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GOE 494 AIRFOIL (goe494-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 494 AIRFOIL (goe494-il)
Reynolds number: 50,000
Max Cl/Cd: 45.48 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe494-il-50000-n5.txt
Download as CSV file: xf-goe494-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 494 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3458   0.10302   0.09640  -0.0292   1.0000   0.0815
  -7.250  -0.3559   0.10244   0.09596  -0.0284   1.0000   0.0836
  -7.000  -0.3633   0.10204   0.09571  -0.0302   1.0000   0.0848
  -6.750  -0.3570   0.09717   0.09089  -0.0266   1.0000   0.0885
  -6.500  -0.3561   0.09488   0.08866  -0.0254   1.0000   0.0934
  -6.250  -0.3590   0.09374   0.08762  -0.0275   1.0000   0.0977
  -6.000  -0.3551   0.09298   0.08693  -0.0349   1.0000   0.0992
  -5.750  -0.3554   0.08804   0.08206  -0.0265   1.0000   0.1029
  -5.500  -0.3518   0.08551   0.07957  -0.0262   1.0000   0.1072
  -5.250  -0.3341   0.08395   0.07802  -0.0382   1.0000   0.1136
  -5.000  -0.3358   0.08002   0.07416  -0.0323   1.0000   0.1155
  -4.750  -0.3298   0.07710   0.07125  -0.0310   1.0000   0.1192
  -4.500  -0.3073   0.07387   0.06798  -0.0392   1.0000   0.1290
  -4.250  -0.3036   0.07118   0.06532  -0.0358   1.0000   0.1369
  -3.750  -0.1852   0.05511   0.04839  -0.0674   0.9981   0.0711
  -3.500  -0.1531   0.05087   0.04405  -0.0712   0.9946   0.0681
  -3.250  -0.0858   0.04391   0.03633  -0.0852   0.9928   0.0710
  -3.000  -0.0397   0.03936   0.03130  -0.0918   0.9903   0.0700
  -2.750   0.0088   0.03530   0.02653  -0.0982   0.9884   0.0697
  -2.500   0.0473   0.03312   0.02396  -0.1020   0.9853   0.0771
  -2.250   0.0888   0.03074   0.02092  -0.1057   0.9823   0.0780
  -2.000   0.1286   0.02890   0.01845  -0.1085   0.9793   0.0773
  -1.750   0.1651   0.02761   0.01666  -0.1105   0.9756   0.0771
  -1.500   0.1996   0.02667   0.01530  -0.1121   0.9711   0.0774
  -1.250   0.2360   0.02598   0.01427  -0.1139   0.9673   0.0781
  -1.000   0.2681   0.02550   0.01349  -0.1149   0.9619   0.0798
  -0.750   0.3032   0.02514   0.01287  -0.1164   0.9570   0.0822
  -0.500   0.3379   0.02486   0.01238  -0.1180   0.9518   0.0864
  -0.250   0.3714   0.02462   0.01206  -0.1194   0.9457   0.0946
   0.000   0.4100   0.02428   0.01183  -0.1219   0.9412   0.1213
   0.250   0.4416   0.02335   0.01225  -0.1234   0.9357   0.4646
   0.500   0.4675   0.02250   0.01217  -0.1229   0.9287   1.0000
   0.750   0.4968   0.02288   0.01229  -0.1235   0.9213   1.0000
   1.000   0.5304   0.02325   0.01246  -0.1249   0.9153   1.0000
   1.250   0.5586   0.02366   0.01273  -0.1253   0.9079   1.0000
   1.500   0.5915   0.02403   0.01301  -0.1265   0.9016   1.0000
   1.750   0.6191   0.02445   0.01339  -0.1268   0.8940   1.0000
   2.000   0.6515   0.02482   0.01378  -0.1279   0.8876   1.0000
   2.250   0.6781   0.02527   0.01425  -0.1280   0.8795   1.0000
   2.500   0.7112   0.02562   0.01467  -0.1292   0.8732   1.0000
   2.750   0.7360   0.02611   0.01529  -0.1290   0.8642   1.0000
   3.000   0.7716   0.02640   0.01573  -0.1304   0.8584   1.0000
   3.500   0.8229   0.02734   0.01706  -0.1300   0.8395   1.0000
   3.750   0.8611   0.02738   0.01738  -0.1314   0.8310   1.0000
   4.000   0.8919   0.02719   0.01746  -0.1309   0.8134   1.0000
   4.250   0.9283   0.02653   0.01716  -0.1306   0.7935   1.0000
   4.500   0.9692   0.02562   0.01671  -0.1305   0.7749   1.0000
   4.750   1.0066   0.02323   0.01461  -0.1267   0.7155   1.0000
   5.000   1.0224   0.02248   0.01398  -0.1213   0.6248   1.0000
   5.250   1.0240   0.02458   0.01336  -0.1140   0.2376   1.0000
   5.500   1.0265   0.02790   0.01541  -0.1109   0.0836   1.0000
   5.750   1.0400   0.03001   0.01740  -0.1086   0.0633   1.0000
   6.000   1.0539   0.03208   0.01953  -0.1065   0.0533   1.0000
   6.250   1.0714   0.03386   0.02160  -0.1045   0.0488   1.0000
   6.500   1.0911   0.03609   0.02393  -0.1030   0.0430   1.0000
   6.750   1.1201   0.03828   0.02637  -0.1022   0.0389   1.0000
   7.000   1.1547   0.04092   0.02925  -0.1021   0.0366   1.0000
   7.250   1.1845   0.04391   0.03252  -0.1019   0.0338   1.0000
   7.500   1.2100   0.04766   0.03652  -0.1014   0.0314   1.0000
   7.750   1.2309   0.05086   0.04030  -0.0998   0.0305   1.0000
   8.000   1.2480   0.05456   0.04453  -0.0980   0.0302   1.0000
   8.250   1.2604   0.05845   0.04895  -0.0959   0.0301   1.0000
   8.500   1.2684   0.06250   0.05350  -0.0936   0.0301   1.0000
   8.750   1.2724   0.06665   0.05812  -0.0911   0.0302   1.0000
   9.000   1.2718   0.07080   0.06271  -0.0885   0.0302   1.0000
   9.250   1.2666   0.07495   0.06726  -0.0859   0.0302   1.0000
   9.500   1.2574   0.07904   0.07171  -0.0833   0.0301   1.0000
   9.750   1.2437   0.08295   0.07590  -0.0806   0.0302   1.0000
  10.000   1.2272   0.08688   0.08006  -0.0783   0.0303   1.0000
  10.250   1.2098   0.09119   0.08457  -0.0770   0.0304   1.0000
  10.500   1.1922   0.09595   0.08951  -0.0767   0.0306   1.0000
  10.750   1.1752   0.10119   0.09491  -0.0776   0.0308   1.0000
  11.000   1.1591   0.10689   0.10073  -0.0794   0.0311   1.0000
  11.250   1.1441   0.11305   0.10699  -0.0820   0.0313   1.0000
  11.500   1.1328   0.11938   0.11339  -0.0850   0.0316   1.0000
  11.750   1.1237   0.12590   0.11995  -0.0882   0.0318   1.0000
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