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GOE 417 AIRFOIL (goe417-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 417 AIRFOIL (goe417-il)
Reynolds number: 100,000
Max Cl/Cd: 63.19 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe417-il-100000-n5.txt
Download as CSV file: xf-goe417-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 417 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2893   0.11356   0.10897  -0.0256   1.0000   0.0263
  -8.000  -0.2981   0.11274   0.10824  -0.0237   1.0000   0.0263
  -7.750  -0.3074   0.11183   0.10743  -0.0217   1.0000   0.0263
  -7.500  -0.3122   0.11045   0.10612  -0.0210   1.0000   0.0264
  -7.250  -0.3147   0.10878   0.10451  -0.0206   1.0000   0.0264
  -7.000  -0.2978   0.10545   0.10118  -0.0255   0.9964   0.0264
  -6.750  -0.2831   0.09944   0.09520  -0.0260   0.9932   0.0267
  -6.500  -0.2692   0.09422   0.08999  -0.0255   0.9901   0.0273
  -6.250  -0.2490   0.09006   0.08580  -0.0289   0.9858   0.0280
  -6.000  -0.2289   0.08641   0.08214  -0.0328   0.9799   0.0291
  -5.750  -0.2050   0.08285   0.07856  -0.0380   0.9744   0.0310
  -5.500  -0.1771   0.07939   0.07506  -0.0447   0.9678   0.0333
  -5.250  -0.1344   0.07665   0.07222  -0.0567   0.9602   0.0349
  -5.000  -0.0895   0.07327   0.06870  -0.0673   0.9543   0.0354
  -4.750  -0.0644   0.06839   0.06380  -0.0713   0.9490   0.0358
  -4.500  -0.0552   0.06415   0.05961  -0.0699   0.9429   0.0370
  -4.250  -0.0286   0.06065   0.05606  -0.0729   0.9388   0.0398
  -4.000   0.0286   0.05846   0.05358  -0.0843   0.9314   0.0470
  -3.750   0.0591   0.05369   0.04875  -0.0886   0.9263   0.0484
  -3.500   0.0847   0.05007   0.04514  -0.0905   0.9231   0.0515
  -3.250   0.1139   0.04761   0.04254  -0.0932   0.9142   0.0574
  -3.000   0.1559   0.04417   0.03896  -0.0987   0.9101   0.0658
  -2.750   0.2028   0.04168   0.03610  -0.1044   0.9020   0.0765
  -2.500   0.2347   0.03840   0.03282  -0.1067   0.8958   0.0819
  -2.250   0.2707   0.03593   0.03014  -0.1093   0.8852   0.0951
  -1.750   0.3609   0.02917   0.02241  -0.1153   0.8684   0.0591
  -1.500   0.3938   0.02712   0.02004  -0.1162   0.8593   0.0593
  -1.250   0.4295   0.02500   0.01762  -0.1177   0.8525   0.0575
  -1.000   0.4595   0.02335   0.01565  -0.1178   0.8419   0.0551
  -0.750   0.4917   0.02184   0.01379  -0.1182   0.8322   0.0535
  -0.500   0.5259   0.02050   0.01210  -0.1188   0.8234   0.0527
  -0.250   0.5544   0.01971   0.01109  -0.1185   0.8108   0.0557
   0.000   0.5836   0.01890   0.01005  -0.1183   0.7979   0.0566
   0.250   0.6128   0.01813   0.00909  -0.1180   0.7841   0.0561
   0.500   0.6416   0.01748   0.00830  -0.1177   0.7694   0.0559
   0.750   0.6703   0.01692   0.00762  -0.1173   0.7533   0.0560
   1.000   0.6984   0.01645   0.00706  -0.1169   0.7361   0.0564
   1.250   0.7254   0.01609   0.00660  -0.1163   0.7170   0.0571
   1.500   0.7535   0.01583   0.00620  -0.1158   0.6960   0.0582
   1.750   0.7818   0.01565   0.00585  -0.1154   0.6746   0.0599
   2.000   0.8089   0.01555   0.00562  -0.1150   0.6521   0.0660
   2.250   0.8359   0.01556   0.00548  -0.1144   0.6301   0.0739
   2.500   0.8618   0.01561   0.00543  -0.1137   0.6072   0.0832
   2.750   0.8905   0.01429   0.00559  -0.1140   0.5846   1.0000
   3.000   0.9150   0.01458   0.00567  -0.1131   0.5617   1.0000
   3.250   0.9392   0.01490   0.00578  -0.1123   0.5397   1.0000
   3.500   0.9630   0.01524   0.00594  -0.1114   0.5172   1.0000
   3.750   0.9861   0.01561   0.00612  -0.1104   0.4936   1.0000
   4.000   1.0085   0.01601   0.00635  -0.1093   0.4688   1.0000
   4.250   1.0308   0.01642   0.00660  -0.1082   0.4450   1.0000
   4.500   1.0532   0.01686   0.00688  -0.1072   0.4250   1.0000
   4.750   1.0759   0.01729   0.00721  -0.1063   0.4088   1.0000
   5.000   1.0989   0.01771   0.00760  -0.1054   0.3948   1.0000
   5.250   1.1220   0.01814   0.00800  -0.1046   0.3822   1.0000
   5.500   1.1450   0.01858   0.00843  -0.1038   0.3704   1.0000
   5.750   1.1678   0.01904   0.00890  -0.1030   0.3594   1.0000
   6.000   1.1903   0.01952   0.00938  -0.1021   0.3493   1.0000
   6.250   1.2131   0.01997   0.00991  -0.1013   0.3389   1.0000
   6.500   1.2355   0.02046   0.01045  -0.1005   0.3293   1.0000
   6.750   1.2573   0.02099   0.01104  -0.0995   0.3197   1.0000
   7.000   1.2794   0.02148   0.01166  -0.0986   0.3095   1.0000
   7.250   1.3009   0.02203   0.01229  -0.0977   0.3000   1.0000
   7.500   1.3220   0.02259   0.01295  -0.0966   0.2903   1.0000
   7.750   1.3428   0.02314   0.01369  -0.0956   0.2795   1.0000
   8.000   1.3610   0.02367   0.01432  -0.0941   0.2642   1.0000
   8.250   1.3770   0.02422   0.01490  -0.0924   0.2455   1.0000
   8.500   1.3936   0.02480   0.01557  -0.0908   0.2265   1.0000
   8.750   1.4084   0.02548   0.01628  -0.0889   0.2050   1.0000
   9.000   1.4200   0.02640   0.01710  -0.0868   0.1774   1.0000
   9.250   1.4302   0.02753   0.01819  -0.0845   0.1505   1.0000
   9.500   1.4349   0.02907   0.01953  -0.0816   0.1079   1.0000
  10.000   1.4240   0.03394   0.02388  -0.0738   0.0327   1.0000
  10.250   1.4238   0.03598   0.02602  -0.0708   0.0278   1.0000
  10.500   1.4248   0.03794   0.02815  -0.0681   0.0252   1.0000
  10.750   1.4244   0.04006   0.03047  -0.0656   0.0230   1.0000
  11.000   1.4208   0.04255   0.03314  -0.0633   0.0213   1.0000
  11.250   1.4146   0.04541   0.03620  -0.0613   0.0204   1.0000
  11.500   1.4057   0.04870   0.03971  -0.0597   0.0198   1.0000
  11.750   1.3943   0.05252   0.04375  -0.0586   0.0193   1.0000
  12.000   1.3852   0.05638   0.04780  -0.0581   0.0190   1.0000
  12.250   1.3757   0.06059   0.05228  -0.0582   0.0188   1.0000
  12.500   1.3653   0.06521   0.05711  -0.0588   0.0186   1.0000
  12.750   1.3550   0.07011   0.06221  -0.0598   0.0184   1.0000
  13.000   1.3449   0.07521   0.06749  -0.0611   0.0181   1.0000
  13.250   1.3357   0.08032   0.07279  -0.0625   0.0178   1.0000
  13.500   1.3278   0.08535   0.07799  -0.0639   0.0174   1.0000
  13.750   1.3213   0.09019   0.08298  -0.0652   0.0170   1.0000
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