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GOE 796 AIRFOIL (goe796-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 796 AIRFOIL (goe796-il)
Reynolds number: 100,000
Max Cl/Cd: 55.5 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe796-il-100000.txt
Download as CSV file: xf-goe796-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 796 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4013   0.09849   0.09376  -0.0368   1.0000   0.1263
  -8.000  -0.4419   0.09792   0.09336  -0.0347   1.0000   0.1267
  -7.750  -0.4800   0.09621   0.09174  -0.0357   1.0000   0.1271
  -7.500  -0.4864   0.09252   0.08812  -0.0336   1.0000   0.1278
  -7.250  -0.4783   0.08966   0.08532  -0.0291   1.0000   0.1288
  -7.000  -0.4791   0.08755   0.08326  -0.0257   1.0000   0.1298
  -6.750  -0.4842   0.08555   0.08130  -0.0232   1.0000   0.1310
  -6.500  -0.4909   0.08340   0.07919  -0.0216   1.0000   0.1324
  -6.250  -0.4874   0.08023   0.07602  -0.0230   0.9981   0.1348
  -6.000  -0.4821   0.05304   0.04747  -0.0487   0.9881   0.0838
  -5.750  -0.4518   0.04833   0.04249  -0.0523   0.9835   0.0809
  -5.500  -0.4268   0.04302   0.03671  -0.0550   0.9776   0.0793
  -5.250  -0.3958   0.03795   0.03095  -0.0580   0.9730   0.0792
  -5.000  -0.3632   0.03397   0.02613  -0.0602   0.9685   0.0816
  -4.750  -0.3315   0.03182   0.02367  -0.0617   0.9628   0.0861
  -4.500  -0.2924   0.03045   0.02191  -0.0643   0.9584   0.0978
  -4.250  -0.2636   0.03005   0.02124  -0.0649   0.9515   0.1113
  -4.000  -0.2287   0.02910   0.02029  -0.0670   0.9463   0.1245
  -3.750  -0.1915   0.02872   0.01984  -0.0695   0.9416   0.1394
  -3.500  -0.1656   0.02825   0.01932  -0.0697   0.9342   0.1501
  -3.250  -0.1274   0.02767   0.01857  -0.0721   0.9296   0.1623
  -3.000  -0.0963   0.02720   0.01797  -0.0730   0.9236   0.1713
  -2.750  -0.0648   0.02651   0.01725  -0.0739   0.9175   0.1793
  -2.500  -0.0246   0.02588   0.01655  -0.0764   0.9136   0.1925
  -2.250   0.0015   0.02563   0.01628  -0.0764   0.9066   0.2067
  -2.000   0.0350   0.02522   0.01594  -0.0777   0.9009   0.2236
  -1.750   0.0763   0.02472   0.01556  -0.0804   0.8973   0.2440
  -1.500   0.0964   0.02467   0.01559  -0.0793   0.8889   0.2627
  -1.250   0.1334   0.02426   0.01537  -0.0812   0.8841   0.3002
  -1.000   0.1655   0.02362   0.01522  -0.0822   0.8783   0.3714
  -0.750   0.2284   0.02163   0.01512  -0.0871   0.8745   1.0000
  -0.500   0.2809   0.02129   0.01448  -0.0912   0.8683   1.0000
  -0.250   0.3099   0.02126   0.01426  -0.0911   0.8575   1.0000
   0.000   0.3594   0.02076   0.01358  -0.0944   0.8524   1.0000
   0.250   0.3779   0.02106   0.01378  -0.0927   0.8418   1.0000
   0.500   0.4190   0.02079   0.01338  -0.0947   0.8374   1.0000
   0.750   0.4371   0.02115   0.01366  -0.0930   0.8271   1.0000
   1.000   0.4767   0.02083   0.01326  -0.0945   0.8224   1.0000
   1.250   0.4962   0.02115   0.01352  -0.0930   0.8121   1.0000
   1.500   0.5351   0.02077   0.01307  -0.0943   0.8070   1.0000
   1.750   0.5553   0.02107   0.01333  -0.0928   0.7965   1.0000
   2.000   0.5934   0.02066   0.01288  -0.0939   0.7914   1.0000
   2.250   0.6140   0.02093   0.01313  -0.0925   0.7803   1.0000
   2.500   0.6533   0.02040   0.01256  -0.0935   0.7751   1.0000
   2.750   0.6741   0.02063   0.01278  -0.0920   0.7631   1.0000
   3.000   0.7008   0.02063   0.01278  -0.0913   0.7531   1.0000
   3.250   0.7351   0.02027   0.01239  -0.0916   0.7453   1.0000
   3.500   0.7591   0.02033   0.01247  -0.0904   0.7328   1.0000
   3.750   0.7865   0.02021   0.01235  -0.0896   0.7206   1.0000
   4.000   0.8168   0.01993   0.01204  -0.0891   0.7086   1.0000
   4.250   0.8490   0.01956   0.01162  -0.0888   0.6965   1.0000
   4.500   0.8750   0.01948   0.01153  -0.0878   0.6817   1.0000
   4.750   0.9008   0.01942   0.01148  -0.0868   0.6663   1.0000
   5.000   0.9267   0.01937   0.01141  -0.0858   0.6505   1.0000
   5.250   0.9524   0.01932   0.01134  -0.0848   0.6339   1.0000
   5.500   0.9748   0.01940   0.01144  -0.0834   0.6152   1.0000
   5.750   0.9984   0.01943   0.01149  -0.0822   0.5967   1.0000
   6.000   1.0226   0.01952   0.01157  -0.0811   0.5792   1.0000
   6.250   1.0470   0.01967   0.01171  -0.0801   0.5623   1.0000
   6.500   1.0713   0.01984   0.01185  -0.0791   0.5452   1.0000
   6.750   1.0953   0.02004   0.01204  -0.0781   0.5282   1.0000
   7.000   1.1188   0.02028   0.01224  -0.0771   0.5109   1.0000
   7.250   1.1387   0.02061   0.01259  -0.0755   0.4912   1.0000
   7.500   1.1589   0.02091   0.01288  -0.0739   0.4707   1.0000
   7.750   1.1799   0.02126   0.01312  -0.0725   0.4506   1.0000
   8.000   1.1977   0.02176   0.01363  -0.0707   0.4296   1.0000
   8.250   1.2158   0.02230   0.01412  -0.0689   0.4083   1.0000
   8.500   1.2334   0.02294   0.01468  -0.0672   0.3868   1.0000
   8.750   1.2482   0.02367   0.01540  -0.0650   0.3638   1.0000
   9.000   1.2646   0.02450   0.01609  -0.0631   0.3416   1.0000
   9.250   1.2766   0.02538   0.01700  -0.0607   0.3190   1.0000
   9.500   1.2892   0.02627   0.01784  -0.0583   0.2984   1.0000
   9.750   1.3014   0.02716   0.01865  -0.0560   0.2795   1.0000
  10.000   1.3097   0.02804   0.01961  -0.0530   0.2615   1.0000
  10.250   1.3166   0.02893   0.02052  -0.0499   0.2449   1.0000
  10.500   1.3210   0.02987   0.02146  -0.0465   0.2292   1.0000
  10.750   1.3248   0.03094   0.02250  -0.0433   0.2141   1.0000
  11.000   1.3286   0.03216   0.02367  -0.0404   0.1995   1.0000
  11.250   1.3334   0.03355   0.02500  -0.0378   0.1857   1.0000
  11.500   1.3398   0.03508   0.02650  -0.0356   0.1727   1.0000
  11.750   1.3492   0.03670   0.02806  -0.0338   0.1609   1.0000
  12.000   1.3598   0.03833   0.02956  -0.0322   0.1490   1.0000
  12.250   1.3579   0.04002   0.03151  -0.0295   0.1396   1.0000
  12.500   1.3594   0.04183   0.03339  -0.0273   0.1300   1.0000
  12.750   1.3615   0.04360   0.03506  -0.0255   0.1205   1.0000
  13.000   1.3562   0.04579   0.03754  -0.0233   0.1118   1.0000
  13.250   1.3542   0.04810   0.03991  -0.0216   0.1032   1.0000
  13.500   1.3527   0.05038   0.04210  -0.0201   0.0949   1.0000
  13.750   1.3468   0.05326   0.04522  -0.0187   0.0872   1.0000
  14.000   1.3476   0.05590   0.04780  -0.0174   0.0803   1.0000
  14.250   1.3458   0.05879   0.05086  -0.0163   0.0745   1.0000
  14.500   1.3526   0.06138   0.05339  -0.0150   0.0691   1.0000
  14.750   1.3486   0.06475   0.05705  -0.0141   0.0655   1.0000
  15.000   1.3502   0.06755   0.05991  -0.0133   0.0620   1.0000
  15.250   1.3563   0.07058   0.06294  -0.0123   0.0586   1.0000
  15.500   1.3444   0.07473   0.06743  -0.0120   0.0569   1.0000
  15.750   1.3339   0.07894   0.07191  -0.0121   0.0552   1.0000
  16.000   1.3234   0.08327   0.07645  -0.0124   0.0537   1.0000
  16.250   1.3155   0.08743   0.08079  -0.0129   0.0522   1.0000
  16.500   1.3233   0.09004   0.08331  -0.0124   0.0499   1.0000
  16.750   1.3078   0.09563   0.08912  -0.0135   0.0492   1.0000
  17.000   1.2858   0.10202   0.09580  -0.0158   0.0490   1.0000
  17.250   1.2626   0.10910   0.10315  -0.0190   0.0490   1.0000
  17.500   1.2383   0.11688   0.11118  -0.0229   0.0490   1.0000
  17.750   1.2131   0.12542   0.11994  -0.0277   0.0492   1.0000
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