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GOE 408 AIRFOIL (goe408-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 408 AIRFOIL (goe408-il)
Reynolds number: 50,000
Max Cl/Cd: 40.83 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe408-il-50000-n5.txt
Download as CSV file: xf-goe408-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 408 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3764   0.10243   0.09573  -0.0242   1.0000   0.0835
  -7.500  -0.3868   0.10100   0.09443  -0.0253   1.0000   0.0847
  -7.250  -0.3921   0.09918   0.09269  -0.0281   1.0000   0.0853
  -7.000  -0.3846   0.09413   0.08771  -0.0254   1.0000   0.0869
  -6.750  -0.3788   0.09062   0.08425  -0.0235   1.0000   0.0898
  -6.500  -0.3769   0.08776   0.08145  -0.0234   1.0000   0.0929
  -6.250  -0.3764   0.08536   0.07909  -0.0252   1.0000   0.0969
  -6.000  -0.3751   0.08384   0.07749  -0.0297   1.0000   0.0989
  -5.750  -0.3706   0.07905   0.07286  -0.0261   1.0000   0.1011
  -5.500  -0.3659   0.07613   0.06998  -0.0241   1.0000   0.1071
  -5.250  -0.3599   0.07452   0.06820  -0.0282   1.0000   0.1137
  -5.000  -0.3573   0.07035   0.06419  -0.0237   1.0000   0.1191
  -4.500  -0.3440   0.06496   0.05867  -0.0240   1.0000   0.1303
  -4.250  -0.3379   0.06210   0.05582  -0.0222   1.0000   0.1341
  -3.750  -0.3236   0.05766   0.05115  -0.0210   1.0000   0.1596
  -3.500  -0.2708   0.05084   0.04335  -0.0269   0.9934   0.0860
  -3.250  -0.2396   0.04719   0.03944  -0.0292   0.9855   0.0834
  -3.000  -0.2096   0.04451   0.03653  -0.0313   0.9764   0.0909
  -2.750  -0.1763   0.04146   0.03292  -0.0330   0.9669   0.0887
  -2.500  -0.1435   0.03894   0.02993  -0.0343   0.9573   0.0887
  -2.250  -0.1131   0.03718   0.02780  -0.0353   0.9463   0.0947
  -2.000  -0.0822   0.03525   0.02543  -0.0360   0.9353   0.0946
  -1.750  -0.0499   0.03354   0.02326  -0.0367   0.9246   0.0942
  -1.500  -0.0141   0.03199   0.02129  -0.0380   0.9151   0.0944
  -1.250   0.0219   0.03088   0.01966  -0.0391   0.9048   0.0983
  -1.000   0.0555   0.02963   0.01824  -0.0403   0.8940   0.1016
  -0.750   0.0957   0.02847   0.01678  -0.0424   0.8853   0.1022
  -0.500   0.1341   0.02748   0.01557  -0.0442   0.8754   0.1034
  -0.250   0.1797   0.02661   0.01445  -0.0474   0.8659   0.1052
   0.000   0.2313   0.02572   0.01335  -0.0516   0.8587   0.1094
   0.250   0.2726   0.02509   0.01262  -0.0541   0.8478   0.1167
   0.500   0.3165   0.02441   0.01186  -0.0570   0.8381   0.1223
   0.750   0.3612   0.02382   0.01114  -0.0599   0.8284   0.1281
   1.000   0.4005   0.02333   0.01068  -0.0621   0.8161   0.1368
   1.250   0.4425   0.02288   0.01027  -0.0647   0.8040   0.1579
   1.500   0.5614   0.02039   0.00964  -0.0839   0.7980   1.0000
   1.750   0.5975   0.02042   0.00946  -0.0851   0.7831   1.0000
   2.000   0.6325   0.02051   0.00940  -0.0862   0.7680   1.0000
   2.250   0.6663   0.02064   0.00941  -0.0871   0.7527   1.0000
   2.750   0.7286   0.02105   0.00967  -0.0879   0.7211   1.0000
   3.000   0.7571   0.02132   0.00991  -0.0878   0.7050   1.0000
   3.250   0.7846   0.02162   0.01019  -0.0876   0.6891   1.0000
   3.500   0.8110   0.02195   0.01053  -0.0871   0.6731   1.0000
   3.750   0.8365   0.02229   0.01089  -0.0864   0.6569   1.0000
   4.000   0.8613   0.02264   0.01127  -0.0856   0.6408   1.0000
   4.250   0.8852   0.02298   0.01168  -0.0846   0.6240   1.0000
   4.500   0.9083   0.02327   0.01199  -0.0833   0.6054   1.0000
   4.750   0.9319   0.02350   0.01221  -0.0820   0.5862   1.0000
   5.000   0.9506   0.02383   0.01260  -0.0800   0.5657   1.0000
   5.250   0.9710   0.02415   0.01300  -0.0782   0.5460   1.0000
   5.500   0.9924   0.02449   0.01338  -0.0766   0.5278   1.0000
   5.750   1.0129   0.02486   0.01382  -0.0750   0.5097   1.0000
   6.000   1.0317   0.02530   0.01437  -0.0731   0.4906   1.0000
   6.250   1.0512   0.02576   0.01496  -0.0713   0.4722   1.0000
   6.500   1.0710   0.02623   0.01552  -0.0696   0.4541   1.0000
   7.000   1.1078   0.02736   0.01688  -0.0658   0.4167   1.0000
   7.250   1.1247   0.02800   0.01764  -0.0636   0.3967   1.0000
   7.500   1.1411   0.02863   0.01839  -0.0614   0.3766   1.0000
   7.750   1.1537   0.02936   0.01925  -0.0586   0.3540   1.0000
   8.000   1.1661   0.03006   0.02000  -0.0558   0.3323   1.0000
   8.250   1.1764   0.03087   0.02094  -0.0528   0.3099   1.0000
   8.500   1.1854   0.03168   0.02179  -0.0497   0.2882   1.0000
   8.750   1.1924   0.03263   0.02283  -0.0463   0.2654   1.0000
   9.000   1.1977   0.03367   0.02394  -0.0428   0.2443   1.0000
   9.250   1.1998   0.03480   0.02514  -0.0390   0.2227   1.0000
   9.500   1.1982   0.03612   0.02644  -0.0348   0.2008   1.0000
   9.750   1.1928   0.03773   0.02801  -0.0307   0.1748   1.0000
  10.000   1.1859   0.03971   0.02991  -0.0269   0.1479   1.0000
  10.250   1.1794   0.04201   0.03213  -0.0238   0.1238   1.0000
  10.500   1.1724   0.04463   0.03474  -0.0211   0.1017   1.0000
  10.750   1.1660   0.04746   0.03753  -0.0190   0.0869   1.0000
  11.000   1.1594   0.05054   0.04058  -0.0174   0.0759   1.0000
  11.250   1.1532   0.05379   0.04383  -0.0162   0.0684   1.0000
  11.500   1.1455   0.05732   0.04732  -0.0153   0.0638   1.0000
  11.750   1.1413   0.06074   0.05087  -0.0144   0.0589   1.0000
  12.000   1.1378   0.06416   0.05440  -0.0136   0.0549   1.0000
  12.250   1.1333   0.06771   0.05799  -0.0131   0.0517   1.0000
  12.500   1.1317   0.07116   0.06157  -0.0123   0.0483   1.0000
  12.750   1.1318   0.07454   0.06524  -0.0119   0.0459   1.0000
  13.000   1.1306   0.07819   0.06912  -0.0116   0.0437   1.0000
  13.250   1.1294   0.08189   0.07302  -0.0114   0.0422   1.0000
  13.500   1.1268   0.08579   0.07715  -0.0115   0.0410   1.0000
  13.750   1.1246   0.08964   0.08105  -0.0115   0.0392   1.0000
  14.000   1.1164   0.09469   0.08629  -0.0126   0.0383   1.0000
  14.250   1.1047   0.10037   0.09223  -0.0146   0.0379   1.0000
  14.500   1.0905   0.10676   0.09887  -0.0173   0.0377   1.0000
  14.750   1.0770   0.11332   0.10565  -0.0203   0.0378   1.0000
  15.000   1.0604   0.12086   0.11338  -0.0241   0.0377   1.0000
  15.250   1.0437   0.12898   0.12167  -0.0283   0.0379   1.0000
  15.500   1.0296   0.13689   0.12969  -0.0325   0.0383   1.0000
  15.750   1.0142   0.14571   0.13853  -0.0372   0.0386   1.0000
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