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GOE 121 (MVA H.1) AIRFOIL (goe121-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 121 (MVA H.1) AIRFOIL (goe121-il)
Reynolds number: 200,000
Max Cl/Cd: 74.94 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe121-il-200000-n5.txt
Download as CSV file: xf-goe121-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3624   0.09898   0.09535  -0.0212   1.0000   0.0284
  -8.250  -0.3590   0.09583   0.09224  -0.0223   1.0000   0.0284
  -8.000  -0.3612   0.09309   0.08956  -0.0244   1.0000   0.0298
  -7.750  -0.3643   0.09110   0.08764  -0.0279   1.0000   0.0306
  -7.250  -0.3578   0.08390   0.08049  -0.0276   1.0000   0.0298
  -7.000  -0.3544   0.08065   0.07729  -0.0289   1.0000   0.0297
  -6.750  -0.3515   0.07740   0.07407  -0.0305   1.0000   0.0298
  -6.500  -0.3451   0.07407   0.07078  -0.0328   0.9990   0.0320
  -6.000  -0.2903   0.06831   0.06495  -0.0413   0.9895   0.0371
  -5.750  -0.2559   0.06243   0.05898  -0.0508   0.9825   0.0356
  -5.500  -0.2192   0.05713   0.05357  -0.0596   0.9757   0.0359
  -5.250  -0.1832   0.05244   0.04874  -0.0672   0.9676   0.0377
  -5.000  -0.1435   0.04697   0.04310  -0.0754   0.9613   0.0373
  -4.750  -0.1039   0.04165   0.03756  -0.0826   0.9543   0.0372
  -4.500  -0.0616   0.03626   0.03189  -0.0897   0.9486   0.0381
  -4.250  -0.0198   0.03019   0.02541  -0.0961   0.9418   0.0386
  -4.000   0.0252   0.02167   0.01595  -0.1029   0.9372   0.0387
  -3.750   0.0613   0.01850   0.01213  -0.1055   0.9295   0.0392
  -3.500   0.0984   0.01675   0.00995  -0.1076   0.9222   0.0398
  -3.250   0.1321   0.01560   0.00850  -0.1088   0.9121   0.0404
  -3.000   0.1651   0.01485   0.00752  -0.1098   0.9011   0.0413
  -2.750   0.1965   0.01409   0.00655  -0.1103   0.8888   0.0421
  -2.500   0.2258   0.01336   0.00566  -0.1104   0.8747   0.0425
  -2.250   0.2538   0.01281   0.00498  -0.1102   0.8600   0.0431
  -2.000   0.2815   0.01237   0.00446  -0.1099   0.8458   0.0440
  -1.750   0.3089   0.01203   0.00405  -0.1096   0.8310   0.0452
  -1.500   0.3363   0.01175   0.00371  -0.1092   0.8154   0.0468
  -1.250   0.3637   0.01152   0.00341  -0.1089   0.7994   0.0491
  -1.000   0.3911   0.01133   0.00314  -0.1085   0.7839   0.0522
  -0.750   0.4184   0.01116   0.00299  -0.1081   0.7686   0.0596
  -0.500   0.4456   0.01113   0.00298  -0.1077   0.7529   0.0792
  -0.250   0.4726   0.01119   0.00293  -0.1072   0.7365   0.0956
   0.000   0.4994   0.01124   0.00290  -0.1067   0.7189   0.1088
   0.250   0.5260   0.01126   0.00285  -0.1063   0.7003   0.1190
   0.500   0.5527   0.01126   0.00280  -0.1059   0.6805   0.1271
   0.750   0.5792   0.01126   0.00275  -0.1054   0.6557   0.1320
   1.000   0.6051   0.01129   0.00271  -0.1049   0.6161   0.1419
   1.250   0.6293   0.01146   0.00266  -0.1040   0.5634   0.1512
   1.500   0.6537   0.01170   0.00269  -0.1032   0.5251   0.1578
   1.750   0.6791   0.01189   0.00279  -0.1026   0.4987   0.1693
   2.000   0.7050   0.01202   0.00294  -0.1022   0.4775   0.2026
   2.250   0.7309   0.01211   0.00310  -0.1019   0.4575   0.2673
   3.250   0.8299   0.01157   0.00366  -0.0990   0.3901   1.0000
   3.500   0.8559   0.01183   0.00384  -0.0986   0.3747   1.0000
   3.750   0.8818   0.01210   0.00404  -0.0982   0.3605   1.0000
   4.000   0.9077   0.01237   0.00428  -0.0978   0.3484   1.0000
   4.250   0.9334   0.01266   0.00453  -0.0974   0.3376   1.0000
   4.500   0.9595   0.01291   0.00479  -0.0970   0.3278   1.0000
   4.750   0.9853   0.01319   0.00507  -0.0966   0.3186   1.0000
   5.000   1.0109   0.01349   0.00538  -0.0962   0.3083   1.0000
   5.250   1.0358   0.01384   0.00570  -0.0957   0.2874   1.0000
   5.500   1.0594   0.01432   0.00602  -0.0950   0.2477   1.0000
   6.000   1.1035   0.01573   0.00698  -0.0935   0.1708   1.0000
   6.250   1.1263   0.01635   0.00754  -0.0927   0.1521   1.0000
   6.500   1.1499   0.01686   0.00806  -0.0921   0.1221   1.0000
   6.750   1.1670   0.01823   0.00904  -0.0907   0.0692   1.0000
   7.000   1.1858   0.01937   0.00999  -0.0894   0.0335   1.0000
   7.250   1.2056   0.02037   0.01104  -0.0881   0.0274   1.0000
   7.500   1.2269   0.02110   0.01190  -0.0871   0.0245   1.0000
   7.750   1.2469   0.02197   0.01290  -0.0859   0.0220   1.0000
   8.000   1.2646   0.02304   0.01411  -0.0844   0.0203   1.0000
   8.250   1.2777   0.02454   0.01576  -0.0824   0.0189   1.0000
   8.500   1.2953   0.02545   0.01681  -0.0809   0.0179   1.0000
   8.750   1.3112   0.02649   0.01797  -0.0793   0.0167   1.0000
   9.000   1.3247   0.02771   0.01930  -0.0773   0.0158   1.0000
   9.250   1.3364   0.02904   0.02074  -0.0752   0.0151   1.0000
   9.500   1.3464   0.03046   0.02224  -0.0729   0.0145   1.0000
   9.750   1.3532   0.03193   0.02380  -0.0702   0.0141   1.0000
  10.000   1.3584   0.03360   0.02555  -0.0674   0.0136   1.0000
  10.250   1.3614   0.03566   0.02772  -0.0646   0.0131   1.0000
  10.500   1.3662   0.03777   0.02993  -0.0622   0.0127   1.0000
  10.750   1.3742   0.03929   0.03162  -0.0602   0.0122   1.0000
  11.000   1.3809   0.04107   0.03357  -0.0583   0.0117   1.0000
  11.250   1.3863   0.04314   0.03579  -0.0565   0.0114   1.0000
  11.500   1.3907   0.04540   0.03822  -0.0547   0.0111   1.0000
  11.750   1.3937   0.04784   0.04084  -0.0531   0.0109   1.0000
  12.000   1.3952   0.05046   0.04365  -0.0516   0.0106   1.0000
  12.250   1.3952   0.05329   0.04667  -0.0504   0.0104   1.0000
  12.500   1.3934   0.05637   0.04994  -0.0494   0.0103   1.0000
  12.750   1.3898   0.05974   0.05352  -0.0487   0.0101   1.0000
  13.000   1.3842   0.06342   0.05740  -0.0484   0.0100   1.0000
  13.250   1.3770   0.06745   0.06167  -0.0485   0.0099   1.0000
  13.500   1.3681   0.07184   0.06627  -0.0490   0.0099   1.0000
  13.750   1.3576   0.07663   0.07127  -0.0500   0.0098   1.0000
  14.000   1.3456   0.08186   0.07671  -0.0516   0.0098   1.0000
  14.250   1.3326   0.08750   0.08254  -0.0537   0.0097   1.0000
  14.500   1.3186   0.09361   0.08885  -0.0564   0.0097   1.0000
  14.750   1.3036   0.10023   0.09568  -0.0597   0.0097   1.0000
  15.000   1.2874   0.10747   0.10312  -0.0635   0.0097   1.0000
  15.250   1.2706   0.11527   0.11111  -0.0680   0.0097   1.0000
  15.500   1.2523   0.12387   0.11991  -0.0732   0.0098   1.0000
  15.750   1.2310   0.13380   0.13005  -0.0795   0.0099   1.0000
  16.000   1.2050   0.14592   0.14236  -0.0875   0.0101   1.0000
  16.250   1.1739   0.16126   0.15791  -0.0977   0.0104   1.0000
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