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GOE 388 AIRFOIL (goe388-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 388 AIRFOIL (goe388-il)
Reynolds number: 50,000
Max Cl/Cd: 41.36 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe388-il-50000.txt
Download as CSV file: xf-goe388-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 388 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3470   0.10288   0.09691  -0.0296   1.0000   0.1969
  -7.500  -0.3750   0.10386   0.09809  -0.0267   1.0000   0.1989
  -7.250  -0.4030   0.10522   0.09961  -0.0269   1.0000   0.2000
  -7.000  -0.3757   0.09814   0.09251  -0.0216   1.0000   0.2080
  -6.750  -0.3909   0.09749   0.09197  -0.0199   1.0000   0.2134
  -6.500  -0.4179   0.09907   0.09367  -0.0234   1.0000   0.2167
  -6.250  -0.4036   0.09342   0.08806  -0.0165   1.0000   0.2227
  -6.000  -0.4119   0.09227   0.08697  -0.0166   1.0000   0.2311
  -5.750  -0.4150   0.08971   0.08447  -0.0162   1.0000   0.2365
  -5.500  -0.4138   0.08748   0.08227  -0.0146   1.0000   0.2463
  -5.250  -0.4139   0.08490   0.07974  -0.0147   1.0000   0.2544
  -5.000  -0.3807   0.08075   0.07551  -0.0197   0.9910   0.2776
  -4.750  -0.3449   0.07642   0.07111  -0.0263   0.9804   0.3048
  -4.500  -0.3157   0.07314   0.06777  -0.0324   0.9703   0.3347
  -4.250  -0.2923   0.06939   0.06402  -0.0319   0.9626   0.3577
  -4.000  -0.2675   0.06614   0.06075  -0.0335   0.9545   0.3920
  -3.750  -0.2415   0.06276   0.05735  -0.0340   0.9424   0.4379
  -3.500  -0.2107   0.05892   0.05352  -0.0317   0.9272   0.5051
  -2.500   0.1115   0.03762   0.02881  -0.1097   0.8924   0.1828
  -2.250   0.1542   0.03509   0.02602  -0.1132   0.8884   0.1773
  -2.000   0.1836   0.03368   0.02424  -0.1141   0.8805   0.1783
  -1.750   0.2206   0.03216   0.02233  -0.1161   0.8752   0.1795
  -1.500   0.2602   0.03070   0.02051  -0.1183   0.8715   0.1797
  -1.250   0.2876   0.02979   0.01929  -0.1181   0.8613   0.1820
  -1.000   0.3250   0.02831   0.01765  -0.1190   0.8499   0.1884
  -0.750   0.3624   0.02715   0.01634  -0.1199   0.8404   0.2045
  -0.500   0.3902   0.02641   0.01562  -0.1195   0.8304   0.2268
  -0.250   0.4235   0.02540   0.01477  -0.1201   0.8250   0.2694
   0.000   0.4487   0.02252   0.01371  -0.1183   0.8198   1.0000
   0.250   0.4742   0.02284   0.01364  -0.1179   0.8123   1.0000
   0.500   0.5052   0.02302   0.01355  -0.1186   0.8077   1.0000
   0.750   0.5276   0.02347   0.01384  -0.1180   0.7995   1.0000
   1.000   0.5561   0.02373   0.01395  -0.1184   0.7938   1.0000
   1.250   0.5830   0.02406   0.01417  -0.1185   0.7876   1.0000
   1.500   0.6080   0.02441   0.01445  -0.1182   0.7794   1.0000
   1.750   0.6367   0.02449   0.01447  -0.1182   0.7710   1.0000
   2.000   0.6665   0.02432   0.01423  -0.1179   0.7601   1.0000
   2.250   0.6903   0.02454   0.01443  -0.1171   0.7486   1.0000
   2.500   0.7228   0.02442   0.01431  -0.1174   0.7420   1.0000
   2.750   0.7436   0.02489   0.01482  -0.1165   0.7304   1.0000
   3.000   0.7722   0.02506   0.01502  -0.1165   0.7236   1.0000
   3.250   0.7948   0.02551   0.01555  -0.1158   0.7134   1.0000
   3.500   0.8194   0.02567   0.01580  -0.1150   0.7016   1.0000
   3.750   0.8485   0.02572   0.01594  -0.1148   0.6936   1.0000
   4.000   0.8722   0.02564   0.01593  -0.1134   0.6776   1.0000
   4.250   0.8938   0.02538   0.01572  -0.1114   0.6564   1.0000
   4.500   0.9141   0.02535   0.01582  -0.1095   0.6366   1.0000
   4.750   0.9359   0.02519   0.01574  -0.1077   0.6160   1.0000
   5.000   0.9593   0.02501   0.01561  -0.1061   0.5964   1.0000
   5.250   0.9797   0.02503   0.01568  -0.1042   0.5727   1.0000
   5.500   1.0028   0.02512   0.01587  -0.1029   0.5553   1.0000
   5.750   1.0256   0.02528   0.01607  -0.1015   0.5374   1.0000
   6.000   1.0477   0.02554   0.01642  -0.1001   0.5205   1.0000
   6.250   1.0688   0.02592   0.01692  -0.0987   0.5044   1.0000
   6.500   1.0887   0.02632   0.01746  -0.0970   0.4844   1.0000
   6.750   1.1055   0.02688   0.01818  -0.0950   0.4592   1.0000
   7.000   1.1209   0.02749   0.01888  -0.0927   0.4239   1.0000
   7.250   1.1313   0.02830   0.01935  -0.0895   0.3574   1.0000
   7.500   1.1348   0.02977   0.02036  -0.0858   0.2890   1.0000
   7.750   1.1355   0.03162   0.02185  -0.0823   0.2320   1.0000
   8.000   1.1377   0.03359   0.02356  -0.0793   0.2096   1.0000
   8.250   1.1428   0.03545   0.02535  -0.0767   0.2001   1.0000
   8.500   1.1505   0.03721   0.02707  -0.0744   0.1944   1.0000
   8.750   1.1609   0.03888   0.02872  -0.0721   0.1880   1.0000
   9.000   1.1776   0.04038   0.03010  -0.0700   0.1824   1.0000
   9.250   1.2170   0.04138   0.03114  -0.0694   0.1744   1.0000
   9.500   1.3093   0.04459   0.03392  -0.0756   0.1519   1.0000
   9.750   1.3601   0.04897   0.03823  -0.0784   0.1392   1.0000
  10.000   1.3961   0.05426   0.04343  -0.0801   0.1271   1.0000
  10.250   1.3974   0.05650   0.04627  -0.0766   0.1219   1.0000
  10.500   1.4231   0.06203   0.05178  -0.0773   0.1129   1.0000
  10.750   1.4187   0.06440   0.05473  -0.0734   0.1097   1.0000
  11.000   1.4384   0.07003   0.06028  -0.0738   0.1013   1.0000
  11.250   1.4233   0.07213   0.06300  -0.0691   0.0993   1.0000
  11.500   1.4119   0.07498   0.06626  -0.0654   0.0962   1.0000
  11.750   1.4159   0.07946   0.07079  -0.0643   0.0899   1.0000
  12.000   1.3958   0.08226   0.07399  -0.0602   0.0887   1.0000
  12.250   1.3749   0.08521   0.07725  -0.0564   0.0878   1.0000
  12.500   1.3532   0.08848   0.08078  -0.0532   0.0871   1.0000
  12.750   1.3303   0.09221   0.08474  -0.0509   0.0870   1.0000
  13.000   1.3063   0.09645   0.08922  -0.0494   0.0874   1.0000
  13.250   1.2818   0.10126   0.09424  -0.0490   0.0881   1.0000
  13.500   1.2584   0.10661   0.09978  -0.0494   0.0889   1.0000
  13.750   1.2362   0.11246   0.10578  -0.0507   0.0897   1.0000
  14.000   1.2160   0.11869   0.11214  -0.0526   0.0904   1.0000
  14.250   1.1978   0.12527   0.11881  -0.0552   0.0909   1.0000
  14.500   0.7623   0.17597   0.16973  -0.0835   0.3382   1.0000
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