   1.3560   0.01683   0.00841  -0.1218   0.3571   1.0000
   6.750   1.3785   0.01715   0.00876  -0.1210   0.3485   1.0000
   7.000   1.4000   0.01752   0.00913  -0.1200   0.3403   1.0000
   7.250   1.4219   0.01786   0.00952  -0.1191   0.3316   1.0000
   7.500   1.4422   0.01827   0.00992  -0.1179   0.3237   1.0000
   7.750   1.4634   0.01863   0.01036  -0.1169   0.3151   1.0000
   8.000   1.4826   0.01907   0.01081  -0.1156   0.3071   1.0000
   8.250   1.5021   0.01949   0.01128  -0.1143   0.2983   1.0000
   8.500   1.5200   0.01997   0.01178  -0.1128   0.2903   1.0000
   8.750   1.5367   0.02046   0.01232  -0.1111   0.2818   1.0000
   9.000   1.5520   0.02098   0.01289  -0.1091   0.2742   1.0000
   9.250   1.5667   0.02155   0.01350  -0.1071   0.2662   1.0000
   9.500   1.5810   0.02217   0.01416  -0.1052   0.2588   1.0000
   9.750   1.5946   0.02283   0.01489  -0.1031   0.2512   1.0000
  10.000   1.6073   0.02356   0.01566  -0.1011   0.2443   1.0000
  10.250   1.6192   0.02434   0.01650  -0.0990   0.2359   1.0000
  10.500   1.6292   0.02524   0.01744  -0.0967   0.2266   1.0000
  10.750   1.6358   0.02636   0.01855  -0.0942   0.2164   1.0000
  11.000   1.6447   0.02742   0.01967  -0.0921   0.2052   1.0000
  11.250   1.6519   0.02862   0.02092  -0.0899   0.1945   1.0000
  11.500   1.6572   0.03002   0.02233  -0.0877   0.1838   1.0000
  12.000   1.6663   0.03314   0.02552  -0.0838   0.1622   1.0000
  12.250   1.6699   0.03491   0.02733  -0.0821   0.1535   1.0000
  12.500   1.6708   0.03698   0.02944  -0.0804   0.1458   1.0000
  12.750   1.6724   0.03911   0.03163  -0.0789   0.1380   1.0000
  13.000   1.6706   0.04165   0.03421  -0.0775   0.1311   1.0000
  13.250   1.6705   0.04414   0.03677  -0.0764   0.1244   1.0000
  13.500   1.6658   0.04720   0.03988  -0.0754   0.1188   1.0000
  13.750   1.6670   0.04971   0.04251  -0.0746   0.1127   1.0000
  14.000   1.6618   0.05302   0.04589  -0.0740   0.1067   1.0000
  14.250   1.6605   0.05597   0.04897  -0.0734   0.0992   1.0000
  14.500   1.6556   0.05943   0.05250  -0.0731   0.0889   1.0000
  14.750   1.6421   0.06406   0.05709  -0.0730   0.0681   1.0000
  15.000   1.6221   0.06965   0.06261  -0.0732   0.0565   1.0000
  15.250   1.6056   0.07497   0.06795  -0.0735   0.0490   1.0000
  15.500   1.5899   0.08035   0.07340  -0.0741   0.0428   1.0000
  15.750   1.5758   0.08564   0.07877  -0.0748   0.0370   1.0000
  16.000   1.5622   0.09101   0.08423  -0.0757   0.0322   1.0000
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