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GOE 121 (MVA H.1) AIRFOIL (goe121-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 121 (MVA H.1) AIRFOIL (goe121-il)
Reynolds number: 100,000
Max Cl/Cd: 59.93 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe121-il-100000-n5.txt
Download as CSV file: xf-goe121-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 121 (MVA H.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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3455   0.09368   0.08878  -0.0226   1.0000   0.0617
  -7.250  -0.3489   0.09232   0.08753  -0.0270   1.0000   0.0646
  -7.000  -0.3447   0.09004   0.08530  -0.0335   1.0000   0.0651
  -6.750  -0.3366   0.08693   0.08221  -0.0376   1.0000   0.0653
  -6.500  -0.3335   0.08285   0.07821  -0.0342   1.0000   0.0659
  -6.250  -0.3293   0.07982   0.07522  -0.0314   1.0000   0.0667
  -6.000  -0.3247   0.07722   0.07266  -0.0304   1.0000   0.0676
  -5.750  -0.3201   0.07496   0.07043  -0.0295   1.0000   0.0694
  -5.500  -0.3136   0.07277   0.06826  -0.0302   1.0000   0.0732
  -5.250  -0.2711   0.06848   0.06370  -0.0461   0.9971   0.0771
  -5.000  -0.2331   0.05766   0.05260  -0.0556   0.9925   0.0536
  -4.750  -0.2049   0.05408   0.04896  -0.0587   0.9874   0.0529
  -4.250  -0.1173   0.04356   0.03787  -0.0742   0.9762   0.0533
  -4.000  -0.0798   0.03963   0.03371  -0.0789   0.9695   0.0528
  -3.750  -0.0373   0.03527   0.02900  -0.0845   0.9646   0.0524
  -3.500   0.0032   0.03096   0.02425  -0.0891   0.9583   0.0524
  -3.250   0.0471   0.02652   0.01908  -0.0939   0.9535   0.0538
  -3.000   0.0837   0.02522   0.01766  -0.0964   0.9470   0.0558
  -2.750   0.1228   0.02293   0.01491  -0.0992   0.9410   0.0563
  -2.250   0.1985   0.01967   0.01096  -0.1033   0.9274   0.0581
  -2.000   0.2373   0.01847   0.00950  -0.1052   0.9196   0.0600
  -1.750   0.2739   0.01746   0.00830  -0.1066   0.9090   0.0625
  -1.500   0.3080   0.01665   0.00737  -0.1074   0.8970   0.0658
  -1.250   0.3405   0.01627   0.00699  -0.1080   0.8857   0.0705
  -1.000   0.3725   0.01594   0.00663  -0.1085   0.8756   0.0803
  -0.750   0.4026   0.01570   0.00635  -0.1086   0.8641   0.0976
  -0.500   0.4310   0.01539   0.00595  -0.1084   0.8512   0.1158
  -0.250   0.4588   0.01511   0.00570  -0.1081   0.8373   0.1306
   0.000   0.4862   0.01489   0.00556  -0.1078   0.8221   0.1492
   0.250   0.5136   0.01475   0.00546  -0.1073   0.8059   0.1698
   0.500   0.5412   0.01459   0.00530  -0.1068   0.7888   0.1832
   0.750   0.5688   0.01445   0.00512  -0.1063   0.7711   0.1922
   1.000   0.5965   0.01434   0.00499  -0.1058   0.7529   0.2055
   1.250   0.6239   0.01424   0.00491  -0.1053   0.7337   0.2316
   1.500   0.6512   0.01413   0.00485  -0.1048   0.7135   0.2839
   1.750   0.6710   0.01295   0.00490  -0.1029   0.6922   0.7636
   2.000   0.6985   0.01286   0.00480  -0.1022   0.6677   1.0000
   2.250   0.7244   0.01303   0.00484  -0.1015   0.6410   1.0000
   2.500   0.7501   0.01322   0.00489  -0.1007   0.6104   1.0000
   2.750   0.7753   0.01346   0.00491  -0.0998   0.5764   1.0000
   3.000   0.7999   0.01379   0.00497  -0.0988   0.5449   1.0000
   3.250   0.8246   0.01417   0.00514  -0.0980   0.5182   1.0000
   3.500   0.8496   0.01455   0.00538  -0.0973   0.4953   1.0000
   3.750   0.8745   0.01494   0.00565  -0.0967   0.4744   1.0000
   4.000   0.8997   0.01529   0.00597  -0.0961   0.4543   1.0000
   4.250   0.9248   0.01565   0.00628  -0.0955   0.4356   1.0000
   4.500   0.9500   0.01600   0.00662  -0.0949   0.4194   1.0000
   4.750   0.9751   0.01636   0.00698  -0.0944   0.4048   1.0000
   5.000   1.0003   0.01673   0.00739  -0.0938   0.3916   1.0000
   5.250   1.0252   0.01711   0.00780  -0.0932   0.3793   1.0000
   5.500   1.0499   0.01752   0.00824  -0.0926   0.3675   1.0000
   5.750   1.0747   0.01794   0.00872  -0.0920   0.3556   1.0000
   6.000   1.0980   0.01841   0.00922  -0.0912   0.3369   1.0000
   6.250   1.1197   0.01896   0.00969  -0.0902   0.3071   1.0000
   6.500   1.1419   0.01948   0.01021  -0.0893   0.2749   1.0000
   6.750   1.1641   0.02004   0.01075  -0.0885   0.2400   1.0000
   7.000   1.1825   0.02100   0.01143  -0.0872   0.1886   1.0000
   7.250   1.1997   0.02225   0.01243  -0.0858   0.1495   1.0000
   7.500   1.2120   0.02421   0.01388  -0.0840   0.0734   1.0000
   7.750   1.2279   0.02568   0.01528  -0.0824   0.0443   1.0000
   8.000   1.2431   0.02715   0.01671  -0.0807   0.0375   1.0000
   8.250   1.2582   0.02853   0.01825  -0.0788   0.0343   1.0000
   8.500   1.2718   0.02995   0.01989  -0.0769   0.0314   1.0000
   8.750   1.2817   0.03160   0.02170  -0.0747   0.0289   1.0000
   9.000   1.2858   0.03364   0.02387  -0.0719   0.0273   1.0000
   9.250   1.2938   0.03523   0.02563  -0.0694   0.0265   1.0000
   9.500   1.2996   0.03687   0.02744  -0.0666   0.0258   1.0000
   9.750   1.3049   0.03862   0.02933  -0.0639   0.0250   1.0000
  10.000   1.3107   0.04045   0.03131  -0.0615   0.0240   1.0000
  10.250   1.3165   0.04239   0.03338  -0.0593   0.0228   1.0000
  10.500   1.3220   0.04444   0.03556  -0.0573   0.0217   1.0000
  10.750   1.3276   0.04666   0.03793  -0.0555   0.0209   1.0000
  11.000   1.3342   0.04906   0.04044  -0.0537   0.0204   1.0000
  11.250   1.3412   0.05169   0.04319  -0.0521   0.0199   1.0000
  11.500   1.3486   0.05466   0.04630  -0.0506   0.0195   1.0000
  11.750   1.3550   0.05817   0.05000  -0.0491   0.0191   1.0000
  12.000   1.3551   0.06176   0.05381  -0.0477   0.0189   1.0000
  12.250   1.3493   0.06500   0.05735  -0.0465   0.0187   1.0000
  12.500   1.3410   0.06858   0.06122  -0.0458   0.0185   1.0000
  12.750   1.3312   0.07257   0.06549  -0.0456   0.0183   1.0000
  13.000   1.3193   0.07699   0.07019  -0.0461   0.0182   1.0000
  13.250   1.3061   0.08188   0.07534  -0.0472   0.0180   1.0000
  13.500   1.2916   0.08726   0.08098  -0.0489   0.0179   1.0000
  13.750   1.2758   0.09316   0.08713  -0.0514   0.0179   1.0000
  14.000   1.2594   0.09960   0.09379  -0.0545   0.0179   1.0000
  14.250   1.2422   0.10653   0.10093  -0.0583   0.0179   1.0000
  14.500   1.2247   0.11403   0.10863  -0.0628   0.0180   1.0000
  14.750   1.2074   0.12205   0.11683  -0.0678   0.0181   1.0000
  15.000   1.1901   0.13063   0.12557  -0.0733   0.0182   1.0000
  15.250   1.1732   0.13970   0.13478  -0.0793   0.0184   1.0000
  15.500   1.1575   0.14909   0.14427  -0.0854   0.0186   1.0000
  15.750   1.1433   0.15871   0.15398  -0.0916   0.0188   1.0000
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