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GOE 395 AIRFOIL (goe395-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 395 AIRFOIL (goe395-il)
Reynolds number: 1,000,000
Max Cl/Cd: 157.32 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe395-il-1000000.txt
Download as CSV file: xf-goe395-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 395 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  -0.1571   0.08436   0.08193  -0.0425   0.7522   0.0167
  -8.250  -0.1540   0.08068   0.07825  -0.0445   0.7508   0.0169
  -8.000  -0.1487   0.07713   0.07470  -0.0460   0.7495   0.0170
  -7.750  -0.1432   0.07351   0.07107  -0.0474   0.7481   0.0170
  -7.500  -0.1403   0.06896   0.06652  -0.0484   0.7467   0.0173
  -7.250  -0.1293   0.06670   0.06425  -0.0489   0.7453   0.0176
  -7.000  -0.1188   0.06434   0.06189  -0.0499   0.7439   0.0180
  -6.750  -0.1088   0.06186   0.05942  -0.0511   0.7430   0.0186
  -6.500  -0.0960   0.05877   0.05634  -0.0537   0.7419   0.0197
  -6.250  -0.0783   0.05370   0.05126  -0.0614   0.7407   0.0214
  -6.000  -0.0602   0.04921   0.04675  -0.0665   0.7395   0.0215
  -5.750  -0.0445   0.04269   0.04022  -0.0727   0.7385   0.0220
  -5.500  -0.0258   0.04099   0.03851  -0.0736   0.7372   0.0225
  -5.250  -0.0045   0.03875   0.03625  -0.0760   0.7355   0.0231
  -5.000   0.0195   0.03603   0.03350  -0.0797   0.7335   0.0245
  -4.500   0.1653   0.01331   0.00875  -0.1436   0.7357   0.0282
  -4.250   0.1944   0.01248   0.00779  -0.1442   0.7337   0.0290
  -4.000   0.2231   0.01204   0.00724  -0.1444   0.7316   0.0298
  -3.750   0.2522   0.01135   0.00636  -0.1448   0.7295   0.0303
  -3.500   0.2814   0.01071   0.00558  -0.1451   0.7280   0.0308
  -3.250   0.3106   0.01016   0.00491  -0.1454   0.7265   0.0314
  -3.000   0.3396   0.00970   0.00435  -0.1455   0.7249   0.0320
  -2.750   0.3685   0.00937   0.00394  -0.1457   0.7230   0.0328
  -2.500   0.3973   0.00911   0.00362  -0.1457   0.7209   0.0336
  -2.250   0.4260   0.00887   0.00331  -0.1458   0.7187   0.0340
  -2.000   0.4548   0.00856   0.00292  -0.1458   0.7164   0.0345
  -1.750   0.4837   0.00824   0.00249  -0.1459   0.7141   0.0356
  -1.500   0.5125   0.00800   0.00224  -0.1460   0.7124   0.0370
  -1.250   0.5413   0.00783   0.00207  -0.1460   0.7105   0.0385
  -1.000   0.5701   0.00770   0.00193  -0.1461   0.7086   0.0405
  -0.750   0.5987   0.00760   0.00182  -0.1461   0.7064   0.0427
  -0.500   0.6274   0.00745   0.00171  -0.1461   0.7040   0.0521
  -0.250   0.6558   0.00742   0.00175  -0.1461   0.7016   0.0685
   0.000   0.6840   0.00751   0.00183  -0.1460   0.6989   0.0752
   0.250   0.7125   0.00747   0.00182  -0.1460   0.6969   0.0790
   0.500   0.7410   0.00740   0.00180  -0.1460   0.6937   0.0835
   0.750   0.7693   0.00736   0.00177  -0.1459   0.6898   0.0868
   1.000   0.7975   0.00735   0.00176  -0.1459   0.6864   0.0895
   1.250   0.8257   0.00735   0.00174  -0.1458   0.6830   0.0928
   1.500   0.8542   0.00725   0.00172  -0.1459   0.6797   0.0976
   1.750   0.8826   0.00719   0.00168  -0.1458   0.6745   0.1009
   2.000   0.9105   0.00719   0.00166  -0.1457   0.6686   0.1041
   2.250   0.9390   0.00709   0.00163  -0.1458   0.6626   0.1086
   2.500   0.9672   0.00704   0.00162  -0.1457   0.6563   0.1139
   2.750   0.9954   0.00701   0.00162  -0.1457   0.6486   0.1189
   3.000   1.0234   0.00697   0.00161  -0.1457   0.6362   0.1306
   3.250   1.0510   0.00695   0.00162  -0.1455   0.6104   0.1593
   3.500   1.0752   0.00730   0.00184  -0.1451   0.5332   0.2775
   3.750   1.1002   0.00752   0.00230  -0.1449   0.4913   0.5529
   4.000   1.1263   0.00776   0.00251  -0.1446   0.4668   0.5959
   4.250   1.1484   0.00730   0.00270  -0.1435   0.4469   1.0000
   4.500   1.1746   0.00757   0.00288  -0.1433   0.4253   1.0000
   4.750   1.2006   0.00787   0.00308  -0.1430   0.4046   1.0000
   5.000   1.2256   0.00828   0.00333  -0.1426   0.3736   1.0000
   5.250   1.2505   0.00868   0.00359  -0.1422   0.3442   1.0000
   5.500   1.2755   0.00905   0.00385  -0.1418   0.3180   1.0000
   5.750   1.2996   0.00951   0.00416  -0.1413   0.2869   1.0000
   6.000   1.3219   0.01017   0.00457  -0.1405   0.2408   1.0000
   6.250   1.3410   0.01117   0.00519  -0.1394   0.1733   1.0000
   6.500   1.3617   0.01196   0.00575  -0.1384   0.1343   1.0000
   6.750   1.3843   0.01251   0.00619  -0.1377   0.1156   1.0000
   7.000   1.4076   0.01295   0.00657  -0.1370   0.1027   1.0000
   7.250   1.4303   0.01344   0.00698  -0.1363   0.0868   1.0000
   7.500   1.4507   0.01414   0.00751  -0.1353   0.0614   1.0000
   7.750   1.4708   0.01485   0.00811  -0.1342   0.0439   1.0000
   8.000   1.4871   0.01590   0.00895  -0.1325   0.0191   1.0000
   8.250   1.5070   0.01655   0.00960  -0.1314   0.0161   1.0000
   8.500   1.5265   0.01720   0.01030  -0.1301   0.0142   1.0000
   8.750   1.5465   0.01776   0.01091  -0.1289   0.0135   1.0000
   9.000   1.5652   0.01839   0.01159  -0.1276   0.0126   1.0000
   9.250   1.5820   0.01914   0.01238  -0.1260   0.0118   1.0000
   9.500   1.5935   0.02024   0.01357  -0.1236   0.0109   1.0000
   9.750   1.6067   0.02096   0.01436  -0.1214   0.0105   1.0000
  10.000   1.6203   0.02167   0.01512  -0.1193   0.0102   1.0000
  10.250   1.6322   0.02251   0.01603  -0.1172   0.0098   1.0000
  10.500   1.6432   0.02347   0.01705  -0.1150   0.0094   1.0000
  10.750   1.6537   0.02451   0.01815  -0.1130   0.0090   1.0000
  11.000   1.6629   0.02568   0.01939  -0.1109   0.0087   1.0000
  11.250   1.6702   0.02707   0.02084  -0.1088   0.0084   1.0000
  11.500   1.6727   0.02894   0.02281  -0.1064   0.0081   1.0000
  11.750   1.6662   0.03171   0.02572  -0.1034   0.0078   1.0000
  12.000   1.6717   0.03346   0.02757  -0.1016   0.0077   1.0000
  12.250   1.6795   0.03503   0.02922  -0.1001   0.0076   1.0000
  12.500   1.6860   0.03675   0.03102  -0.0986   0.0074   1.0000
  12.750   1.6903   0.03872   0.03309  -0.0970   0.0073   1.0000
  13.000   1.6943   0.04072   0.03518  -0.0956   0.0071   1.0000
  13.250   1.6978   0.04282   0.03737  -0.0941   0.0070   1.0000
  13.500   1.7010   0.04498   0.03962  -0.0928   0.0068   1.0000
  13.750   1.7036   0.04720   0.04193  -0.0916   0.0066   1.0000
  14.000   1.7049   0.04961   0.04442  -0.0904   0.0064   1.0000
  14.250   1.7054   0.05215   0.04705  -0.0892   0.0063   1.0000
  14.500   1.7049   0.05487   0.04985  -0.0882   0.0062   1.0000
  14.750   1.7029   0.05786   0.05294  -0.0873   0.0061   1.0000
  15.000   1.6996   0.06113   0.05630  -0.0866   0.0060   1.0000
  15.250   1.6942   0.06475   0.06002  -0.0860   0.0059   1.0000
  15.500   1.6865   0.06879   0.06417  -0.0856   0.0058   1.0000
  15.750   1.6756   0.07343   0.06893  -0.0854   0.0057   1.0000
  16.000   1.6623   0.07854   0.07418  -0.0854   0.0056   1.0000
  16.250   1.6425   0.08464   0.08045  -0.0856   0.0055   1.0000
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