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GOE 396 AIRFOIL (goe396-il) Xfoil prediction polar at RE=200,000 Ncrit=0


Details Polar file
Airfoil: GOE 396 AIRFOIL (goe396-il)
Reynolds number: 200,000
Max Cl/Cd: 92.37 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe396-il-200000.txt
Download as CSV file: xf-goe396-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 396 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3212   0.12549   0.12188  -0.0296   1.0000   0.0153
 -10.000  -0.3146   0.12162   0.11802  -0.0294   1.0000   0.0157
  -9.750  -0.3092   0.11860   0.11502  -0.0296   1.0000   0.0161
  -9.500  -0.3041   0.11586   0.11232  -0.0299   1.0000   0.0164
  -9.250  -0.2993   0.11312   0.10960  -0.0301   1.0000   0.0169
  -9.000  -0.2949   0.11052   0.10704  -0.0304   1.0000   0.0174
  -8.750  -0.2909   0.10800   0.10456  -0.0305   1.0000   0.0178
  -8.500  -0.2875   0.10554   0.10214  -0.0306   1.0000   0.0185
  -8.250  -0.2848   0.10327   0.09991  -0.0304   1.0000   0.0188
  -8.000  -0.2835   0.10108   0.09779  -0.0300   1.0000   0.0193
  -7.750  -0.2842   0.09909   0.09585  -0.0292   1.0000   0.0198
  -7.500  -0.2884   0.09748   0.09432  -0.0275   1.0000   0.0205
  -7.250  -0.2994   0.09658   0.09352  -0.0243   1.0000   0.0208
  -7.000  -0.3190   0.09663   0.09367  -0.0194   1.0000   0.0207
  -6.750  -0.3357   0.09638   0.09349  -0.0155   0.9996   0.0209
  -6.500  -0.3083   0.09204   0.08914  -0.0230   0.9943   0.0225
  -6.250  -0.2689   0.08836   0.08541  -0.0353   0.9877   0.0243
  -6.000  -0.2274   0.08497   0.08197  -0.0487   0.9803   0.0248
  -5.750  -0.1926   0.08084   0.07779  -0.0573   0.9743   0.0249
  -5.500  -0.1689   0.07455   0.07150  -0.0624   0.9700   0.0254
  -5.250  -0.1544   0.06975   0.06670  -0.0620   0.9665   0.0266
  -5.000  -0.1286   0.06598   0.06291  -0.0662   0.9602   0.0281
  -4.750  -0.0900   0.06172   0.05859  -0.0739   0.9568   0.0302
  -4.500  -0.0553   0.05796   0.05475  -0.0805   0.9496   0.0326
  -4.250   0.0147   0.05407   0.05059  -0.0954   0.9454   0.0350
  -4.000   0.0482   0.04821   0.04468  -0.1009   0.9430   0.0361
  -3.750   0.0711   0.04510   0.04155  -0.1023   0.9364   0.0381
  -3.500   0.1120   0.04161   0.03792  -0.1076   0.9322   0.0417
  -3.250   0.1637   0.03702   0.03306  -0.1153   0.9292   0.0478
  -3.000   0.1883   0.03494   0.03091  -0.1160   0.9214   0.0537
  -2.750   0.2322   0.03108   0.02675  -0.1206   0.9171   0.0618
  -2.500   0.2682   0.02841   0.02370  -0.1227   0.9103   0.0738
  -2.250   0.3057   0.02050   0.01493  -0.1237   0.9047   0.0342
  -2.000   0.3389   0.01734   0.01102  -0.1243   0.8999   0.0362
  -1.750   0.3658   0.01582   0.00922  -0.1238   0.8916   0.0415
  -1.500   0.3976   0.01440   0.00746  -0.1240   0.8863   0.0535
  -1.250   0.4240   0.01372   0.00659  -0.1233   0.8775   0.0703
  -1.000   0.4524   0.01323   0.00595  -0.1231   0.8702   0.0831
  -0.750   0.4798   0.01263   0.00528  -0.1226   0.8622   0.0942
  -0.500   0.5058   0.01223   0.00488  -0.1219   0.8532   0.1201
  -0.250   0.5336   0.01194   0.00458  -0.1216   0.8452   0.1627
   0.000   0.5590   0.01181   0.00444  -0.1208   0.8345   0.1917
   0.250   0.5840   0.01167   0.00430  -0.1200   0.8230   0.2164
   0.500   0.6093   0.01152   0.00419  -0.1192   0.8121   0.2474
   0.750   0.6349   0.01131   0.00404  -0.1185   0.8020   0.2850
   1.000   0.6590   0.01085   0.00393  -0.1177   0.7922   0.4065
   1.250   0.7086   0.00981   0.00374  -0.1224   0.7825   1.0000
   1.500   0.7344   0.00988   0.00371  -0.1218   0.7728   1.0000
   1.750   0.7602   0.00994   0.00366  -0.1211   0.7624   1.0000
   2.000   0.7849   0.01000   0.00367  -0.1203   0.7504   1.0000
   2.250   0.8098   0.01008   0.00374  -0.1196   0.7390   1.0000
   2.500   0.8351   0.01016   0.00379  -0.1189   0.7279   1.0000
   2.750   0.8606   0.01023   0.00383  -0.1183   0.7170   1.0000
   3.000   0.8859   0.01032   0.00390  -0.1176   0.7055   1.0000
   3.250   0.9107   0.01041   0.00404  -0.1168   0.6922   1.0000
   3.500   0.9354   0.01051   0.00417  -0.1161   0.6787   1.0000
   3.750   0.9602   0.01064   0.00434  -0.1153   0.6653   1.0000
   4.000   0.9840   0.01076   0.00445  -0.1143   0.6462   1.0000
   4.250   1.0041   0.01087   0.00447  -0.1122   0.6061   1.0000
   4.500   1.0225   0.01114   0.00457  -0.1100   0.5522   1.0000
   4.750   1.0341   0.01190   0.00478  -0.1066   0.4446   1.0000
   5.000   1.0289   0.01450   0.00582  -0.1013   0.1829   1.0000
   5.250   1.0357   0.01654   0.00704  -0.0981   0.0425   1.0000
   5.500   1.0515   0.01768   0.00817  -0.0958   0.0250   1.0000
   5.750   1.0684   0.01869   0.00939  -0.0937   0.0216   1.0000
   6.000   1.0833   0.01988   0.01079  -0.0912   0.0205   1.0000
   6.250   1.0948   0.02131   0.01237  -0.0883   0.0202   1.0000
   6.500   1.1051   0.02293   0.01405  -0.0853   0.0201   1.0000
   6.750   1.1188   0.02454   0.01570  -0.0828   0.0192   1.0000
   7.000   1.1377   0.02662   0.01780  -0.0811   0.0193   1.0000
   7.250   1.1636   0.02812   0.01933  -0.0802   0.0209   1.0000
  11.500   1.0488   0.09347   0.09042  -0.0380   0.0672   1.0000
  11.750   1.0277   0.10000   0.09703  -0.0399   0.0681   1.0000
  12.000   1.0087   0.10644   0.10352  -0.0420   0.0686   1.0000
  12.250   0.9874   0.11248   0.10962  -0.0443   0.0689   1.0000
  12.500   0.9678   0.11864   0.11583  -0.0472   0.0692   1.0000
  12.750   0.9467   0.12519   0.12244  -0.0511   0.0693   1.0000
  13.000   0.9260   0.13217   0.12945  -0.0558   0.0693   1.0000
  13.250   0.9065   0.13959   0.13689  -0.0612   0.0693   1.0000
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