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GOE 376 AIRFOIL (goe376-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 376 AIRFOIL (goe376-il)
Reynolds number: 200,000
Max Cl/Cd: 76.2 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe376-il-200000.txt
Download as CSV file: xf-goe376-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 376 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3251   0.10464   0.10113  -0.0234   1.0000   0.0241
  -8.250  -0.3302   0.10330   0.09987  -0.0244   1.0000   0.0242
  -8.000  -0.3334   0.10151   0.09815  -0.0250   1.0000   0.0242
  -7.500  -0.3243   0.09376   0.09048  -0.0235   1.0000   0.0245
  -7.250  -0.3186   0.09005   0.08678  -0.0213   1.0000   0.0248
  -7.000  -0.3158   0.08716   0.08394  -0.0204   1.0000   0.0252
  -6.750  -0.3142   0.08470   0.08153  -0.0201   1.0000   0.0255
  -6.500  -0.3135   0.08234   0.07922  -0.0199   1.0000   0.0260
  -6.250  -0.3137   0.08018   0.07712  -0.0195   1.0000   0.0263
  -6.000  -0.3150   0.07813   0.07511  -0.0189   1.0000   0.0267
  -5.750  -0.3165   0.07612   0.07314  -0.0183   1.0000   0.0272
  -5.500  -0.3140   0.07392   0.07097  -0.0187   0.9996   0.0278
  -5.250  -0.2332   0.06914   0.06585  -0.0407   0.9917   0.0302
  -5.000  -0.2106   0.06302   0.05977  -0.0439   0.9864   0.0307
  -4.750  -0.1844   0.05887   0.05560  -0.0468   0.9810   0.0315
  -4.500  -0.1498   0.05501   0.05166  -0.0520   0.9745   0.0331
  -4.250  -0.1088   0.05117   0.04770  -0.0583   0.9681   0.0353
  -4.000  -0.0525   0.04696   0.04309  -0.0672   0.9608   0.0385
  -3.750  -0.0262   0.04328   0.03945  -0.0696   0.9545   0.0399
  -3.500   0.0090   0.04030   0.03636  -0.0731   0.9476   0.0424
  -3.250   0.0685   0.03967   0.03507  -0.0783   0.9424   0.0480
  -3.000   0.0898   0.03415   0.02976  -0.0807   0.9347   0.0506
  -2.750   0.1302   0.03173   0.02719  -0.0843   0.9304   0.0555
  -2.500   0.1689   0.02955   0.02462  -0.0863   0.9207   0.0619
  -2.250   0.2040   0.02719   0.02225  -0.0890   0.9137   0.0666
  -2.000   0.2405   0.02550   0.02022  -0.0905   0.9030   0.0763
  -1.500   0.3014   0.02244   0.01692  -0.0922   0.8778   0.0961
  -1.250   0.3331   0.02265   0.01667  -0.0921   0.8632   0.1172
  -1.000   0.3568   0.02026   0.01438  -0.0921   0.8483   0.1275
  -0.750   0.3811   0.01904   0.01304  -0.0917   0.8325   0.1516
  -0.500   0.4047   0.01812   0.01205  -0.0910   0.8161   0.1857
   0.500   0.5192   0.01561   0.00813  -0.0861   0.7394   0.1171
   0.750   0.5449   0.01580   0.00871  -0.0854   0.7210   0.1105
   1.000   0.5737   0.01426   0.00628  -0.0836   0.7016   0.0739
   1.250   0.5985   0.01343   0.00541  -0.0826   0.6818   0.0701
   1.500   0.6231   0.01305   0.00491  -0.0815   0.6621   0.0672
   1.750   0.6471   0.01277   0.00456  -0.0803   0.6412   0.0655
   2.000   0.6708   0.01257   0.00431  -0.0792   0.6209   0.0650
   2.250   0.6945   0.01248   0.00415  -0.0781   0.6015   0.0683
   2.500   0.7182   0.01244   0.00403  -0.0771   0.5817   0.0705
   2.750   0.7422   0.01246   0.00394  -0.0761   0.5634   0.0714
   3.000   0.7664   0.01255   0.00391  -0.0751   0.5463   0.0733
   3.250   0.7907   0.01265   0.00392  -0.0742   0.5299   0.0797
   3.500   0.8532   0.01130   0.00415  -0.0823   0.5078   1.0000
   3.750   0.8768   0.01156   0.00427  -0.0813   0.4914   1.0000
   4.000   0.9003   0.01184   0.00442  -0.0803   0.4752   1.0000
   4.250   0.9238   0.01213   0.00463  -0.0794   0.4600   1.0000
   4.500   0.9472   0.01243   0.00485  -0.0785   0.4453   1.0000
   4.750   0.9705   0.01274   0.00509  -0.0775   0.4308   1.0000
   5.000   0.9937   0.01305   0.00535  -0.0766   0.4160   1.0000
   5.250   1.0165   0.01337   0.00565  -0.0756   0.4004   1.0000
   5.500   1.0392   0.01368   0.00594  -0.0746   0.3843   1.0000
   5.750   1.0617   0.01400   0.00624  -0.0736   0.3683   1.0000
   6.000   1.0840   0.01434   0.00656  -0.0725   0.3525   1.0000
   6.250   1.1056   0.01468   0.00687  -0.0714   0.3354   1.0000
   6.500   1.1267   0.01500   0.00715  -0.0702   0.3165   1.0000
   6.750   1.1478   0.01532   0.00747  -0.0690   0.2970   1.0000
   7.000   1.1688   0.01573   0.00785  -0.0678   0.2810   1.0000
   7.250   1.1893   0.01616   0.00827  -0.0666   0.2648   1.0000
   7.500   1.2091   0.01663   0.00870  -0.0653   0.2480   1.0000
   7.750   1.2289   0.01711   0.00917  -0.0640   0.2326   1.0000
   8.000   1.2485   0.01760   0.00965  -0.0628   0.2173   1.0000
   8.250   1.2686   0.01803   0.01013  -0.0615   0.2002   1.0000
   8.500   1.2878   0.01851   0.01064  -0.0602   0.1777   1.0000
   8.750   1.3052   0.01917   0.01120  -0.0587   0.1477   1.0000
   9.000   1.3175   0.02032   0.01207  -0.0564   0.0994   1.0000
   9.250   1.3180   0.02251   0.01375  -0.0527   0.0419   1.0000
   9.500   1.3269   0.02387   0.01511  -0.0500   0.0321   1.0000
   9.750   1.3367   0.02506   0.01642  -0.0473   0.0292   1.0000
  10.000   1.3447   0.02615   0.01767  -0.0443   0.0276   1.0000
  10.250   1.3495   0.02736   0.01903  -0.0411   0.0265   1.0000
  10.500   1.3526   0.02869   0.02051  -0.0379   0.0258   1.0000
  10.750   1.3529   0.03026   0.02221  -0.0346   0.0251   1.0000
  11.000   1.3497   0.03218   0.02426  -0.0316   0.0244   1.0000
  11.250   1.3465   0.03428   0.02647  -0.0290   0.0240   1.0000
  11.500   1.3397   0.03691   0.02920  -0.0267   0.0234   1.0000
  11.750   1.3364   0.03948   0.03187  -0.0249   0.0232   1.0000
  12.000   1.3336   0.04224   0.03471  -0.0234   0.0228   1.0000
  12.250   1.3364   0.04449   0.03713  -0.0224   0.0223   1.0000
  12.500   1.3381   0.04700   0.03976  -0.0214   0.0218   1.0000
  12.750   1.3409   0.04953   0.04241  -0.0204   0.0217   1.0000
  13.000   1.3445   0.05211   0.04512  -0.0193   0.0214   1.0000
  13.250   1.3487   0.05475   0.04790  -0.0182   0.0214   1.0000
  13.500   1.3512   0.05767   0.05099  -0.0174   0.0212   1.0000
  13.750   1.3531   0.06081   0.05431  -0.0167   0.0212   1.0000
  14.000   1.3528   0.06422   0.05793  -0.0162   0.0213   1.0000
  14.250   1.3492   0.06811   0.06204  -0.0162   0.0214   1.0000
  14.500   1.3426   0.07244   0.06660  -0.0165   0.0216   1.0000
  14.750   1.3335   0.07715   0.07153  -0.0173   0.0218   1.0000
  15.000   1.3224   0.08225   0.07684  -0.0186   0.0220   1.0000
  15.250   1.3089   0.08786   0.08266  -0.0204   0.0221   1.0000
  15.500   1.2948   0.09378   0.08878  -0.0227   0.0224   1.0000
  15.750   1.2794   0.10019   0.09537  -0.0254   0.0225   1.0000
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