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GOE 388 AIRFOIL (goe388-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 388 AIRFOIL (goe388-il)
Reynolds number: 100,000
Max Cl/Cd: 55.79 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe388-il-100000.txt
Download as CSV file: xf-goe388-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3305   0.10493   0.10044  -0.0406   1.0000   0.0861
  -8.500  -0.3528   0.10544   0.10111  -0.0389   1.0000   0.0868
  -8.250  -0.3779   0.10590   0.10171  -0.0355   1.0000   0.0870
  -8.000  -0.3888   0.10540   0.10130  -0.0414   0.9962   0.0875
  -7.750  -0.3432   0.09542   0.09123  -0.0367   0.9943   0.0914
  -7.500  -0.3206   0.09134   0.08711  -0.0409   0.9863   0.0956
  -7.250  -0.2938   0.08787   0.08357  -0.0609   0.9706   0.1028
  -7.000  -0.2733   0.08206   0.07776  -0.0635   0.9652   0.1049
  -6.750  -0.2523   0.07854   0.07422  -0.0611   0.9592   0.1095
  -6.500  -0.2173   0.07399   0.06951  -0.0807   0.9464   0.1197
  -6.250  -0.1923   0.06944   0.06496  -0.0775   0.9366   0.1229
  -6.000  -0.1658   0.06602   0.06145  -0.0816   0.9220   0.1305
  -5.750  -0.1407   0.06186   0.05717  -0.0894   0.9102   0.1374
  -5.500  -0.1052   0.05912   0.05411  -0.0998   0.8993   0.1514
  -5.250  -0.0927   0.05543   0.05055  -0.0962   0.8909   0.1538
  -5.000  -0.0651   0.05275   0.04766  -0.1014   0.8803   0.1685
  -4.750  -0.0366   0.05057   0.04527  -0.1052   0.8724   0.1841
  -4.500  -0.0236   0.04732   0.04217  -0.1026   0.8649   0.1871
  -4.250   0.0026   0.04488   0.03960  -0.1054   0.8589   0.2026
  -4.000   0.0281   0.04261   0.03721  -0.1072   0.8527   0.2189
  -3.750   0.0509   0.04044   0.03496  -0.1078   0.8416   0.2358
  -3.500   0.0729   0.03834   0.03280  -0.1079   0.8302   0.2532
  -3.250   0.0964   0.03632   0.03075  -0.1080   0.8247   0.2720
  -3.000   0.1699   0.02806   0.02070  -0.1202   0.8202   0.1327
  -2.750   0.2020   0.02523   0.01727  -0.1212   0.8160   0.1169
  -2.500   0.2309   0.02332   0.01509  -0.1216   0.8098   0.1126
  -2.250   0.2616   0.02171   0.01309  -0.1221   0.8074   0.1089
  -2.000   0.2909   0.02056   0.01164  -0.1224   0.8049   0.1077
  -1.750   0.3192   0.01969   0.01064  -0.1226   0.8023   0.1084
  -1.500   0.3471   0.01907   0.00997  -0.1228   0.8001   0.1124
  -1.250   0.3753   0.01860   0.00939  -0.1229   0.7979   0.1178
  -1.000   0.4032   0.01792   0.00877  -0.1231   0.7960   0.1216
  -0.750   0.4309   0.01745   0.00841  -0.1233   0.7943   0.1280
  -0.500   0.4591   0.01697   0.00798  -0.1233   0.7915   0.1382
  -0.250   0.4849   0.01659   0.00772  -0.1230   0.7854   0.1601
   0.000   0.5098   0.01389   0.00730  -0.1219   0.7791   1.0000
   0.250   0.5375   0.01393   0.00702  -0.1215   0.7716   1.0000
   0.500   0.5640   0.01397   0.00686  -0.1211   0.7616   1.0000
   0.750   0.5898   0.01395   0.00667  -0.1204   0.7478   1.0000
   1.000   0.6158   0.01397   0.00653  -0.1198   0.7346   1.0000
   1.250   0.6415   0.01399   0.00642  -0.1191   0.7200   1.0000
   1.500   0.6665   0.01403   0.00633  -0.1184   0.7028   1.0000
   1.750   0.6910   0.01409   0.00628  -0.1175   0.6838   1.0000
   2.000   0.7155   0.01417   0.00629  -0.1168   0.6651   1.0000
   2.250   0.7401   0.01427   0.00637  -0.1162   0.6478   1.0000
   2.500   0.7643   0.01438   0.00641  -0.1154   0.6261   1.0000
   2.750   0.7887   0.01451   0.00650  -0.1147   0.6041   1.0000
   3.000   0.8122   0.01466   0.00648  -0.1137   0.5729   1.0000
   3.250   0.8340   0.01495   0.00649  -0.1124   0.5330   1.0000
   3.500   0.8556   0.01537   0.00669  -0.1113   0.4953   1.0000
   3.750   0.8754   0.01592   0.00697  -0.1099   0.4375   1.0000
   4.000   0.8911   0.01683   0.00736  -0.1080   0.3563   1.0000
   4.250   0.9070   0.01786   0.00796  -0.1063   0.2917   1.0000
   4.500   0.9143   0.01986   0.00899  -0.1036   0.1267   1.0000
   4.750   0.9334   0.02070   0.00976  -0.1024   0.1160   1.0000
   5.000   0.9539   0.02137   0.01046  -0.1014   0.1112   1.0000
   5.250   0.9740   0.02203   0.01120  -0.1003   0.1078   1.0000
   5.500   0.9929   0.02279   0.01206  -0.0991   0.1050   1.0000
   5.750   1.0098   0.02368   0.01302  -0.0976   0.1027   1.0000
   6.000   1.0259   0.02456   0.01398  -0.0961   0.1010   1.0000
   6.250   1.0422   0.02537   0.01489  -0.0945   0.0994   1.0000
   6.500   1.0569   0.02626   0.01587  -0.0927   0.0978   1.0000
   6.750   1.0701   0.02724   0.01694  -0.0907   0.0962   1.0000
   7.000   1.0817   0.02827   0.01800  -0.0885   0.0946   1.0000
   7.250   1.0934   0.02941   0.01912  -0.0864   0.0929   1.0000
   7.500   1.1091   0.03073   0.02031  -0.0849   0.0909   1.0000
   7.750   1.1281   0.03165   0.02130  -0.0837   0.0879   1.0000
   8.000   1.1513   0.03289   0.02247  -0.0834   0.0834   1.0000
   8.250   1.1797   0.03421   0.02376  -0.0838   0.0791   1.0000
   8.500   1.2212   0.03663   0.02574  -0.0869   0.0699   1.0000
   8.750   1.3042   0.04885   0.03729  -0.0976   0.0532   1.0000
   9.000   1.3143   0.05152   0.04050  -0.0952   0.0488   1.0000
   9.250   1.3312   0.05573   0.04504  -0.0940   0.0447   1.0000
   9.500   1.3387   0.05788   0.04770  -0.0912   0.0418   1.0000
   9.750   1.3485   0.06143   0.05164  -0.0890   0.0400   1.0000
  10.000   1.3524   0.06372   0.05438  -0.0860   0.0377   1.0000
  10.250   1.3756   0.07118   0.06185  -0.0868   0.0361   1.0000
  10.500   1.3616   0.07081   0.06216  -0.0811   0.0355   1.0000
  10.750   1.3567   0.07279   0.06456  -0.0773   0.0345   1.0000
  11.000   1.3548   0.07603   0.06814  -0.0745   0.0336   1.0000
  11.250   1.3573   0.08059   0.07290  -0.0727   0.0328   1.0000
  11.500   1.3939   0.09198   0.08408  -0.0763   0.0320   1.0000
  11.750   1.3729   0.09325   0.08579  -0.0715   0.0319   1.0000
  12.000   1.3510   0.09486   0.08776  -0.0670   0.0318   1.0000
  12.250   1.3276   0.09674   0.08993  -0.0626   0.0318   1.0000
  12.500   1.3037   0.09898   0.09239  -0.0588   0.0318   1.0000
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