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GOE 711 AIRFOIL (goe711-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 711 AIRFOIL (goe711-il)
Reynolds number: 100,000
Max Cl/Cd: 49.15 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe711-il-100000-n5.txt
Download as CSV file: xf-goe711-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 711 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.1292   0.09658   0.09199  -0.0770   0.9472   0.0574
  -7.500  -0.1377   0.09317   0.08861  -0.0845   0.9335   0.0592
  -7.250  -0.1357   0.08891   0.08425  -0.0925   0.9217   0.0597
  -7.000  -0.1192   0.08350   0.07885  -0.0947   0.9179   0.0604
  -6.750  -0.0971   0.07979   0.07516  -0.0942   0.9158   0.0618
  -6.500  -0.0916   0.07710   0.07248  -0.0935   0.9051   0.0631
  -6.250  -0.0678   0.07308   0.06839  -0.0981   0.9012   0.0666
  -6.000  -0.0544   0.06890   0.06367  -0.1077   0.8880   0.0726
  -5.750  -0.0413   0.06458   0.05957  -0.1062   0.8818   0.0742
  -5.500  -0.0221   0.06150   0.05647  -0.1068   0.8750   0.0763
  -5.250   0.0076   0.05775   0.05257  -0.1104   0.8714   0.0796
  -5.000   0.0278   0.05443   0.04871  -0.1138   0.8599   0.0880
  -4.500   0.0815   0.04449   0.03817  -0.1163   0.8457   0.0577
  -4.250   0.1121   0.04106   0.03446  -0.1181   0.8397   0.0554
  -4.000   0.1384   0.03832   0.03137  -0.1186   0.8303   0.0547
  -3.750   0.1685   0.03593   0.02861  -0.1195   0.8220   0.0558
  -3.500   0.2009   0.03348   0.02577  -0.1206   0.8138   0.0551
  -3.250   0.2300   0.03146   0.02338  -0.1209   0.8037   0.0544
  -3.000   0.2670   0.02943   0.02094  -0.1225   0.7963   0.0541
  -2.750   0.2952   0.02810   0.01932  -0.1225   0.7844   0.0548
  -2.500   0.3279   0.02688   0.01777  -0.1232   0.7740   0.0566
  -2.250   0.3635   0.02558   0.01614  -0.1244   0.7643   0.0572
  -2.000   0.3932   0.02458   0.01490  -0.1245   0.7514   0.0574
  -1.750   0.4243   0.02367   0.01377  -0.1249   0.7389   0.0578
  -1.500   0.4560   0.02286   0.01275  -0.1253   0.7261   0.0584
  -1.250   0.4874   0.02224   0.01191  -0.1257   0.7127   0.0595
  -1.000   0.5175   0.02144   0.01106  -0.1261   0.6990   0.0620
  -0.750   0.5453   0.02094   0.01051  -0.1261   0.6841   0.0640
  -0.500   0.5728   0.02052   0.01002  -0.1259   0.6689   0.0654
  -0.250   0.5997   0.02020   0.00959  -0.1256   0.6536   0.0671
   0.000   0.6264   0.01997   0.00924  -0.1253   0.6382   0.0692
   0.250   0.6529   0.01983   0.00894  -0.1250   0.6228   0.0718
   0.500   0.6789   0.01968   0.00868  -0.1247   0.6074   0.0775
   0.750   0.7049   0.01965   0.00851  -0.1243   0.5924   0.0844
   1.000   0.7307   0.01962   0.00837  -0.1240   0.5777   0.0940
   1.250   0.7550   0.01847   0.00845  -0.1241   0.5639   0.5264
   1.750   0.8033   0.01794   0.00839  -0.1217   0.5367   1.0000
   2.250   0.8513   0.01853   0.00859  -0.1205   0.5111   1.0000
   2.500   0.8752   0.01884   0.00873  -0.1199   0.4995   1.0000
   2.750   0.8991   0.01918   0.00887  -0.1194   0.4887   1.0000
   3.000   0.9223   0.01951   0.00909  -0.1187   0.4775   1.0000
   3.250   0.9459   0.01986   0.00931  -0.1181   0.4678   1.0000
   3.500   0.9693   0.02022   0.00954  -0.1176   0.4586   1.0000
   3.750   0.9926   0.02059   0.00983  -0.1170   0.4498   1.0000
   4.000   1.0157   0.02097   0.01009  -0.1164   0.4417   1.0000
   4.250   1.0386   0.02135   0.01041  -0.1158   0.4336   1.0000
   4.500   1.0614   0.02176   0.01073  -0.1152   0.4263   1.0000
   4.750   1.0843   0.02216   0.01108  -0.1146   0.4193   1.0000
   5.000   1.1069   0.02258   0.01145  -0.1140   0.4128   1.0000
   5.250   1.1303   0.02302   0.01180  -0.1135   0.4073   1.0000
   5.500   1.1521   0.02345   0.01226  -0.1128   0.4008   1.0000
   5.750   1.1743   0.02389   0.01266  -0.1122   0.3951   1.0000
   6.000   1.1970   0.02436   0.01308  -0.1116   0.3900   1.0000
   6.250   1.2179   0.02483   0.01360  -0.1108   0.3843   1.0000
   6.500   1.2397   0.02531   0.01406  -0.1102   0.3795   1.0000
   6.750   1.2636   0.02580   0.01449  -0.1099   0.3755   1.0000
   7.000   1.2836   0.02633   0.01512  -0.1090   0.3708   1.0000
   7.250   1.3039   0.02685   0.01569  -0.1081   0.3662   1.0000
   7.500   1.3252   0.02737   0.01619  -0.1074   0.3622   1.0000
   7.750   1.3465   0.02791   0.01676  -0.1068   0.3583   1.0000
   8.000   1.3633   0.02851   0.01747  -0.1053   0.3537   1.0000
   8.250   1.3816   0.02909   0.01811  -0.1042   0.3495   1.0000
   8.500   1.4020   0.02965   0.01866  -0.1034   0.3457   1.0000
   8.750   1.4203   0.03029   0.01938  -0.1023   0.3418   1.0000
   9.000   1.4343   0.03100   0.02023  -0.1006   0.3373   1.0000
   9.250   1.4503   0.03165   0.02095  -0.0992   0.3331   1.0000
   9.500   1.4697   0.03225   0.02155  -0.0983   0.3294   1.0000
   9.750   1.4844   0.03302   0.02247  -0.0968   0.3256   1.0000
  10.000   1.4970   0.03388   0.02349  -0.0951   0.3218   1.0000
  10.250   1.5123   0.03467   0.02440  -0.0937   0.3184   1.0000
  10.500   1.5284   0.03536   0.02513  -0.0925   0.3146   1.0000
  10.750   1.5361   0.03629   0.02619  -0.0902   0.3095   1.0000
  11.000   1.5379   0.03739   0.02746  -0.0871   0.3033   1.0000
  11.250   1.5465   0.03813   0.02815  -0.0850   0.2968   1.0000
  11.500   1.5424   0.03971   0.02998  -0.0816   0.2902   1.0000
  11.750   1.5455   0.04096   0.03131  -0.0793   0.2840   1.0000
  12.000   1.5469   0.04244   0.03292  -0.0769   0.2779   1.0000
  12.250   1.5450   0.04425   0.03491  -0.0745   0.2709   1.0000
  12.500   1.5456   0.04593   0.03664  -0.0725   0.2644   1.0000
  12.750   1.5419   0.04823   0.03917  -0.0705   0.2574   1.0000
  13.000   1.5411   0.05029   0.04129  -0.0689   0.2512   1.0000
  13.250   1.5375   0.05293   0.04415  -0.0674   0.2448   1.0000
  13.500   1.5341   0.05564   0.04700  -0.0662   0.2385   1.0000
  13.750   1.5292   0.05868   0.05019  -0.0651   0.2323   1.0000
  14.000   1.5199   0.06241   0.05410  -0.0643   0.2246   1.0000
  14.250   1.5089   0.06653   0.05836  -0.0638   0.2169   1.0000
  14.500   1.4957   0.07116   0.06315  -0.0636   0.2092   1.0000
  14.750   1.4805   0.07629   0.06844  -0.0637   0.2023   1.0000
  15.000   1.4619   0.08210   0.07440  -0.0642   0.1953   1.0000
  15.250   1.4408   0.08851   0.08098  -0.0650   0.1891   1.0000
  15.500   1.4174   0.09550   0.08815  -0.0662   0.1835   1.0000
  15.750   1.3941   0.10260   0.09541  -0.0676   0.1779   1.0000
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