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GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL (goe304-il)
Reynolds number: 50,000
Max Cl/Cd: 38.92 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe304-il-50000-n5.txt
Download as CSV file: xf-goe304-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 304 (FRIEDRICHSHAFEN G02) 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  -0.2753   0.11282   0.10615  -0.0269   1.0000   0.0886
  -7.750  -0.2883   0.11231   0.10576  -0.0243   1.0000   0.0901
  -7.500  -0.3051   0.11222   0.10579  -0.0215   1.0000   0.0911
  -7.250  -0.3034   0.11161   0.10523  -0.0276   0.9927   0.0928
  -7.000  -0.2826   0.10745   0.10108  -0.0334   0.9846   0.0940
  -6.750  -0.2638   0.10262   0.09624  -0.0329   0.9800   0.0961
  -6.500  -0.2422   0.09894   0.09253  -0.0365   0.9730   0.0991
  -6.250  -0.2223   0.09590   0.08947  -0.0417   0.9633   0.1029
  -6.000  -0.1916   0.09475   0.08818  -0.0573   0.9495   0.1067
  -5.750  -0.1762   0.08930   0.08281  -0.0546   0.9457   0.1087
  -5.500  -0.1602   0.08605   0.07957  -0.0548   0.9376   0.1127
  -5.250  -0.1155   0.08489   0.07813  -0.0718   0.9267   0.1215
  -5.000  -0.1088   0.08022   0.07360  -0.0677   0.9193   0.1233
  -4.750  -0.0858   0.07664   0.07003  -0.0689   0.9138   0.1275
  -4.500  -0.0444   0.07558   0.06869  -0.0816   0.9021   0.1375
  -4.250  -0.0284   0.07086   0.06406  -0.0798   0.8975   0.1400
  -4.000  -0.0105   0.06821   0.06142  -0.0801   0.8890   0.1450
  -3.750   0.0284   0.06544   0.05848  -0.0879   0.8818   0.1560
  -3.500   0.0549   0.06317   0.05614  -0.0903   0.8745   0.1688
  -3.250   0.0771   0.06024   0.05322  -0.0914   0.8669   0.1771
  -3.000   0.1143   0.05740   0.05029  -0.0960   0.8624   0.1941
  -2.750   0.1347   0.05558   0.04841  -0.0972   0.8520   0.2094
  -2.500   0.1683   0.05303   0.04580  -0.1001   0.8468   0.2291
  -2.000   0.2788   0.04611   0.03770  -0.1151   0.8326   0.1027
  -1.500   0.3528   0.04196   0.03281  -0.1201   0.8185   0.0920
  -1.250   0.3905   0.03992   0.03058  -0.1224   0.8132   0.0894
  -1.000   0.4209   0.03852   0.02891  -0.1233   0.8052   0.0873
  -0.750   0.4555   0.03707   0.02714  -0.1247   0.7982   0.0859
  -0.500   0.4959   0.03560   0.02536  -0.1267   0.7938   0.0876
  -0.250   0.5185   0.03507   0.02461  -0.1260   0.7833   0.0890
   0.000   0.5561   0.03386   0.02309  -0.1273   0.7781   0.0895
   0.250   0.5813   0.03336   0.02237  -0.1268   0.7688   0.0898
   0.500   0.6148   0.03254   0.02129  -0.1273   0.7623   0.0913
   0.750   0.6434   0.03206   0.02061  -0.1271   0.7546   0.0947
   1.000   0.6723   0.03163   0.02008  -0.1270   0.7466   0.0983
   1.250   0.7100   0.03081   0.01905  -0.1277   0.7418   0.1015
   1.500   0.7295   0.03101   0.01912  -0.1263   0.7306   0.1057
   1.750   0.7646   0.03030   0.01840  -0.1268   0.7253   0.1132
   2.000   0.7843   0.03052   0.01858  -0.1254   0.7144   0.1185
   2.250   0.8183   0.02997   0.01803  -0.1258   0.7085   0.1304
   2.500   0.8384   0.03024   0.01835  -0.1246   0.6976   0.1421
   2.750   0.8726   0.02969   0.01791  -0.1250   0.6914   0.1739
   3.000   0.8890   0.02858   0.01838  -0.1232   0.6804   1.0000
   3.250   0.9230   0.02843   0.01787  -0.1231   0.6739   1.0000
   3.500   0.9413   0.02908   0.01840  -0.1215   0.6618   1.0000
   3.750   0.9698   0.02913   0.01830  -0.1210   0.6528   1.0000
   4.000   0.9950   0.02929   0.01838  -0.1200   0.6418   1.0000
   4.250   1.0165   0.02965   0.01868  -0.1186   0.6294   1.0000
   4.500   1.0459   0.02950   0.01844  -0.1180   0.6192   1.0000
   4.750   1.0697   0.02968   0.01859  -0.1168   0.6070   1.0000
   5.000   1.0896   0.03010   0.01901  -0.1153   0.5939   1.0000
   5.250   1.1138   0.03027   0.01916  -0.1142   0.5822   1.0000
   5.500   1.1417   0.03022   0.01909  -0.1135   0.5712   1.0000
   5.750   1.1592   0.03077   0.01969  -0.1118   0.5574   1.0000
   6.000   1.1788   0.03119   0.02014  -0.1102   0.5441   1.0000
   6.250   1.2010   0.03145   0.02044  -0.1089   0.5313   1.0000
   6.500   1.2263   0.03153   0.02050  -0.1079   0.5190   1.0000
   6.750   1.2448   0.03198   0.02101  -0.1062   0.5048   1.0000
   7.000   1.2620   0.03251   0.02159  -0.1044   0.4900   1.0000
   7.250   1.2798   0.03302   0.02217  -0.1027   0.4753   1.0000
   7.500   1.2976   0.03350   0.02268  -0.1009   0.4600   1.0000
   7.750   1.3145   0.03398   0.02317  -0.0990   0.4437   1.0000
   8.000   1.3300   0.03452   0.02371  -0.0969   0.4267   1.0000
   8.250   1.3437   0.03514   0.02434  -0.0947   0.4091   1.0000
   8.500   1.3544   0.03586   0.02503  -0.0921   0.3913   1.0000
   8.750   1.3638   0.03671   0.02585  -0.0894   0.3737   1.0000
   9.000   1.3722   0.03771   0.02683  -0.0869   0.3568   1.0000
   9.250   1.3800   0.03885   0.02800  -0.0845   0.3409   1.0000
   9.500   1.3884   0.04009   0.02927  -0.0823   0.3267   1.0000
   9.750   1.3975   0.04137   0.03057  -0.0803   0.3138   1.0000
  10.000   1.4072   0.04263   0.03183  -0.0783   0.3016   1.0000
  10.250   1.4159   0.04399   0.03320  -0.0764   0.2897   1.0000
  10.500   1.4214   0.04570   0.03502  -0.0745   0.2780   1.0000
  10.750   1.4287   0.04729   0.03665  -0.0728   0.2672   1.0000
  11.000   1.4384   0.04868   0.03801  -0.0711   0.2570   1.0000
  11.250   1.4416   0.05079   0.04027  -0.0695   0.2469   1.0000
  11.500   1.4511   0.05238   0.04188  -0.0680   0.2381   1.0000
  11.750   1.4569   0.05437   0.04402  -0.0666   0.2294   1.0000
  12.000   1.4654   0.05618   0.04590  -0.0652   0.2215   1.0000
  12.250   1.4708   0.05829   0.04814  -0.0639   0.2135   1.0000
  12.500   1.4789   0.06021   0.05012  -0.0626   0.2063   1.0000
  12.750   1.4796   0.06287   0.05297  -0.0614   0.1993   1.0000
  13.000   1.4941   0.06419   0.05428  -0.0603   0.1929   1.0000
  13.250   1.4868   0.06789   0.05830  -0.0593   0.1876   1.0000
  13.500   1.4901   0.07044   0.06100  -0.0584   0.1822   1.0000
  13.750   1.5008   0.07222   0.06280  -0.0574   0.1768   1.0000
  14.000   1.4817   0.07735   0.06828  -0.0571   0.1725   1.0000
  14.250   1.4731   0.08124   0.07234  -0.0569   0.1675   1.0000
  14.500   1.4801   0.08301   0.07409  -0.0561   0.1616   1.0000
  14.750   1.4485   0.09041   0.08185  -0.0574   0.1584   1.0000
  15.000   1.4185   0.09817   0.08986  -0.0595   0.1550   1.0000
  15.250   1.4442   0.09659   0.08815  -0.0576   0.1475   1.0000
  15.500   1.3977   0.10782   0.09971  -0.0618   0.1458   1.0000
  15.750   1.3003   0.13181   0.12399  -0.0743   0.1454   1.0000
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