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GOE 413 AIRFOIL (goe413-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 413 AIRFOIL (goe413-il)
Reynolds number: 200,000
Max Cl/Cd: 75.29 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe413-il-200000.txt
Download as CSV file: xf-goe413-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 413 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4038   0.04751   0.04298  -0.1123   0.9118   0.0820
  -9.000  -0.3957   0.04401   0.03933  -0.1133   0.9003   0.0803
  -8.750  -0.3931   0.03939   0.03437  -0.1153   0.8898   0.0786
  -8.500  -0.3922   0.03361   0.02781  -0.1177   0.8785   0.0762
  -8.250  -0.3771   0.03076   0.02441  -0.1181   0.8685   0.0756
  -8.000  -0.3561   0.02918   0.02261  -0.1177   0.8588   0.0760
  -7.750  -0.3338   0.02781   0.02103  -0.1174   0.8495   0.0764
  -7.500  -0.3106   0.02647   0.01947  -0.1171   0.8398   0.0768
  -7.250  -0.2865   0.02525   0.01802  -0.1167   0.8313   0.0770
  -7.000  -0.2616   0.02415   0.01674  -0.1165   0.8211   0.0773
  -6.750  -0.2361   0.02319   0.01559  -0.1160   0.8132   0.0777
  -6.500  -0.2100   0.02231   0.01459  -0.1158   0.8026   0.0782
  -6.250  -0.1836   0.02152   0.01364  -0.1154   0.7951   0.0789
  -6.000  -0.1566   0.02085   0.01287  -0.1153   0.7851   0.0799
  -5.750  -0.1293   0.02022   0.01210  -0.1150   0.7773   0.0808
  -5.500  -0.1020   0.01963   0.01142  -0.1148   0.7689   0.0816
  -5.250  -0.0751   0.01881   0.01064  -0.1145   0.7603   0.0826
  -5.000  -0.0478   0.01821   0.01000  -0.1142   0.7539   0.0837
  -4.750  -0.0201   0.01772   0.00956  -0.1143   0.7448   0.0850
  -4.500   0.0079   0.01725   0.00904  -0.1141   0.7379   0.0865
  -4.250   0.0361   0.01687   0.00861  -0.1141   0.7311   0.0883
  -4.000   0.0643   0.01645   0.00819  -0.1141   0.7231   0.0906
  -3.750   0.0929   0.01604   0.00776  -0.1142   0.7170   0.0936
  -3.500   0.1217   0.01577   0.00747  -0.1143   0.7103   0.0971
  -3.250   0.1505   0.01544   0.00717  -0.1144   0.7032   0.1018
  -3.000   0.1797   0.01514   0.00685  -0.1145   0.6975   0.1103
  -2.750   0.2087   0.01485   0.00671  -0.1147   0.6910   0.1354
  -2.500   0.2378   0.01462   0.00664  -0.1149   0.6843   0.1804
  -2.250   0.2671   0.01453   0.00655  -0.1150   0.6787   0.2102
  -2.000   0.2961   0.01454   0.00658  -0.1151   0.6727   0.2317
  -1.750   0.3250   0.01454   0.00659  -0.1152   0.6660   0.2490
  -1.500   0.3542   0.01452   0.00652  -0.1152   0.6603   0.2638
  -1.250   0.3833   0.01458   0.00653  -0.1152   0.6546   0.2800
  -1.000   0.4119   0.01456   0.00659  -0.1153   0.6479   0.2964
  -0.750   0.4409   0.01453   0.00658  -0.1154   0.6422   0.3143
  -0.500   0.4702   0.01459   0.00660  -0.1154   0.6371   0.3355
  -0.250   0.4985   0.01459   0.00671  -0.1155   0.6309   0.3581
   0.000   0.5273   0.01458   0.00676  -0.1156   0.6250   0.3842
   0.250   0.5563   0.01455   0.00679  -0.1156   0.6199   0.4138
   0.500   0.5847   0.01461   0.00693  -0.1156   0.6145   0.4467
   0.750   0.6127   0.01459   0.00710  -0.1156   0.6084   0.4825
   1.000   0.6412   0.01461   0.00722  -0.1155   0.6029   0.5248
   1.250   0.6700   0.01470   0.00733  -0.1154   0.5980   0.5695
   1.500   0.6967   0.01470   0.00754  -0.1151   0.5919   0.6118
   2.000   0.7492   0.01456   0.00775  -0.1138   0.5809   0.7130
   2.250   0.7719   0.01455   0.00793  -0.1122   0.5757   0.7898
   2.500   0.7886   0.01438   0.00803  -0.1092   0.5696   0.8947
   2.750   0.8212   0.01436   0.00796  -0.1099   0.5637   1.0000
   3.000   0.8519   0.01457   0.00800  -0.1103   0.5586   1.0000
   3.250   0.8794   0.01477   0.00822  -0.1104   0.5517   1.0000
   3.500   0.9082   0.01491   0.00831  -0.1105   0.5453   1.0000
   3.750   0.9381   0.01507   0.00833  -0.1107   0.5399   1.0000
   4.000   0.9650   0.01526   0.00854  -0.1106   0.5324   1.0000
   4.250   0.9932   0.01534   0.00856  -0.1105   0.5248   1.0000
   4.500   1.0218   0.01547   0.00858  -0.1105   0.5178   1.0000
   4.750   1.0480   0.01557   0.00871  -0.1102   0.5088   1.0000
   5.000   1.0765   0.01565   0.00866  -0.1101   0.5017   1.0000
   5.250   1.1023   0.01584   0.00890  -0.1098   0.4932   1.0000
   5.500   1.1295   0.01594   0.00895  -0.1095   0.4853   1.0000
   5.750   1.1557   0.01612   0.00910  -0.1092   0.4769   1.0000
   6.000   1.1816   0.01625   0.00923  -0.1088   0.4680   1.0000
   6.250   1.2079   0.01646   0.00938  -0.1085   0.4602   1.0000
   6.500   1.2328   0.01666   0.00961  -0.1080   0.4510   1.0000
   6.750   1.2584   0.01688   0.00976  -0.1076   0.4427   1.0000
   7.000   1.2823   0.01711   0.01003  -0.1070   0.4331   1.0000
   7.250   1.3072   0.01739   0.01025  -0.1065   0.4251   1.0000
   7.500   1.3303   0.01767   0.01058  -0.1058   0.4155   1.0000
   7.750   1.3538   0.01799   0.01084  -0.1052   0.4067   1.0000
   8.000   1.3755   0.01831   0.01118  -0.1043   0.3963   1.0000
   8.250   1.3974   0.01869   0.01155  -0.1034   0.3873   1.0000
   8.500   1.4183   0.01908   0.01194  -0.1025   0.3780   1.0000
   8.750   1.4387   0.01953   0.01238  -0.1014   0.3693   1.0000
   9.000   1.4574   0.01999   0.01284  -0.1002   0.3596   1.0000
   9.250   1.4750   0.02050   0.01337  -0.0988   0.3500   1.0000
   9.500   1.4910   0.02107   0.01390  -0.0972   0.3410   1.0000
   9.750   1.5049   0.02164   0.01454  -0.0954   0.3321   1.0000
  10.000   1.5162   0.02237   0.01521  -0.0933   0.3226   1.0000
  10.250   1.5277   0.02314   0.01606  -0.0914   0.3122   1.0000
  10.500   1.5365   0.02410   0.01701  -0.0894   0.3015   1.0000
  10.750   1.5433   0.02525   0.01815  -0.0874   0.2893   1.0000
  11.000   1.5506   0.02649   0.01944  -0.0857   0.2763   1.0000
  11.250   1.5550   0.02800   0.02096  -0.0840   0.2617   1.0000
  11.500   1.5559   0.02988   0.02281  -0.0822   0.2442   1.0000
  11.750   1.5512   0.03232   0.02518  -0.0803   0.2236   1.0000
  12.000   1.5429   0.03524   0.02801  -0.0786   0.1977   1.0000
  12.250   1.5279   0.03895   0.03158  -0.0769   0.1702   1.0000
  12.500   1.5107   0.04309   0.03559  -0.0755   0.1467   1.0000
  12.750   1.4956   0.04725   0.03965  -0.0745   0.1306   1.0000
  13.000   1.4849   0.05114   0.04352  -0.0738   0.1212   1.0000
  13.250   1.4760   0.05498   0.04736  -0.0733   0.1156   1.0000
  13.500   1.4707   0.05851   0.05092  -0.0729   0.1116   1.0000
  13.750   1.4646   0.06218   0.05462  -0.0726   0.1087   1.0000
  14.000   1.4575   0.06601   0.05847  -0.0724   0.1065   1.0000
  14.250   1.4568   0.06909   0.06161  -0.0721   0.1046   1.0000
  14.500   1.4564   0.07217   0.06474  -0.0720   0.1029   1.0000
  14.750   1.4567   0.07515   0.06778  -0.0718   0.1014   1.0000
  15.000   1.4573   0.07809   0.07075  -0.0716   0.1000   1.0000
  15.250   1.4592   0.08080   0.07347  -0.0713   0.0988   1.0000
  15.500   1.4627   0.08319   0.07583  -0.0709   0.0975   1.0000
  15.750   1.4699   0.08501   0.07761  -0.0702   0.0963   1.0000
  16.000   1.4770   0.08711   0.07978  -0.0699   0.0954   1.0000
  16.250   1.4848   0.08906   0.08179  -0.0696   0.0944   1.0000
  16.500   1.4936   0.09084   0.08362  -0.0692   0.0935   1.0000
  16.750   1.5033   0.09245   0.08527  -0.0687   0.0927   1.0000
  17.000   1.5138   0.09392   0.08678  -0.0681   0.0919   1.0000
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