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GOE 481 AIRFOIL (goe481-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 481 AIRFOIL (goe481-il)
Reynolds number: 50,000
Max Cl/Cd: 28.93 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe481-il-50000-n5.txt
Download as CSV file: xf-goe481-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 481 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
  ------ -------- --------- --------- -------- -------- --------
  -6.500  -0.1322   0.12178   0.11493  -0.0329   0.9606   0.1132
  -6.250  -0.1180   0.11937   0.11253  -0.0359   0.9526   0.1135
  -6.000  -0.1100   0.11731   0.11050  -0.0374   0.9421   0.1136
  -5.750  -0.0917   0.11430   0.10749  -0.0403   0.9348   0.1145
  -5.500  -0.0818   0.11200   0.10522  -0.0415   0.9235   0.1154
  -5.250  -0.0683   0.10956   0.10278  -0.0439   0.9133   0.1161
  -5.000  -0.0512   0.10686   0.10007  -0.0471   0.9035   0.1165
  -4.750  -0.0404   0.10451   0.09774  -0.0486   0.8911   0.1167
  -4.250  -0.0093   0.09911   0.09234  -0.0526   0.8694   0.1179
  -3.750   0.0252   0.09414   0.08734  -0.0577   0.8465   0.1198
  -3.500   0.0530   0.09077   0.08392  -0.0619   0.8395   0.1202
  -3.250   0.0608   0.08885   0.08201  -0.0616   0.8247   0.1212
  -3.000   0.0935   0.08585   0.07894  -0.0670   0.8179   0.1228
  -2.750   0.1035   0.08395   0.07704  -0.0671   0.8032   0.1233
  -2.500   0.1347   0.08077   0.07379  -0.0710   0.7968   0.1247
  -2.250   0.1522   0.07920   0.07217  -0.0730   0.7826   0.1258
  -2.000   0.1823   0.07606   0.06899  -0.0761   0.7761   0.1272
  -1.750   0.2033   0.07427   0.06713  -0.0781   0.7637   0.1285
  -1.500   0.2358   0.07152   0.06429  -0.0817   0.7561   0.1298
  -1.250   0.2791   0.06862   0.06126  -0.0871   0.7515   0.1318
  -1.000   0.2953   0.06726   0.05986  -0.0877   0.7372   0.1326
  -0.750   0.3361   0.06457   0.05704  -0.0920   0.7314   0.1350
  -0.500   0.3627   0.06290   0.05528  -0.0940   0.7206   0.1358
  -0.250   0.3965   0.06076   0.05304  -0.0968   0.7122   0.1381
   0.000   0.4423   0.05806   0.05018  -0.1015   0.7071   0.1399
   0.250   0.4647   0.05708   0.04912  -0.1023   0.6945   0.1417
   0.500   0.5050   0.05495   0.04686  -0.1058   0.6874   0.1438
   0.750   0.5609   0.05285   0.04450  -0.1118   0.6823   0.1468
   1.000   0.5719   0.05198   0.04364  -0.1103   0.6691   0.1486
   1.250   0.6181   0.05022   0.04167  -0.1144   0.6621   0.1521
   1.500   0.6604   0.04918   0.04042  -0.1177   0.6539   0.1565
   1.750   0.6787   0.04793   0.03916  -0.1172   0.6432   0.1596
   2.000   0.7256   0.04621   0.03723  -0.1210   0.6365   0.1654
   2.250   0.7516   0.04573   0.03664  -0.1216   0.6266   0.1707
   2.500   0.7817   0.04511   0.03589  -0.1226   0.6171   0.1776
   2.750   0.8289   0.04343   0.03402  -0.1263   0.6105   0.1875
   3.000   0.8410   0.04384   0.03439  -0.1244   0.5994   0.1952
   3.250   0.8729   0.04317   0.03361  -0.1255   0.5910   0.2053
   3.500   0.9223   0.04178   0.03203  -0.1295   0.5849   0.2174
   3.750   0.9197   0.04231   0.03266  -0.1251   0.5740   0.2213
   4.000   0.9519   0.04183   0.03208  -0.1261   0.5659   0.2316
   4.250   0.9937   0.04093   0.03103  -0.1287   0.5591   0.2479
   4.500   0.9928   0.04181   0.03199  -0.1246   0.5489   0.2587
   4.750   1.0213   0.04117   0.03132  -0.1252   0.5415   0.2784
   5.000   1.0664   0.04045   0.03042  -0.1281   0.5354   0.3077
   5.250   1.0556   0.04142   0.03156  -0.1225   0.5257   0.3138
   5.500   1.0795   0.04135   0.03145  -0.1220   0.5179   0.3248
   5.750   1.1289   0.04033   0.03027  -0.1254   0.5117   0.3426
   6.000   1.1129   0.04198   0.03209  -0.1191   0.5018   0.3443
   6.250   1.1380   0.04218   0.03219  -0.1186   0.4932   0.3538
   6.500   1.1713   0.04171   0.03161  -0.1195   0.4846   0.3604
   6.750   1.1664   0.04298   0.03296  -0.1149   0.4741   0.3618
   7.000   1.2102   0.04225   0.03202  -0.1168   0.4653   0.3675
   7.250   1.2030   0.04377   0.03364  -0.1122   0.4557   0.3681
   7.500   1.2189   0.04434   0.03417  -0.1105   0.4469   0.3704
   7.750   1.2658   0.04375   0.03336  -0.1128   0.4405   0.3737
   8.000   1.2418   0.04623   0.03609  -0.1065   0.4313   0.3731
   8.250   1.2576   0.04698   0.03681  -0.1050   0.4239   0.3742
   8.500   1.3080   0.04601   0.03563  -0.1077   0.4178   0.3779
   8.750   1.2743   0.04934   0.03923  -0.1009   0.4087   0.3766
   9.000   1.2903   0.05004   0.03993  -0.0998   0.4011   0.3787
   9.250   1.3375   0.04901   0.03870  -0.1015   0.3947   0.3821
   9.500   1.2938   0.05342   0.04342  -0.0950   0.3851   0.3805
   9.750   1.3146   0.05383   0.04380  -0.0942   0.3778   0.3820
  10.000   1.3486   0.05344   0.04331  -0.0944   0.3714   0.3829
  10.250   1.2974   0.05927   0.04943  -0.0890   0.3611   0.3816
  10.500   1.3260   0.05911   0.04923  -0.0886   0.3548   0.3817
  10.750   1.3504   0.05939   0.04946  -0.0880   0.3487   0.3810
  11.000   1.2833   0.06792   0.05831  -0.0842   0.3368   0.3804
  11.250   1.3244   0.06631   0.05661  -0.0837   0.3319   0.3794
  11.500   1.2412   0.07843   0.06905  -0.0824   0.3173   0.3792
  11.750   1.2667   0.07820   0.06878  -0.0815   0.3120   0.3784
  12.000   1.3146   0.07530   0.06577  -0.0804   0.3089   0.3768
  12.500   1.2415   0.09118   0.08195  -0.0812   0.2884   0.3764
  12.750   1.2827   0.08864   0.07935  -0.0796   0.2864   0.3746
  13.250   1.2076   0.10712   0.09808  -0.0835   0.2664   0.3747
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