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GOE 359 AIRFOIL (goe359-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 359 AIRFOIL (goe359-il)
Reynolds number: 100,000
Max Cl/Cd: 63 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe359-il-100000-n5.txt
Download as CSV file: xf-goe359-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 359 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2493   0.09787   0.09350  -0.0282   1.0000   0.0310
  -7.250  -0.2535   0.09612   0.09187  -0.0268   1.0000   0.0315
  -7.000  -0.2629   0.09489   0.09076  -0.0245   1.0000   0.0318
  -6.750  -0.2492   0.09162   0.08753  -0.0283   0.9931   0.0332
  -6.500  -0.2181   0.08771   0.08361  -0.0388   0.9786   0.0372
  -6.250  -0.1798   0.08408   0.07991  -0.0532   0.9600   0.0382
  -6.000  -0.1455   0.07956   0.07531  -0.0624   0.9465   0.0384
  -5.750  -0.1109   0.07468   0.07032  -0.0704   0.9353   0.0385
  -5.500  -0.0874   0.06878   0.06442  -0.0742   0.9261   0.0391
  -5.250  -0.0713   0.06462   0.06026  -0.0738   0.9155   0.0406
  -5.000  -0.0438   0.06111   0.05668  -0.0773   0.9050   0.0447
  -4.500   0.0358   0.05215   0.04736  -0.0934   0.8826   0.0529
  -4.250   0.0633   0.04900   0.04408  -0.0960   0.8703   0.0562
  -4.000   0.0989   0.04552   0.04039  -0.1012   0.8582   0.0661
  -3.750   0.1291   0.04293   0.03763  -0.1041   0.8463   0.0792
  -3.500   0.1728   0.03789   0.03211  -0.1093   0.8359   0.0604
  -3.250   0.2052   0.03459   0.02851  -0.1117   0.8241   0.0586
  -3.000   0.2384   0.03139   0.02489  -0.1137   0.8123   0.0567
  -2.750   0.2773   0.02737   0.01996  -0.1158   0.8017   0.0515
  -2.500   0.3034   0.02608   0.01863  -0.1163   0.7900   0.0553
  -2.250   0.3334   0.02440   0.01655  -0.1167   0.7788   0.0569
  -2.000   0.3632   0.02266   0.01433  -0.1169   0.7669   0.0555
  -1.750   0.3925   0.02129   0.01253  -0.1169   0.7555   0.0549
  -1.500   0.4212   0.02022   0.01109  -0.1168   0.7443   0.0550
  -1.250   0.4496   0.01936   0.00994  -0.1166   0.7334   0.0556
  -1.000   0.4770   0.01867   0.00903  -0.1163   0.7216   0.0565
  -0.750   0.5043   0.01822   0.00840  -0.1160   0.7103   0.0604
  -0.500   0.5316   0.01779   0.00778  -0.1156   0.6996   0.0624
  -0.250   0.5587   0.01735   0.00720  -0.1152   0.6893   0.0626
   0.000   0.5853   0.01700   0.00678  -0.1148   0.6779   0.0628
   0.250   0.6118   0.01672   0.00644  -0.1143   0.6676   0.0633
   0.500   0.6384   0.01651   0.00611  -0.1139   0.6583   0.0643
   0.750   0.6652   0.01641   0.00591  -0.1135   0.6477   0.0658
   1.000   0.6922   0.01636   0.00578  -0.1132   0.6372   0.0682
   1.250   0.7192   0.01635   0.00567  -0.1128   0.6269   0.0721
   1.500   0.7460   0.01634   0.00564  -0.1125   0.6164   0.0833
   1.750   0.7723   0.01595   0.00579  -0.1124   0.6048   0.3015
   2.250   0.8232   0.01500   0.00581  -0.1110   0.5823   1.0000
   2.750   0.8744   0.01542   0.00599  -0.1100   0.5592   1.0000
   3.000   0.9001   0.01565   0.00614  -0.1095   0.5491   1.0000
   3.500   0.9517   0.01614   0.00653  -0.1087   0.5316   1.0000
   3.750   0.9773   0.01639   0.00676  -0.1083   0.5229   1.0000
   4.000   1.0027   0.01665   0.00700  -0.1078   0.5138   1.0000
   4.250   1.0279   0.01692   0.00728  -0.1074   0.5044   1.0000
   4.500   1.0533   0.01719   0.00755  -0.1069   0.4962   1.0000
   4.750   1.0781   0.01748   0.00789  -0.1064   0.4862   1.0000
   5.000   1.1025   0.01776   0.00821  -0.1058   0.4754   1.0000
   5.250   1.1266   0.01805   0.00853  -0.1051   0.4635   1.0000
   5.500   1.1502   0.01834   0.00884  -0.1044   0.4508   1.0000
   5.750   1.1734   0.01865   0.00917  -0.1036   0.4373   1.0000
   6.000   1.1944   0.01896   0.00950  -0.1024   0.4139   1.0000
   6.250   1.2135   0.01933   0.00981  -0.1009   0.3824   1.0000
   6.500   1.2329   0.01978   0.01019  -0.0996   0.3507   1.0000
   6.750   1.2512   0.02036   0.01064  -0.0982   0.3120   1.0000
   7.000   1.2665   0.02122   0.01122  -0.0965   0.2705   1.0000
   7.250   1.2816   0.02219   0.01198  -0.0948   0.2392   1.0000
   7.500   1.2953   0.02331   0.01289  -0.0931   0.2062   1.0000
   7.750   1.3083   0.02448   0.01389  -0.0913   0.1598   1.0000
   8.000   1.3130   0.02632   0.01523  -0.0886   0.0989   1.0000
   8.250   1.3147   0.02836   0.01691  -0.0854   0.0513   1.0000
   8.500   1.3230   0.02974   0.01828  -0.0830   0.0245   1.0000
   8.750   1.3281   0.03121   0.01973  -0.0801   0.0214   1.0000
   9.000   1.3370   0.03244   0.02110  -0.0779   0.0200   1.0000
   9.250   1.3451   0.03376   0.02258  -0.0757   0.0192   1.0000
   9.500   1.3513   0.03529   0.02433  -0.0735   0.0185   1.0000
   9.750   1.3553   0.03707   0.02638  -0.0714   0.0176   1.0000
  10.000   1.3572   0.03914   0.02868  -0.0695   0.0168   1.0000
  10.250   1.3575   0.04148   0.03124  -0.0679   0.0162   1.0000
  10.500   1.3568   0.04404   0.03402  -0.0665   0.0158   1.0000
  10.750   1.3544   0.04691   0.03711  -0.0654   0.0156   1.0000
  11.000   1.3503   0.05012   0.04054  -0.0647   0.0154   1.0000
  11.250   1.3447   0.05367   0.04430  -0.0643   0.0152   1.0000
  11.500   1.3375   0.05756   0.04839  -0.0641   0.0150   1.0000
  11.750   1.3294   0.06173   0.05277  -0.0643   0.0149   1.0000
  12.000   1.3204   0.06618   0.05740  -0.0648   0.0148   1.0000
  12.250   1.3108   0.07082   0.06223  -0.0654   0.0147   1.0000
  12.500   1.3010   0.07558   0.06716  -0.0662   0.0147   1.0000
  12.750   1.2915   0.08042   0.07217  -0.0671   0.0146   1.0000
  13.000   1.2827   0.08525   0.07714  -0.0680   0.0145   1.0000
  13.250   1.2751   0.08987   0.08190  -0.0689   0.0144   1.0000
  13.500   1.2693   0.09414   0.08628  -0.0695   0.0142   1.0000
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