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GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il)
Reynolds number: 50,000
Max Cl/Cd: 38.09 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe300-il-50000-n5.txt
Download as CSV file: xf-goe300-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 300 (FRIEDRICHSHAFEN G20) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2633   0.11372   0.10765  -0.0277   1.0000   0.0723
  -7.750  -0.2792   0.11368   0.10775  -0.0252   1.0000   0.0725
  -7.500  -0.2920   0.11333   0.10753  -0.0239   1.0000   0.0726
  -7.250  -0.2781   0.11132   0.10553  -0.0315   0.9917   0.0729
  -7.000  -0.2589   0.10456   0.09880  -0.0310   0.9871   0.0739
  -6.750  -0.2379   0.09959   0.09381  -0.0329   0.9800   0.0757
  -6.500  -0.2150   0.09554   0.08973  -0.0375   0.9709   0.0779
  -6.250  -0.1906   0.09193   0.08609  -0.0434   0.9607   0.0817
  -6.000  -0.1557   0.08995   0.08399  -0.0568   0.9468   0.0858
  -5.500  -0.1101   0.08057   0.07458  -0.0626   0.9306   0.0890
  -5.250  -0.0867   0.07700   0.07097  -0.0658   0.9206   0.0921
  -5.000  -0.0421   0.07483   0.06854  -0.0776   0.9098   0.1001
  -4.750  -0.0193   0.07029   0.06399  -0.0800   0.9010   0.1023
  -4.500   0.0011   0.06672   0.06039  -0.0809   0.8914   0.1060
  -4.250   0.0514   0.06471   0.05798  -0.0912   0.8823   0.1156
  -4.000   0.0631   0.06054   0.05392  -0.0899   0.8717   0.1192
  -3.750   0.1109   0.05853   0.05148  -0.0975   0.8642   0.1309
  -3.500   0.1249   0.05470   0.04775  -0.0966   0.8533   0.1346
  -3.250   0.1546   0.05215   0.04504  -0.0993   0.8441   0.1494
  -3.000   0.1985   0.04838   0.04080  -0.1038   0.8358   0.1116
  -2.750   0.2306   0.04590   0.03803  -0.1060   0.8262   0.1114
  -2.500   0.2672   0.04311   0.03490  -0.1086   0.8184   0.1070
  -2.250   0.2980   0.04137   0.03284  -0.1100   0.8085   0.1116
  -2.000   0.3344   0.03917   0.03027  -0.1119   0.8012   0.1109
  -1.750   0.3668   0.03801   0.02856  -0.1129   0.7908   0.1155
  -1.500   0.4019   0.03604   0.02631  -0.1142   0.7838   0.1169
  -1.250   0.4295   0.03479   0.02476  -0.1142   0.7718   0.1172
  -1.000   0.4576   0.03363   0.02346  -0.1142   0.7610   0.1225
  -0.750   0.4913   0.03243   0.02191  -0.1147   0.7519   0.1261
  -0.500   0.5187   0.03158   0.02078  -0.1143   0.7398   0.1263
  -0.250   0.5486   0.03075   0.01965  -0.1142   0.7297   0.1270
   0.000   0.5792   0.02998   0.01858  -0.1141   0.7206   0.1283
   0.250   0.6053   0.02956   0.01798  -0.1136   0.7098   0.1330
   0.500   0.6361   0.02888   0.01713  -0.1136   0.7023   0.1385
   0.750   0.6619   0.02867   0.01673  -0.1130   0.6909   0.1405
   1.000   0.6913   0.02829   0.01611  -0.1126   0.6820   0.1425
   1.250   0.7192   0.02802   0.01565  -0.1121   0.6725   0.1449
   1.500   0.7452   0.02783   0.01537  -0.1115   0.6626   0.1477
   1.750   0.7736   0.02748   0.01495  -0.1111   0.6541   0.1522
   2.000   0.7973   0.02758   0.01497  -0.1103   0.6435   0.1610
   2.250   0.8261   0.02724   0.01462  -0.1099   0.6358   0.1713
   2.500   0.8488   0.02740   0.01478  -0.1091   0.6247   0.1783
   2.750   0.8749   0.02739   0.01474  -0.1086   0.6156   0.1877
   3.000   0.9008   0.02741   0.01479  -0.1082   0.6062   0.2032
   3.250   0.9252   0.02755   0.01507  -0.1077   0.5965   0.2326
   3.500   0.9505   0.02629   0.01509  -0.1069   0.5885   1.0000
   3.750   0.9730   0.02689   0.01551  -0.1060   0.5782   1.0000
   4.000   1.0015   0.02709   0.01548  -0.1056   0.5706   1.0000
   4.250   1.0219   0.02781   0.01618  -0.1046   0.5599   1.0000
   4.500   1.0490   0.02813   0.01637  -0.1042   0.5524   1.0000
   4.750   1.0696   0.02889   0.01715  -0.1033   0.5427   1.0000
   5.000   1.0951   0.02930   0.01752  -0.1027   0.5347   1.0000
   5.250   1.1164   0.02992   0.01815  -0.1018   0.5247   1.0000
   5.500   1.1382   0.03048   0.01872  -0.1008   0.5149   1.0000
   5.750   1.1631   0.03079   0.01901  -0.1001   0.5058   1.0000
   6.000   1.1811   0.03158   0.01988  -0.0989   0.4952   1.0000
   6.250   1.2066   0.03178   0.02006  -0.0981   0.4862   1.0000
   6.500   1.2241   0.03249   0.02087  -0.0968   0.4752   1.0000
   6.750   1.2428   0.03312   0.02158  -0.0955   0.4649   1.0000
   7.000   1.2675   0.03328   0.02172  -0.0946   0.4557   1.0000
   7.250   1.2809   0.03423   0.02284  -0.0929   0.4446   1.0000
   7.500   1.3012   0.03477   0.02346  -0.0918   0.4358   1.0000
   7.750   1.3188   0.03550   0.02430  -0.0905   0.4267   1.0000
   8.000   1.3341   0.03636   0.02531  -0.0890   0.4173   1.0000
   8.250   1.3566   0.03664   0.02564  -0.0879   0.4083   1.0000
   8.500   1.3659   0.03782   0.02700  -0.0859   0.3976   1.0000
   8.750   1.3829   0.03844   0.02771  -0.0844   0.3879   1.0000
   9.000   1.3992   0.03910   0.02849  -0.0828   0.3779   1.0000
   9.250   1.4072   0.04034   0.02989  -0.0806   0.3673   1.0000
   9.500   1.4243   0.04091   0.03052  -0.0791   0.3571   1.0000
   9.750   1.4322   0.04200   0.03172  -0.0767   0.3461   1.0000
  10.000   1.4355   0.04350   0.03339  -0.0742   0.3352   1.0000
  10.250   1.4502   0.04427   0.03420  -0.0726   0.3245   1.0000
  10.500   1.4517   0.04604   0.03612  -0.0703   0.3138   1.0000
  10.750   1.4530   0.04797   0.03820  -0.0682   0.3036   1.0000
  11.000   1.4697   0.04870   0.03896  -0.0668   0.2940   1.0000
  11.250   1.4551   0.05213   0.04263  -0.0645   0.2846   1.0000
  11.500   1.4663   0.05340   0.04399  -0.0631   0.2762   1.0000
  11.750   1.4529   0.05715   0.04797  -0.0616   0.2680   1.0000
  12.000   1.4638   0.05853   0.04942  -0.0604   0.2610   1.0000
  12.250   1.4424   0.06357   0.05471  -0.0596   0.2539   1.0000
  12.500   1.4617   0.06398   0.05519  -0.0583   0.2478   1.0000
  12.750   1.4229   0.07173   0.06319  -0.0588   0.2415   1.0000
  13.000   1.4203   0.07505   0.06664  -0.0584   0.2359   1.0000
  13.250   1.4125   0.07924   0.07097  -0.0584   0.2309   1.0000
  13.500   1.3406   0.09393   0.08579  -0.0629   0.2236   1.0000
  13.750   1.3722   0.09189   0.08390  -0.0606   0.2201   1.0000
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