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GOE 100 (SOPWITH) AIRFOIL (goe100-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 100 (SOPWITH) AIRFOIL (goe100-il)
Reynolds number: 200,000
Max Cl/Cd: 61.67 at α=1.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe100-il-200000-n5.txt
Download as CSV file: xf-goe100-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 100 (SOPWITH) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2853   0.08947   0.08632  -0.0257   1.0000   0.0185
  -8.250  -0.3850   0.10007   0.09672  -0.0235   1.0000   0.0149
  -8.000  -0.3850   0.09658   0.09327  -0.0237   1.0000   0.0152
  -7.750  -0.3815   0.09345   0.09017  -0.0228   1.0000   0.0158
  -7.500  -0.3801   0.09101   0.08777  -0.0218   1.0000   0.0167
  -7.250  -0.3832   0.08877   0.08560  -0.0210   1.0000   0.0173
  -7.000  -0.3842   0.08627   0.08315  -0.0211   1.0000   0.0182
  -6.750  -0.3849   0.08364   0.08058  -0.0215   1.0000   0.0190
  -6.500  -0.3858   0.08104   0.07802  -0.0218   1.0000   0.0200
  -6.250  -0.3869   0.07841   0.07543  -0.0219   1.0000   0.0207
  -6.000  -0.3739   0.07448   0.07149  -0.0259   0.9980   0.0222
  -5.750  -0.3280   0.06805   0.06490  -0.0401   0.9927   0.0246
  -5.250  -0.2804   0.05611   0.05280  -0.0482   0.9851   0.0133
  -5.000  -0.2506   0.05065   0.04719  -0.0535   0.9808   0.0123
  -4.750  -0.2161   0.04497   0.04130  -0.0589   0.9777   0.0115
  -4.500  -0.1840   0.03931   0.03538  -0.0627   0.9726   0.0109
  -4.250  -0.1475   0.03267   0.02833  -0.0665   0.9696   0.0103
  -4.000  -0.1104   0.02466   0.01952  -0.0693   0.9676   0.0097
  -3.750  -0.0807   0.02064   0.01476  -0.0697   0.9631   0.0098
  -3.500  -0.0484   0.01829   0.01187  -0.0705   0.9602   0.0106
  -3.250  -0.0145   0.01681   0.01001  -0.0717   0.9578   0.0127
  -3.000   0.0213   0.01520   0.00804  -0.0730   0.9558   0.0136
  -2.750   0.0527   0.01408   0.00668  -0.0734   0.9499   0.0148
  -2.500   0.0881   0.01307   0.00551  -0.0747   0.9447   0.0216
  -2.250   0.1227   0.01254   0.00497  -0.0758   0.9394   0.0434
  -2.000   0.1539   0.01224   0.00464  -0.0765   0.9325   0.0633
  -1.750   0.1877   0.01189   0.00425  -0.0776   0.9251   0.0823
  -1.500   0.2215   0.01149   0.00381  -0.0786   0.9149   0.0900
  -1.250   0.2518   0.01121   0.00353  -0.0789   0.9034   0.1061
  -1.000   0.2816   0.01099   0.00335  -0.0792   0.8937   0.1425
  -0.750   0.3115   0.01080   0.00316  -0.0794   0.8834   0.1724
  -0.250   0.3676   0.01043   0.00281  -0.0791   0.8554   0.2276
   0.000   0.3940   0.01013   0.00272  -0.0788   0.8386   0.3058
   0.250   0.4171   0.00852   0.00273  -0.0770   0.8221   0.9523
   0.500   0.4528   0.00849   0.00256  -0.0785   0.8027   1.0000
   0.750   0.4786   0.00854   0.00248  -0.0778   0.7793   1.0000
   1.000   0.5043   0.00861   0.00241  -0.0771   0.7503   1.0000
   1.250   0.5295   0.00873   0.00233  -0.0763   0.7089   1.0000
   1.500   0.5532   0.00897   0.00225  -0.0751   0.6481   1.0000
   1.750   0.5753   0.00938   0.00227  -0.0738   0.5799   1.0000
   2.000   0.5976   0.00984   0.00238  -0.0727   0.5230   1.0000
   2.250   0.6207   0.01026   0.00257  -0.0718   0.4758   1.0000
   2.500   0.6443   0.01066   0.00275  -0.0710   0.4324   1.0000
   2.750   0.6680   0.01106   0.00295  -0.0704   0.3913   1.0000
   3.000   0.6920   0.01145   0.00320  -0.0697   0.3568   1.0000
   3.250   0.7162   0.01182   0.00344  -0.0692   0.3273   1.0000
   3.500   0.7384   0.01244   0.00373  -0.0684   0.2714   1.0000
   3.750   0.7624   0.01287   0.00402  -0.0679   0.2385   1.0000
   4.000   0.7854   0.01343   0.00435  -0.0673   0.1936   1.0000
   4.250   0.8056   0.01442   0.00476  -0.0664   0.1151   1.0000
   4.500   0.8243   0.01575   0.00558  -0.0651   0.0192   1.0000
   4.750   0.8490   0.01621   0.00619  -0.0645   0.0155   1.0000
   5.000   0.8733   0.01676   0.00691  -0.0637   0.0138   1.0000
   5.250   0.8958   0.01763   0.00806  -0.0627   0.0115   1.0000
   5.500   0.9184   0.01848   0.00912  -0.0617   0.0103   1.0000
   5.750   0.9410   0.01930   0.01012  -0.0607   0.0099   1.0000
   6.000   0.9622   0.02025   0.01125  -0.0595   0.0095   1.0000
   6.250   0.9814   0.02136   0.01248  -0.0581   0.0093   1.0000
   6.500   0.9998   0.02248   0.01368  -0.0566   0.0085   1.0000
   6.750   1.0162   0.02385   0.01510  -0.0550   0.0074   1.0000
   7.000   1.0314   0.02567   0.01687  -0.0532   0.0069   1.0000
   7.250   1.0502   0.02745   0.01864  -0.0518   0.0069   1.0000
   7.500   1.0717   0.02922   0.02042  -0.0507   0.0069   1.0000
   7.750   1.0943   0.03082   0.02212  -0.0497   0.0070   1.0000
   8.000   1.1154   0.03227   0.02384  -0.0482   0.0075   1.0000
   8.250   1.1366   0.03434   0.02616  -0.0468   0.0083   1.0000
   8.500   1.1571   0.03739   0.02943  -0.0456   0.0094   1.0000
   8.750   1.1839   0.03800   0.03039  -0.0438   0.0151   1.0000
   9.000   1.1994   0.04056   0.03325  -0.0419   0.0154   1.0000
   9.250   1.2109   0.04314   0.03622  -0.0396   0.0151   1.0000
   9.500   1.2184   0.04584   0.03925  -0.0371   0.0146   1.0000
   9.750   1.2219   0.04872   0.04243  -0.0345   0.0139   1.0000
  10.000   1.2229   0.05188   0.04583  -0.0319   0.0132   1.0000
  10.250   1.2285   0.05622   0.05025  -0.0305   0.0122   1.0000
  10.500   1.2303   0.06276   0.05691  -0.0295   0.0114   1.0000
  10.750   1.2180   0.06888   0.06331  -0.0271   0.0111   1.0000
  13.750   0.8234   0.11427   0.11102  -0.0267   0.0165   1.0000
  14.000   0.8044   0.12068   0.11750  -0.0305   0.0169   1.0000
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