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GOE 370 AIRFOIL (goe370-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 370 AIRFOIL (goe370-il)
Reynolds number: 100,000
Max Cl/Cd: 67.16 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe370-il-100000.txt
Download as CSV file: xf-goe370-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 370 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3079   0.09584   0.09127  -0.0266   1.0000   0.0497
  -7.000  -0.3135   0.09432   0.08984  -0.0251   1.0000   0.0510
  -6.750  -0.3178   0.09277   0.08839  -0.0241   1.0000   0.0522
  -6.500  -0.3238   0.09164   0.08737  -0.0232   1.0000   0.0533
  -6.250  -0.3316   0.09121   0.08702  -0.0229   1.0000   0.0543
  -6.000  -0.3360   0.09094   0.08681  -0.0239   1.0000   0.0548
  -5.750  -0.3329   0.09064   0.08652  -0.0274   1.0000   0.0552
  -5.500  -0.3227   0.08956   0.08540  -0.0316   1.0000   0.0555
  -5.250  -0.3322   0.08394   0.07991  -0.0254   1.0000   0.0563
  -5.000  -0.3350   0.08053   0.07655  -0.0215   1.0000   0.0575
  -4.750  -0.3320   0.07790   0.07395  -0.0204   1.0000   0.0593
  -4.500  -0.3242   0.07545   0.07149  -0.0211   1.0000   0.0617
  -4.250  -0.2401   0.07273   0.06841  -0.0437   0.9930   0.0687
  -4.000  -0.2378   0.06666   0.06243  -0.0400   0.9884   0.0709
  -3.500  -0.1615   0.05886   0.05442  -0.0528   0.9767   0.0853
  -3.250  -0.1015   0.05551   0.05075  -0.0640   0.9712   0.0965
  -3.000  -0.0821   0.05164   0.04693  -0.0643   0.9653   0.1009
  -2.750  -0.0351   0.04823   0.04327  -0.0713   0.9594   0.1117
  -2.500   0.0038   0.04516   0.04003  -0.0757   0.9541   0.1264
  -2.250   0.0421   0.04236   0.03703  -0.0797   0.9472   0.1393
  -2.000   0.0867   0.03940   0.03386  -0.0845   0.9430   0.1539
  -1.750   0.1176   0.03726   0.03155  -0.0864   0.9351   0.1702
  -1.500   0.1611   0.03506   0.02911  -0.0905   0.9302   0.2058
  -1.250   0.1905   0.03316   0.02708  -0.0916   0.9224   0.2267
  -1.000   0.2600   0.02768   0.02010  -0.0973   0.9194   0.1069
  -0.750   0.3062   0.02564   0.01750  -0.1004   0.9157   0.1076
  -0.500   0.3362   0.02434   0.01586  -0.1007   0.9071   0.1069
  -0.250   0.3813   0.02288   0.01404  -0.1035   0.9028   0.1110
   0.000   0.4117   0.02228   0.01334  -0.1039   0.8941   0.1198
   0.250   0.4564   0.02152   0.01253  -0.1070   0.8895   0.1460
   0.500   0.4886   0.02064   0.01174  -0.1077   0.8813   0.1932
   0.750   0.5337   0.01997   0.01125  -0.1109   0.8763   0.2621
   1.000   0.5647   0.01973   0.01120  -0.1115   0.8676   0.3224
   1.250   0.6226   0.01788   0.01058  -0.1173   0.8637   1.0000
   1.500   0.6539   0.01801   0.01050  -0.1177   0.8546   1.0000
   1.750   0.6915   0.01791   0.01028  -0.1190   0.8476   1.0000
   2.000   0.7195   0.01799   0.01029  -0.1186   0.8361   1.0000
   2.250   0.7496   0.01792   0.01020  -0.1183   0.8245   1.0000
   2.500   0.7798   0.01781   0.01007  -0.1180   0.8133   1.0000
   2.750   0.8134   0.01762   0.00986  -0.1182   0.8045   1.0000
   3.000   0.8382   0.01777   0.01004  -0.1172   0.7925   1.0000
   3.250   0.8629   0.01794   0.01032  -0.1161   0.7805   1.0000
   3.500   0.8879   0.01811   0.01056  -0.1152   0.7690   1.0000
   3.750   0.9140   0.01824   0.01077  -0.1144   0.7579   1.0000
   4.000   0.9418   0.01829   0.01090  -0.1137   0.7475   1.0000
   4.250   0.9681   0.01838   0.01112  -0.1128   0.7361   1.0000
   4.500   0.9939   0.01832   0.01124  -0.1115   0.7219   1.0000
   4.750   1.0156   0.01714   0.01006  -0.1076   0.6853   1.0000
   5.000   1.0368   0.01635   0.00930  -0.1042   0.6478   1.0000
   5.250   1.0518   0.01566   0.00847  -0.0996   0.5769   1.0000
   5.500   1.0547   0.01642   0.00827  -0.0933   0.3999   1.0000
   5.750   1.0411   0.02012   0.00977  -0.0870   0.1015   1.0000
   6.000   1.0507   0.02209   0.01145  -0.0839   0.0687   1.0000
   6.250   1.0642   0.02348   0.01300  -0.0814   0.0579   1.0000
   6.500   1.0749   0.02506   0.01471  -0.0784   0.0541   1.0000
   6.750   1.0871   0.02653   0.01630  -0.0756   0.0519   1.0000
   7.000   1.1018   0.02824   0.01805  -0.0732   0.0502   1.0000
   7.250   1.1239   0.03024   0.02003  -0.0718   0.0481   1.0000
   7.500   1.1600   0.03433   0.02389  -0.0731   0.0440   1.0000
   7.750   1.1922   0.03695   0.02668  -0.0730   0.0444   1.0000
   8.000   1.2192   0.03873   0.02893  -0.0715   0.0463   1.0000
   8.250   1.2451   0.04226   0.03310  -0.0696   0.0512   1.0000
   8.500   1.2762   0.04702   0.03806  -0.0692   0.0571   1.0000
  10.000   1.1050   0.07549   0.07134  -0.0409   0.1668   1.0000
  10.250   1.0760   0.08229   0.07821  -0.0413   0.1692   1.0000
  10.500   1.0516   0.08532   0.08125  -0.0407   0.1507   1.0000
  10.750   1.0239   0.09228   0.08824  -0.0427   0.1486   1.0000
  11.000   0.9994   0.09789   0.09386  -0.0445   0.1365   1.0000
  11.250   0.9708   0.10652   0.10249  -0.0489   0.1352   1.0000
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