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GOE 121 (MVA H.1) AIRFOIL (goe121-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 121 (MVA H.1) AIRFOIL (goe121-il)
Reynolds number: 500,000
Max Cl/Cd: 99.13 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe121-il-500000.txt
Download as CSV file: xf-goe121-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2859   0.09385   0.09165  -0.0266   1.0000   0.0239
  -9.000  -0.2801   0.09106   0.08887  -0.0264   1.0000   0.0243
  -8.750  -0.3782   0.09912   0.09681  -0.0225   1.0000   0.0236
  -8.500  -0.3687   0.09644   0.09413  -0.0219   1.0000   0.0240
  -8.250  -0.3617   0.09399   0.09169  -0.0220   1.0000   0.0243
  -8.000  -0.3565   0.09159   0.08932  -0.0222   1.0000   0.0248
  -7.750  -0.3538   0.08928   0.08703  -0.0222   1.0000   0.0254
  -7.500  -0.3545   0.08712   0.08492  -0.0216   1.0000   0.0260
  -7.250  -0.3538   0.08471   0.08254  -0.0217   1.0000   0.0269
  -6.500  -0.3171   0.07351   0.07137  -0.0393   0.9963   0.0295
  -6.250  -0.2966   0.06664   0.06448  -0.0456   0.9934   0.0305
  -6.000  -0.2705   0.06390   0.06172  -0.0486   0.9898   0.0312
  -5.750  -0.2383   0.06058   0.05836  -0.0541   0.9862   0.0324
  -5.500  -0.1832   0.05514   0.05278  -0.0681   0.9815   0.0374
  -5.250  -0.1423   0.04619   0.04366  -0.0799   0.9753   0.0386
  -5.000  -0.1108   0.04385   0.04129  -0.0831   0.9719   0.0395
  -4.750  -0.0811   0.04176   0.03914  -0.0857   0.9639   0.0407
  -4.500  -0.0436   0.03896   0.03626  -0.0904   0.9585   0.0437
  -4.250   0.0054   0.03137   0.02828  -0.0997   0.9494   0.0493
  -4.000   0.0382   0.02996   0.02682  -0.1019   0.9392   0.0506
  -3.750   0.0875   0.01437   0.00949  -0.1105   0.9320   0.0396
  -3.500   0.1193   0.01290   0.00766  -0.1113   0.9189   0.0393
  -3.250   0.1484   0.01191   0.00642  -0.1114   0.9052   0.0394
  -3.000   0.1762   0.01117   0.00548  -0.1112   0.8921   0.0397
  -2.750   0.2037   0.01056   0.00473  -0.1109   0.8804   0.0400
  -2.500   0.2312   0.01008   0.00413  -0.1106   0.8696   0.0405
  -2.250   0.2585   0.00969   0.00367  -0.1103   0.8576   0.0416
  -2.000   0.2857   0.00935   0.00326  -0.1099   0.8439   0.0427
  -1.750   0.3130   0.00903   0.00286  -0.1095   0.8288   0.0436
  -1.500   0.3400   0.00878   0.00252  -0.1091   0.8113   0.0449
  -1.250   0.3670   0.00859   0.00223  -0.1086   0.7910   0.0462
  -1.000   0.3941   0.00847   0.00200  -0.1082   0.7726   0.0475
  -0.750   0.4214   0.00832   0.00177  -0.1078   0.7560   0.0511
  -0.500   0.4488   0.00823   0.00164  -0.1075   0.7411   0.0584
  -0.250   0.4761   0.00831   0.00179  -0.1071   0.7266   0.0932
   0.000   0.5034   0.00843   0.00186  -0.1068   0.7118   0.1060
   0.250   0.5306   0.00846   0.00184  -0.1065   0.6961   0.1131
   0.500   0.5577   0.00849   0.00183  -0.1062   0.6782   0.1197
   0.750   0.5847   0.00854   0.00181  -0.1059   0.6539   0.1234
   1.000   0.6110   0.00854   0.00173  -0.1054   0.6153   0.1296
   1.250   0.6361   0.00875   0.00171  -0.1048   0.5628   0.1345
   1.750   0.6880   0.00913   0.00185  -0.1040   0.5030   0.1493
   2.000   0.7146   0.00926   0.00194  -0.1037   0.4826   0.1578
   2.250   0.7415   0.00934   0.00206  -0.1035   0.4629   0.1870
   2.500   0.7684   0.00935   0.00223  -0.1033   0.4404   0.2882
   3.000   0.8158   0.00833   0.00251  -0.1017   0.3990   1.0000
   3.250   0.8422   0.00857   0.00263  -0.1014   0.3790   1.0000
   3.500   0.8686   0.00881   0.00277  -0.1010   0.3621   1.0000
   3.750   0.8951   0.00903   0.00294  -0.1007   0.3480   1.0000
   4.000   0.9212   0.00931   0.00311  -0.1004   0.3303   1.0000
   4.250   0.9473   0.00958   0.00329  -0.1001   0.3106   1.0000
   4.500   0.9734   0.00984   0.00348  -0.0997   0.2927   1.0000
   4.750   0.9992   0.01014   0.00370  -0.0994   0.2713   1.0000
   5.000   1.0243   0.01052   0.00392  -0.0989   0.2330   1.0000
   5.250   1.0472   0.01120   0.00429  -0.0982   0.1838   1.0000
   5.500   1.0717   0.01167   0.00467  -0.0977   0.1652   1.0000
   5.750   1.0964   0.01209   0.00503  -0.0972   0.1485   1.0000
   6.000   1.1181   0.01292   0.00552  -0.0963   0.0886   1.0000
   6.250   1.1394   0.01384   0.00625  -0.0953   0.0440   1.0000
   6.500   1.1611   0.01472   0.00702  -0.0942   0.0287   1.0000
   6.750   1.1848   0.01526   0.00765  -0.0935   0.0262   1.0000
   7.000   1.2073   0.01595   0.00841  -0.0925   0.0240   1.0000
   7.250   1.2262   0.01711   0.00968  -0.0911   0.0219   1.0000
   7.500   1.2488   0.01770   0.01033  -0.0902   0.0209   1.0000
   7.750   1.2703   0.01839   0.01109  -0.0891   0.0196   1.0000
   8.000   1.2902   0.01922   0.01199  -0.0879   0.0186   1.0000
   8.250   1.3087   0.02017   0.01299  -0.0865   0.0178   1.0000
   8.500   1.3237   0.02148   0.01436  -0.0846   0.0170   1.0000
   8.750   1.3310   0.02372   0.01669  -0.0816   0.0163   1.0000
   9.000   1.3503   0.02446   0.01752  -0.0803   0.0160   1.0000
   9.250   1.3682   0.02533   0.01848  -0.0788   0.0154   1.0000
   9.500   1.3846   0.02633   0.01957  -0.0772   0.0147   1.0000
   9.750   1.3993   0.02750   0.02081  -0.0753   0.0142   1.0000
  10.000   1.4130   0.02879   0.02218  -0.0734   0.0138   1.0000
  10.250   1.4255   0.03014   0.02360  -0.0714   0.0134   1.0000
  10.500   1.4357   0.03154   0.02508  -0.0691   0.0131   1.0000
  10.750   1.4456   0.03325   0.02685  -0.0668   0.0128   1.0000
  11.000   1.4575   0.03570   0.02938  -0.0651   0.0125   1.0000
  11.250   1.4746   0.03985   0.03370  -0.0644   0.0122   1.0000
  11.500   1.4780   0.04225   0.03633  -0.0615   0.0121   1.0000
  11.750   1.4768   0.04403   0.03830  -0.0581   0.0120   1.0000
  12.000   1.4742   0.04613   0.04062  -0.0551   0.0119   1.0000
  12.250   1.4698   0.04836   0.04305  -0.0523   0.0118   1.0000
  12.500   1.4640   0.05094   0.04585  -0.0500   0.0117   1.0000
  12.750   1.4562   0.05404   0.04918  -0.0481   0.0116   1.0000
  13.000   1.4465   0.05739   0.05274  -0.0467   0.0115   1.0000
  13.250   1.4350   0.06124   0.05681  -0.0459   0.0114   1.0000
  13.500   1.4215   0.06561   0.06139  -0.0458   0.0113   1.0000
  13.750   1.4059   0.07058   0.06657  -0.0463   0.0113   1.0000
  14.000   1.3888   0.07605   0.07224  -0.0475   0.0114   1.0000
  14.250   1.3707   0.08202   0.07839  -0.0494   0.0114   1.0000
  14.500   1.3516   0.08851   0.08507  -0.0521   0.0115   1.0000
  14.750   1.3321   0.09554   0.09226  -0.0554   0.0116   1.0000
  15.000   1.3123   0.10305   0.09994  -0.0594   0.0117   1.0000
  15.250   1.2920   0.11112   0.10815  -0.0638   0.0118   1.0000
  15.750   1.0104   0.12435   0.12201  -0.0546   0.0145   1.0000
  16.000   0.9782   0.13300   0.13079  -0.0599   0.0149   1.0000
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