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GOE 155 (SSW D.1) AIRFOIL (goe155-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 155 (SSW D.1) AIRFOIL (goe155-il)
Reynolds number: 100,000
Max Cl/Cd: 61.57 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe155-il-100000-n5.txt
Download as CSV file: xf-goe155-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 155 (SSW D.1) 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  -0.3070   0.10456   0.09999  -0.0287   1.0000   0.0339
  -8.000  -0.3092   0.10316   0.09869  -0.0312   1.0000   0.0341
  -7.750  -0.3122   0.10171   0.09734  -0.0329   1.0000   0.0342
  -7.500  -0.3003   0.09546   0.09111  -0.0279   1.0000   0.0357
  -7.250  -0.3036   0.09360   0.08932  -0.0265   0.9985   0.0365
  -7.000  -0.2823   0.08957   0.08525  -0.0317   0.9898   0.0383
  -6.750  -0.2585   0.08550   0.08115  -0.0384   0.9812   0.0405
  -6.500  -0.2208   0.08164   0.07721  -0.0538   0.9695   0.0434
  -6.250  -0.1944   0.07670   0.07222  -0.0605   0.9625   0.0441
  -6.000  -0.1833   0.07321   0.06876  -0.0577   0.9562   0.0471
  -5.750  -0.1314   0.06978   0.06506  -0.0754   0.9451   0.0538
  -5.500  -0.1229   0.06534   0.06071  -0.0727   0.9391   0.0551
  -5.250  -0.1038   0.06224   0.05756  -0.0738   0.9315   0.0580
  -5.000  -0.0490   0.05881   0.05371  -0.0880   0.9228   0.0645
  -4.750  -0.0445   0.05512   0.05018  -0.0844   0.9152   0.0666
  -4.500   0.0028   0.05280   0.04739  -0.0931   0.9081   0.0757
  -4.250   0.0207   0.04869   0.04331  -0.0936   0.9006   0.0767
  -4.000   0.0424   0.04565   0.04023  -0.0943   0.8941   0.0784
  -3.750   0.0798   0.02489   0.01945  -0.0922   0.8639   0.0885
  -3.250   0.1441   0.03425   0.02765  -0.1021   0.8740   0.0530
  -3.000   0.1704   0.03186   0.02506  -0.1026   0.8651   0.0516
  -2.750   0.2002   0.02938   0.02214  -0.1031   0.8560   0.0525
  -2.500   0.2290   0.02723   0.01959  -0.1032   0.8481   0.0525
  -2.250   0.2567   0.02543   0.01746  -0.1033   0.8391   0.0516
  -2.000   0.2856   0.02376   0.01542  -0.1032   0.8333   0.0509
  -1.750   0.3137   0.02242   0.01375  -0.1032   0.8254   0.0506
  -1.500   0.3420   0.02123   0.01223  -0.1029   0.8191   0.0506
  -1.250   0.3698   0.02036   0.01107  -0.1027   0.8114   0.0520
  -1.000   0.3977   0.01967   0.01009  -0.1022   0.8047   0.0539
  -0.750   0.4247   0.01892   0.00924  -0.1019   0.7968   0.0544
  -0.500   0.4518   0.01827   0.00849  -0.1014   0.7899   0.0547
  -0.250   0.4786   0.01777   0.00795  -0.1010   0.7816   0.0554
   0.000   0.5055   0.01730   0.00744  -0.1005   0.7743   0.0563
   0.250   0.5320   0.01698   0.00711  -0.1001   0.7654   0.0576
   0.500   0.5586   0.01666   0.00670  -0.0994   0.7578   0.0595
   0.750   0.5854   0.01648   0.00645  -0.0990   0.7469   0.0623
   1.000   0.6123   0.01628   0.00618  -0.0985   0.7352   0.0665
   1.250   0.6389   0.01605   0.00590  -0.0978   0.7217   0.0791
   1.500   0.6655   0.01568   0.00578  -0.0973   0.7066   0.1675
   2.000   0.7193   0.01406   0.00557  -0.0965   0.6775   1.0000
   2.250   0.7456   0.01417   0.00555  -0.0959   0.6640   1.0000
   2.500   0.7719   0.01428   0.00557  -0.0955   0.6496   1.0000
   2.750   0.7980   0.01441   0.00563  -0.0950   0.6339   1.0000
   3.000   0.8240   0.01454   0.00569  -0.0945   0.6168   1.0000
   3.250   0.8497   0.01469   0.00576  -0.0939   0.5983   1.0000
   3.500   0.8754   0.01485   0.00583  -0.0933   0.5792   1.0000
   3.750   0.9008   0.01505   0.00598  -0.0928   0.5587   1.0000
   4.000   0.9261   0.01529   0.00614  -0.0922   0.5386   1.0000
   4.250   0.9511   0.01557   0.00632  -0.0916   0.5192   1.0000
   4.500   0.9760   0.01589   0.00661  -0.0910   0.4996   1.0000
   4.750   1.0005   0.01625   0.00691  -0.0904   0.4807   1.0000
   5.000   1.0249   0.01665   0.00725  -0.0898   0.4627   1.0000
   5.250   1.0490   0.01708   0.00764  -0.0892   0.4457   1.0000
   5.500   1.0731   0.01753   0.00810  -0.0886   0.4297   1.0000
   5.750   1.0971   0.01800   0.00858  -0.0881   0.4146   1.0000
   6.000   1.1205   0.01849   0.00909  -0.0874   0.3975   1.0000
   6.250   1.1433   0.01899   0.00962  -0.0867   0.3777   1.0000
   6.500   1.1659   0.01951   0.01020  -0.0860   0.3596   1.0000
   6.750   1.1886   0.02002   0.01079  -0.0853   0.3438   1.0000
   7.000   1.2094   0.02058   0.01136  -0.0843   0.3203   1.0000
   7.250   1.2290   0.02122   0.01197  -0.0833   0.2951   1.0000
   7.500   1.2462   0.02203   0.01272  -0.0820   0.2586   1.0000
   7.750   1.2604   0.02318   0.01365  -0.0804   0.2103   1.0000
   8.000   1.2590   0.02608   0.01551  -0.0774   0.0711   1.0000
   8.250   1.2672   0.02808   0.01741  -0.0750   0.0484   1.0000
   8.500   1.2777   0.02966   0.01909  -0.0729   0.0406   1.0000
   8.750   1.2845   0.03142   0.02099  -0.0705   0.0362   1.0000
   9.000   1.2900   0.03298   0.02279  -0.0678   0.0338   1.0000
   9.250   1.2920   0.03473   0.02476  -0.0650   0.0315   1.0000
   9.500   1.2914   0.03678   0.02695  -0.0624   0.0295   1.0000
   9.750   1.2854   0.03938   0.02968  -0.0599   0.0279   1.0000
  10.000   1.2835   0.04181   0.03226  -0.0578   0.0267   1.0000
  10.250   1.2845   0.04411   0.03473  -0.0561   0.0259   1.0000
  10.500   1.2860   0.04648   0.03724  -0.0544   0.0250   1.0000
  10.750   1.2895   0.04878   0.03966  -0.0528   0.0241   1.0000
  11.000   1.2950   0.05099   0.04198  -0.0513   0.0228   1.0000
  11.250   1.3009   0.05321   0.04431  -0.0499   0.0214   1.0000
  11.500   1.3067   0.05551   0.04668  -0.0487   0.0201   1.0000
  11.750   1.3158   0.05781   0.04906  -0.0472   0.0193   1.0000
  12.000   1.3315   0.06036   0.05167  -0.0453   0.0185   1.0000
  12.250   1.3450   0.06342   0.05492  -0.0437   0.0180   1.0000
  12.500   1.3481   0.06650   0.05827  -0.0426   0.0178   1.0000
  12.750   1.3463   0.06985   0.06192  -0.0418   0.0175   1.0000
  13.000   1.3412   0.07349   0.06585  -0.0412   0.0171   1.0000
  13.250   1.3338   0.07745   0.07010  -0.0411   0.0168   1.0000
  13.500   1.3244   0.08175   0.07468  -0.0413   0.0164   1.0000
  13.750   1.3135   0.08639   0.07958  -0.0419   0.0162   1.0000
  14.000   1.3010   0.09142   0.08487  -0.0431   0.0160   1.0000
  14.250   1.2873   0.09683   0.09053  -0.0447   0.0158   1.0000
  14.500   1.2726   0.10267   0.09660  -0.0470   0.0157   1.0000
  14.750   1.2574   0.10901   0.10318  -0.0499   0.0157   1.0000
  15.000   1.2418   0.11585   0.11023  -0.0535   0.0157   1.0000
  15.250   1.2257   0.12323   0.11781  -0.0577   0.0158   1.0000
  15.500   1.2095   0.13115   0.12593  -0.0626   0.0159   1.0000
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