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GOE 144 (MVA H.21) AIRFOIL (goe144-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 144 (MVA H.21) AIRFOIL (goe144-il)
Reynolds number: 100,000
Max Cl/Cd: 60.34 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe144-il-100000-n5.txt
Download as CSV file: xf-goe144-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 144 (MVA H.21) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3418   0.09311   0.08847  -0.0279   1.0000   0.0311
  -7.500  -0.3465   0.09065   0.08610  -0.0268   1.0000   0.0310
  -7.250  -0.3490   0.08789   0.08342  -0.0264   1.0000   0.0309
  -7.000  -0.3499   0.08514   0.08073  -0.0259   1.0000   0.0305
  -6.750  -0.3511   0.08231   0.07796  -0.0259   1.0000   0.0303
  -6.500  -0.3516   0.07921   0.07492  -0.0265   1.0000   0.0301
  -6.250  -0.3501   0.07594   0.07169  -0.0275   1.0000   0.0300
  -6.000  -0.3464   0.07231   0.06808  -0.0291   1.0000   0.0300
  -5.750  -0.3398   0.06839   0.06417  -0.0313   1.0000   0.0299
  -5.500  -0.3090   0.06091   0.05656  -0.0416   0.9958   0.0312
  -5.250  -0.2765   0.05693   0.05248  -0.0477   0.9897   0.0338
  -5.000  -0.2380   0.05092   0.04627  -0.0561   0.9835   0.0349
  -4.750  -0.1958   0.04451   0.03957  -0.0647   0.9774   0.0377
  -4.500  -0.1489   0.02907   0.02281  -0.0772   0.9723   0.0419
  -4.250  -0.1118   0.02777   0.02134  -0.0799   0.9662   0.0459
  -4.000  -0.0770   0.02422   0.01701  -0.0824   0.9590   0.0515
  -3.750  -0.0385   0.02279   0.01527  -0.0849   0.9532   0.0563
  -3.500  -0.0052   0.02128   0.01327  -0.0860   0.9444   0.0622
  -3.250   0.0338   0.01989   0.01159  -0.0883   0.9386   0.0671
  -3.000   0.0674   0.01880   0.01019  -0.0892   0.9293   0.0747
  -2.750   0.1054   0.01795   0.00923  -0.0911   0.9222   0.0850
  -2.500   0.1414   0.01764   0.00886  -0.0926   0.9128   0.0998
  -2.250   0.1763   0.01744   0.00858  -0.0937   0.9022   0.1117
  -2.000   0.2122   0.01718   0.00819  -0.0950   0.8916   0.1217
  -1.750   0.2469   0.01695   0.00785  -0.0961   0.8796   0.1326
  -1.500   0.2780   0.01678   0.00759  -0.0964   0.8639   0.1444
  -1.250   0.3079   0.01639   0.00709  -0.0965   0.8463   0.1515
  -1.000   0.3385   0.01594   0.00658  -0.0967   0.8280   0.1576
  -0.750   0.3690   0.01556   0.00615  -0.0969   0.8078   0.1655
  -0.500   0.4006   0.01520   0.00573  -0.0972   0.7871   0.1745
   0.000   0.4648   0.01474   0.00506  -0.0980   0.7476   0.1984
   0.250   0.4955   0.01464   0.00488  -0.0982   0.7289   0.2114
   0.500   0.5255   0.01461   0.00476  -0.0984   0.7114   0.2246
   0.750   0.5544   0.01463   0.00471  -0.0983   0.6950   0.2389
   1.000   0.5824   0.01468   0.00469  -0.0981   0.6792   0.2546
   1.250   0.6095   0.01473   0.00471  -0.0978   0.6636   0.2736
   1.500   0.6357   0.01475   0.00474  -0.0973   0.6461   0.3002
   1.750   0.6614   0.01460   0.00477  -0.0969   0.6290   0.3610
   2.000   0.6956   0.01355   0.00481  -0.0979   0.6120   1.0000
   2.250   0.7212   0.01378   0.00491  -0.0973   0.5977   1.0000
   2.500   0.7469   0.01401   0.00504  -0.0967   0.5852   1.0000
   2.750   0.7725   0.01425   0.00519  -0.0961   0.5733   1.0000
   3.000   0.7980   0.01450   0.00538  -0.0954   0.5616   1.0000
   3.250   0.8232   0.01474   0.00560  -0.0948   0.5498   1.0000
   3.500   0.8484   0.01500   0.00584  -0.0942   0.5380   1.0000
   3.750   0.8735   0.01527   0.00608  -0.0935   0.5266   1.0000
   4.000   0.8982   0.01554   0.00636  -0.0928   0.5143   1.0000
   4.250   0.9227   0.01582   0.00662  -0.0920   0.5014   1.0000
   4.500   0.9465   0.01609   0.00690  -0.0912   0.4866   1.0000
   4.750   0.9699   0.01637   0.00722  -0.0902   0.4699   1.0000
   5.000   0.9931   0.01665   0.00753  -0.0892   0.4527   1.0000
   5.250   1.0162   0.01695   0.00787  -0.0883   0.4360   1.0000
   5.500   1.0392   0.01726   0.00824  -0.0873   0.4195   1.0000
   5.750   1.0618   0.01760   0.00864  -0.0862   0.4023   1.0000
   6.000   1.0837   0.01796   0.00903  -0.0851   0.3828   1.0000
   6.250   1.1031   0.01836   0.00939  -0.0836   0.3490   1.0000
   6.500   1.1208   0.01893   0.00978  -0.0818   0.3066   1.0000
   6.750   1.1388   0.01960   0.01032  -0.0803   0.2713   1.0000
   7.000   1.1562   0.02039   0.01101  -0.0787   0.2373   1.0000
   7.250   1.1710   0.02144   0.01181  -0.0769   0.1850   1.0000
   7.500   1.1843   0.02269   0.01274  -0.0749   0.1288   1.0000
   7.750   1.1939   0.02435   0.01402  -0.0725   0.0820   1.0000
   8.000   1.1998   0.02633   0.01559  -0.0696   0.0317   1.0000
   8.250   1.2123   0.02760   0.01700  -0.0674   0.0277   1.0000
   8.500   1.2229   0.02898   0.01854  -0.0649   0.0253   1.0000
   8.750   1.2300   0.03056   0.02028  -0.0621   0.0234   1.0000
   9.000   1.2384   0.03180   0.02173  -0.0595   0.0221   1.0000
   9.250   1.2437   0.03320   0.02341  -0.0565   0.0209   1.0000
   9.500   1.2469   0.03478   0.02518  -0.0536   0.0202   1.0000
   9.750   1.2481   0.03654   0.02713  -0.0507   0.0197   1.0000
  10.000   1.2482   0.03846   0.02923  -0.0481   0.0193   1.0000
  10.250   1.2470   0.04062   0.03156  -0.0458   0.0188   1.0000
  10.500   1.2456   0.04295   0.03405  -0.0438   0.0185   1.0000
  10.750   1.2447   0.04541   0.03666  -0.0422   0.0181   1.0000
  11.000   1.2438   0.04805   0.03943  -0.0409   0.0174   1.0000
  11.250   1.2437   0.05078   0.04228  -0.0399   0.0169   1.0000
  11.500   1.2438   0.05365   0.04526  -0.0391   0.0162   1.0000
  11.750   1.2445   0.05665   0.04836  -0.0383   0.0155   1.0000
  12.000   1.2482   0.05959   0.05140  -0.0373   0.0150   1.0000
  12.250   1.2543   0.06249   0.05443  -0.0364   0.0147   1.0000
  12.500   1.2602   0.06572   0.05783  -0.0355   0.0145   1.0000
  12.750   1.2631   0.06927   0.06158  -0.0350   0.0143   1.0000
  13.000   1.2622   0.07324   0.06577  -0.0349   0.0142   1.0000
  13.250   1.2580   0.07756   0.07040  -0.0353   0.0141   1.0000
  13.500   1.2514   0.08207   0.07516  -0.0361   0.0141   1.0000
  13.750   1.2426   0.08694   0.08025  -0.0375   0.0141   1.0000
  14.000   1.2317   0.09223   0.08577  -0.0393   0.0141   1.0000
  14.250   1.2205   0.09764   0.09140  -0.0417   0.0141   1.0000
  14.500   1.2083   0.10344   0.09741  -0.0445   0.0141   1.0000
  14.750   1.1960   0.10952   0.10370  -0.0478   0.0142   1.0000
  15.000   1.1835   0.11593   0.11030  -0.0515   0.0142   1.0000
  15.250   1.1709   0.12270   0.11726  -0.0557   0.0143   1.0000
  15.500   1.1581   0.12993   0.12467  -0.0604   0.0144   1.0000
  15.750   1.1459   0.13753   0.13243  -0.0655   0.0145   1.0000
  16.000   1.1324   0.14602   0.14108  -0.0713   0.0146   1.0000
  16.250   1.1187   0.15530   0.15051  -0.0776   0.0148   1.0000
  16.500   1.1030   0.16617   0.16146  -0.0849   0.0151   1.0000
  16.750   1.0849   0.17941   0.17480  -0.0931   0.0157   1.0000
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