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GOE 412 AIRFOIL (goe412-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 412 AIRFOIL (goe412-il)
Reynolds number: 100,000
Max Cl/Cd: 54.66 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe412-il-100000.txt
Download as CSV file: xf-goe412-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 412 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3052   0.10191   0.09746  -0.0465   0.9741   0.1227
  -7.500  -0.3130   0.09955   0.09513  -0.0509   0.9650   0.1271
  -7.250  -0.3268   0.09490   0.09048  -0.0636   0.9522   0.1299
  -7.000  -0.3024   0.09167   0.08727  -0.0588   0.9498   0.1319
  -6.750  -0.2799   0.08879   0.08435  -0.0593   0.9453   0.1367
  -6.500  -0.2925   0.08421   0.07960  -0.0751   0.9310   0.1455
  -6.250  -0.2668   0.08066   0.07615  -0.0711   0.9290   0.1476
  -6.000  -0.2519   0.07830   0.07379  -0.0700   0.9234   0.1509
  -5.500  -0.2156   0.07036   0.06566  -0.0802   0.9117   0.1650
  -5.250  -0.2158   0.06884   0.06414  -0.0772   0.9024   0.1679
  -5.000  -0.1882   0.06443   0.05952  -0.0844   0.8977   0.1805
  -4.750  -0.1679   0.05074   0.04432  -0.0946   0.8895   0.1139
  -4.500  -0.1387   0.04405   0.03689  -0.0973   0.8856   0.1003
  -4.250  -0.1017   0.04086   0.03342  -0.1000   0.8826   0.0983
  -4.000  -0.0815   0.03890   0.03113  -0.0996   0.8762   0.0974
  -3.750  -0.0520   0.03689   0.02869  -0.1005   0.8711   0.0973
  -3.500  -0.0122   0.03521   0.02644  -0.1027   0.8678   0.0995
  -3.250   0.0156   0.03403   0.02516  -0.1032   0.8627   0.1029
  -3.000   0.0393   0.03342   0.02444  -0.1029   0.8561   0.1062
  -2.750   0.0788   0.03235   0.02309  -0.1047   0.8526   0.1117
  -2.500   0.1229   0.03119   0.02190  -0.1075   0.8503   0.1212
  -2.250   0.1315   0.03136   0.02197  -0.1046   0.8408   0.1309
  -2.000   0.1699   0.03046   0.02110  -0.1064   0.8371   0.1611
  -1.750   0.2127   0.02946   0.02035  -0.1091   0.8347   0.1986
  -1.500   0.2197   0.03003   0.02102  -0.1062   0.8248   0.2179
  -1.250   0.2571   0.02977   0.02084  -0.1079   0.8209   0.2598
  -1.000   0.3006   0.02910   0.02042  -0.1104   0.8185   0.3134
  -0.750   0.3048   0.02966   0.02122  -0.1072   0.8078   0.3559
  -0.500   0.3532   0.02739   0.02092  -0.1094   0.8056   1.0000
  -0.250   0.3994   0.02718   0.02033  -0.1122   0.8029   1.0000
   0.000   0.4009   0.02830   0.02132  -0.1085   0.7916   1.0000
   0.250   0.4433   0.02810   0.02089  -0.1106   0.7879   1.0000
   0.500   0.4833   0.02796   0.02057  -0.1123   0.7841   1.0000
   0.750   0.4909   0.02889   0.02141  -0.1094   0.7731   1.0000
   1.000   0.5386   0.02831   0.02067  -0.1120   0.7705   1.0000
   1.250   0.5425   0.02947   0.02177  -0.1087   0.7586   1.0000
   1.500   0.5871   0.02891   0.02109  -0.1107   0.7553   1.0000
   1.750   0.6343   0.02816   0.02023  -0.1130   0.7532   1.0000
   2.000   0.6360   0.02951   0.02156  -0.1095   0.7404   1.0000
   2.250   0.6808   0.02881   0.02078  -0.1114   0.7378   1.0000
   2.500   0.6858   0.03007   0.02202  -0.1084   0.7258   1.0000
   2.750   0.7288   0.02938   0.02128  -0.1100   0.7226   1.0000
   3.000   0.7689   0.02876   0.02061  -0.1111   0.7184   1.0000
   3.250   0.7845   0.02930   0.02114  -0.1091   0.7075   1.0000
   3.500   0.8362   0.02789   0.01968  -0.1115   0.7048   1.0000
   3.750   0.8459   0.02870   0.02050  -0.1088   0.6925   1.0000
   4.000   0.8951   0.02739   0.01917  -0.1109   0.6892   1.0000
   4.250   0.9077   0.02805   0.01985  -0.1085   0.6775   1.0000
   4.500   0.9541   0.02690   0.01867  -0.1103   0.6734   1.0000
   4.750   0.9692   0.02740   0.01922  -0.1082   0.6623   1.0000
   5.000   1.0139   0.02635   0.01815  -0.1098   0.6574   1.0000
   5.250   1.0312   0.02663   0.01848  -0.1079   0.6459   1.0000
   5.500   1.0798   0.02531   0.01712  -0.1100   0.6403   1.0000
   5.750   1.0960   0.02557   0.01744  -0.1079   0.6279   1.0000
   6.000   1.1230   0.02539   0.01729  -0.1072   0.6180   1.0000
   6.250   1.1594   0.02480   0.01670  -0.1079   0.6094   1.0000
   6.500   1.1781   0.02501   0.01698  -0.1062   0.5973   1.0000
   6.750   1.2057   0.02485   0.01685  -0.1057   0.5867   1.0000
   7.000   1.2407   0.02439   0.01639  -0.1063   0.5766   1.0000
   7.250   1.2592   0.02459   0.01665  -0.1045   0.5631   1.0000
   7.500   1.2805   0.02464   0.01674  -0.1030   0.5493   1.0000
   7.750   1.3028   0.02465   0.01679  -0.1017   0.5349   1.0000
   8.000   1.3244   0.02468   0.01683  -0.1003   0.5196   1.0000
   8.250   1.3446   0.02479   0.01694  -0.0987   0.5036   1.0000
   8.500   1.3635   0.02498   0.01713  -0.0970   0.4870   1.0000
   8.750   1.3812   0.02527   0.01742  -0.0951   0.4700   1.0000
   9.000   1.3980   0.02564   0.01775  -0.0931   0.4526   1.0000
   9.250   1.4141   0.02608   0.01814  -0.0911   0.4350   1.0000
   9.500   1.4287   0.02663   0.01862  -0.0888   0.4170   1.0000
   9.750   1.4370   0.02736   0.01934  -0.0857   0.3996   1.0000
  10.000   1.4477   0.02816   0.02011  -0.0831   0.3831   1.0000
  10.250   1.4607   0.02901   0.02091  -0.0809   0.3677   1.0000
  10.500   1.4743   0.02988   0.02173  -0.0790   0.3532   1.0000
  10.750   1.4852   0.03079   0.02262  -0.0766   0.3395   1.0000
  11.000   1.4895   0.03186   0.02377  -0.0736   0.3267   1.0000
  11.250   1.4943   0.03295   0.02490  -0.0707   0.3143   1.0000
  11.500   1.4989   0.03404   0.02600  -0.0679   0.3022   1.0000
  11.750   1.5056   0.03509   0.02701  -0.0655   0.2906   1.0000
  12.000   1.5053   0.03645   0.02850  -0.0626   0.2799   1.0000
  12.250   1.5062   0.03787   0.03003  -0.0600   0.2693   1.0000
  12.500   1.5072   0.03930   0.03147  -0.0575   0.2586   1.0000
  12.750   1.5045   0.04100   0.03325  -0.0550   0.2477   1.0000
  13.000   1.5003   0.04297   0.03536  -0.0526   0.2369   1.0000
  13.250   1.4981   0.04493   0.03739  -0.0506   0.2265   1.0000
  13.500   1.4965   0.04692   0.03936  -0.0487   0.2160   1.0000
  13.750   1.4894   0.04952   0.04216  -0.0469   0.2051   1.0000
  14.000   1.4825   0.05225   0.04499  -0.0453   0.1935   1.0000
  14.250   1.4736   0.05532   0.04811  -0.0439   0.1811   1.0000
  14.500   1.4622   0.05884   0.05167  -0.0428   0.1676   1.0000
  14.750   1.4475   0.06300   0.05591  -0.0420   0.1524   1.0000
  15.000   1.4295   0.06793   0.06094  -0.0417   0.1342   1.0000
  15.250   1.4094   0.07351   0.06653  -0.0419   0.1140   1.0000
  15.500   1.3885   0.07937   0.07225  -0.0423   0.0988   1.0000
  15.750   1.3691   0.08506   0.07778  -0.0426   0.0889   1.0000
  16.000   1.3544   0.08992   0.08244  -0.0424   0.0811   1.0000
  16.250   1.3475   0.09383   0.08634  -0.0421   0.0739   1.0000
  16.500   1.3467   0.09668   0.08917  -0.0413   0.0681   1.0000
  16.750   1.3469   0.09970   0.09222  -0.0411   0.0636   1.0000
  17.000   1.3556   0.10111   0.09353  -0.0398   0.0598   1.0000
  17.250   1.3582   0.10404   0.09667  -0.0397   0.0572   1.0000
  17.500   1.3639   0.10637   0.09910  -0.0393   0.0548   1.0000
  17.750   1.3792   0.10695   0.09954  -0.0379   0.0522   1.0000
  18.000   1.3825   0.10981   0.10256  -0.0379   0.0507   1.0000
  18.250   1.3789   0.11390   0.10690  -0.0388   0.0495   1.0000
  18.500   1.3760   0.11792   0.11113  -0.0399   0.0483   1.0000
  18.750   1.3727   0.12204   0.11544  -0.0412   0.0472   1.0000
  19.000   1.3692   0.12625   0.11983  -0.0426   0.0465   1.0000
  19.250   1.3647   0.13074   0.12450  -0.0443   0.0459   1.0000
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