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GOE 121 (MVA H.1) AIRFOIL (goe121-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 121 (MVA H.1) AIRFOIL (goe121-il)
Reynolds number: 1,000,000
Max Cl/Cd: 104.58 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe121-il-1000000.txt
Download as CSV file: xf-goe121-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3732   0.09088   0.08927  -0.0239   1.0000   0.0182
  -8.000  -0.3765   0.08805   0.08647  -0.0236   1.0000   0.0183
  -7.750  -0.3839   0.08391   0.08237  -0.0235   1.0000   0.0187
  -7.500  -0.3774   0.08214   0.08061  -0.0231   1.0000   0.0189
  -7.250  -0.3723   0.08030   0.07879  -0.0231   0.9999   0.0192
  -7.000  -0.3456   0.07699   0.07547  -0.0288   0.9977   0.0198
  -6.750  -0.3156   0.07282   0.07128  -0.0366   0.9948   0.0215
  -6.500  -0.2729   0.06520   0.06360  -0.0522   0.9883   0.0231
  -6.250  -0.2371   0.05877   0.05710  -0.0625   0.9831   0.0232
  -5.750  -0.1792   0.04988   0.04811  -0.0750   0.9622   0.0249
  -5.500  -0.1419   0.04701   0.04517  -0.0808   0.9487   0.0264
  -5.250  -0.0933   0.04182   0.03978  -0.0898   0.9314   0.0294
  -5.000  -0.0484   0.01910   0.01599  -0.1077   0.9191   0.0284
  -4.750  -0.0203   0.01495   0.01120  -0.1094   0.9054   0.0282
  -4.500   0.0069   0.01339   0.00929  -0.1097   0.8930   0.0283
  -4.250   0.0343   0.01237   0.00803  -0.1097   0.8816   0.0286
  -4.000   0.0616   0.01198   0.00748  -0.1094   0.8689   0.0291
  -3.750   0.0890   0.01183   0.00722  -0.1091   0.8563   0.0295
  -3.500   0.1166   0.01060   0.00573  -0.1092   0.8433   0.0299
  -3.250   0.1440   0.00961   0.00453  -0.1091   0.8280   0.0303
  -3.000   0.1713   0.00902   0.00379  -0.1089   0.8094   0.0306
  -2.750   0.1983   0.00863   0.00324  -0.1085   0.7848   0.0309
  -2.500   0.2252   0.00834   0.00280  -0.1082   0.7614   0.0313
  -2.250   0.2525   0.00811   0.00245  -0.1079   0.7432   0.0317
  -2.000   0.2802   0.00791   0.00216  -0.1078   0.7298   0.0323
  -1.750   0.3080   0.00776   0.00195  -0.1076   0.7182   0.0333
  -1.500   0.3359   0.00762   0.00174  -0.1075   0.7067   0.0343
  -1.250   0.3640   0.00749   0.00157  -0.1073   0.6948   0.0353
  -1.000   0.3919   0.00740   0.00142  -0.1072   0.6820   0.0363
  -0.750   0.4198   0.00734   0.00130  -0.1071   0.6655   0.0372
  -0.500   0.4474   0.00732   0.00120  -0.1068   0.6430   0.0380
  -0.250   0.4741   0.00738   0.00107  -0.1065   0.5932   0.0411
   0.000   0.5000   0.00758   0.00106  -0.1060   0.5382   0.0484
   0.250   0.5268   0.00770   0.00120  -0.1058   0.5099   0.0905
   0.500   0.5539   0.00790   0.00132  -0.1055   0.4862   0.0973
   0.750   0.5811   0.00800   0.00136  -0.1053   0.4644   0.1030
   1.000   0.6084   0.00812   0.00140  -0.1052   0.4426   0.1067
   1.250   0.6355   0.00826   0.00146  -0.1050   0.4189   0.1090
   1.500   0.6625   0.00839   0.00148  -0.1048   0.3923   0.1115
   1.750   0.6895   0.00852   0.00152  -0.1046   0.3679   0.1151
   2.250   0.7434   0.00881   0.00168  -0.1041   0.3309   0.1231
   2.500   0.7708   0.00889   0.00174  -0.1040   0.3195   0.1285
   2.750   0.7980   0.00898   0.00183  -0.1038   0.3079   0.1344
   3.000   0.8253   0.00907   0.00193  -0.1037   0.2965   0.1485
   3.250   0.8526   0.00907   0.00211  -0.1037   0.2840   0.2596
   3.500   0.8793   0.00897   0.00233  -0.1038   0.2553   0.4850
   4.000   0.9236   0.00891   0.00288  -0.1017   0.1687   1.0000
   4.250   0.9499   0.00916   0.00307  -0.1014   0.1589   1.0000
   4.500   0.9768   0.00934   0.00324  -0.1012   0.1527   1.0000
   4.750   1.0030   0.00961   0.00344  -0.1009   0.1421   1.0000
   5.000   1.0290   0.00989   0.00364  -0.1006   0.1222   1.0000
   5.250   1.0526   0.01051   0.00402  -0.0999   0.0821   1.0000
   5.500   1.0784   0.01082   0.00433  -0.0996   0.0747   1.0000
   5.750   1.1037   0.01118   0.00465  -0.0991   0.0588   1.0000
   6.000   1.1263   0.01195   0.00522  -0.0982   0.0254   1.0000
   6.250   1.1510   0.01240   0.00569  -0.0976   0.0213   1.0000
   6.500   1.1761   0.01276   0.00608  -0.0971   0.0196   1.0000
   6.750   1.2005   0.01322   0.00655  -0.0965   0.0177   1.0000
   7.000   1.2239   0.01381   0.00719  -0.0957   0.0161   1.0000
   7.250   1.2484   0.01419   0.00760  -0.0952   0.0153   1.0000
   7.500   1.2724   0.01463   0.00808  -0.0945   0.0144   1.0000
   7.750   1.2959   0.01511   0.00859  -0.0938   0.0136   1.0000
   8.000   1.3175   0.01583   0.00936  -0.0928   0.0127   1.0000
   8.250   1.3364   0.01685   0.01048  -0.0914   0.0121   1.0000
   8.500   1.3596   0.01728   0.01094  -0.0907   0.0117   1.0000
   8.750   1.3818   0.01780   0.01152  -0.0898   0.0111   1.0000
   9.000   1.4030   0.01841   0.01217  -0.0888   0.0106   1.0000
   9.250   1.4236   0.01905   0.01285  -0.0878   0.0102   1.0000
   9.500   1.4433   0.01975   0.01359  -0.0866   0.0098   1.0000
   9.750   1.4593   0.02078   0.01468  -0.0849   0.0094   1.0000
  10.000   1.4633   0.02293   0.01698  -0.0815   0.0089   1.0000
  10.250   1.4814   0.02360   0.01773  -0.0801   0.0088   1.0000
  10.500   1.4972   0.02443   0.01863  -0.0784   0.0086   1.0000
  10.750   1.5103   0.02544   0.01972  -0.0764   0.0084   1.0000
  11.000   1.5199   0.02648   0.02085  -0.0737   0.0082   1.0000
  11.250   1.5270   0.02763   0.02209  -0.0708   0.0080   1.0000
  11.500   1.5340   0.02881   0.02335  -0.0681   0.0078   1.0000
  11.750   1.5412   0.02999   0.02463  -0.0657   0.0076   1.0000
  12.000   1.5482   0.03125   0.02598  -0.0636   0.0074   1.0000
  12.250   1.5555   0.03254   0.02734  -0.0617   0.0072   1.0000
  12.500   1.5617   0.03401   0.02887  -0.0600   0.0071   1.0000
  12.750   1.5654   0.03581   0.03076  -0.0584   0.0069   1.0000
  13.000   1.5664   0.03797   0.03301  -0.0568   0.0068   1.0000
  13.250   1.5631   0.04076   0.03591  -0.0552   0.0067   1.0000
  13.500   1.5524   0.04455   0.03985  -0.0536   0.0065   1.0000
  13.750   1.5323   0.04976   0.04530  -0.0518   0.0064   1.0000
  14.000   1.5302   0.05287   0.04853  -0.0516   0.0063   1.0000
  14.250   1.5267   0.05628   0.05209  -0.0517   0.0063   1.0000
  14.500   1.5207   0.06015   0.05610  -0.0520   0.0063   1.0000
  14.750   1.5127   0.06445   0.06055  -0.0527   0.0062   1.0000
  15.000   1.5039   0.06908   0.06533  -0.0538   0.0062   1.0000
  15.250   1.4929   0.07427   0.07067  -0.0553   0.0062   1.0000
  15.500   1.4811   0.07988   0.07644  -0.0573   0.0061   1.0000
  15.750   1.4679   0.08590   0.08261  -0.0596   0.0061   1.0000
  16.000   1.4533   0.09231   0.08917  -0.0623   0.0061   1.0000
  16.250   1.4374   0.09921   0.09622  -0.0653   0.0061   1.0000
  16.500   1.4201   0.10657   0.10374  -0.0688   0.0061   1.0000
  16.750   1.4034   0.11402   0.11134  -0.0725   0.0061   1.0000
  17.000   1.3844   0.12220   0.11966  -0.0768   0.0061   1.0000
  17.250   1.3667   0.13041   0.12802  -0.0813   0.0061   1.0000
  17.500   1.3465   0.13946   0.13721  -0.0864   0.0061   1.0000
  17.750   1.3270   0.14877   0.14667  -0.0920   0.0061   1.0000
  18.000   1.3047   0.15934   0.15738  -0.0985   0.0062   1.0000
  18.250   1.2819   0.17087   0.16905  -0.1059   0.0062   1.0000
  18.500   1.2456   0.18746   0.18582  -0.1165   0.0063   1.0000
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