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GOE 290 (MVA 290) AIRFOIL (goe290-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 290 (MVA 290) AIRFOIL (goe290-il)
Reynolds number: 100,000
Max Cl/Cd: 41.75 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe290-il-100000.txt
Download as CSV file: xf-goe290-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 290 (MVA 290) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2855   0.09767   0.09294  -0.0363   1.0000   0.1994
  -8.750  -0.5646   0.06146   0.05637  -0.0601   0.9851   0.1196
  -8.500  -0.5415   0.05470   0.04930  -0.0660   0.9738   0.1147
  -8.250  -0.5262   0.04749   0.04146  -0.0713   0.9601   0.1119
  -8.000  -0.4966   0.04272   0.03614  -0.0756   0.9477   0.1122
  -7.750  -0.4602   0.03878   0.03168  -0.0796   0.9371   0.1130
  -7.500  -0.4265   0.03572   0.02815  -0.0819   0.9222   0.1140
  -7.250  -0.3946   0.03338   0.02535  -0.0832   0.9053   0.1161
  -7.000  -0.3643   0.03147   0.02296  -0.0838   0.8879   0.1187
  -6.750  -0.3333   0.02954   0.02099  -0.0844   0.8704   0.1218
  -6.500  -0.3041   0.02818   0.01946  -0.0843   0.8524   0.1249
  -6.250  -0.2769   0.02710   0.01810  -0.0837   0.8343   0.1291
  -6.000  -0.2509   0.02599   0.01676  -0.0830   0.8167   0.1333
  -5.750  -0.2248   0.02506   0.01583  -0.0825   0.8002   0.1380
  -5.500  -0.1988   0.02441   0.01499  -0.0820   0.7858   0.1439
  -5.250  -0.1724   0.02354   0.01408  -0.0815   0.7740   0.1503
  -5.000  -0.1466   0.02292   0.01343  -0.0810   0.7616   0.1581
  -4.750  -0.1214   0.02223   0.01277  -0.0805   0.7508   0.1670
  -4.500  -0.0957   0.02165   0.01216  -0.0799   0.7412   0.1788
  -4.250  -0.0711   0.02108   0.01171  -0.0794   0.7323   0.1949
  -4.000  -0.0470   0.02048   0.01137  -0.0789   0.7241   0.2217
  -3.750  -0.0230   0.02002   0.01136  -0.0781   0.7176   0.3039
  -3.500   0.0002   0.02025   0.01175  -0.0772   0.7091   0.3854
  -3.250   0.0257   0.02040   0.01185  -0.0764   0.7026   0.4244
  -3.000   0.0516   0.02058   0.01195  -0.0759   0.6962   0.4525
  -2.750   0.0772   0.02068   0.01210  -0.0755   0.6896   0.4749
  -2.500   0.1041   0.02071   0.01210  -0.0751   0.6843   0.4955
  -2.250   0.1311   0.02078   0.01213  -0.0747   0.6794   0.5151
  -2.000   0.1564   0.02091   0.01235  -0.0744   0.6729   0.5350
  -1.750   0.1824   0.02095   0.01245  -0.0739   0.6675   0.5580
  -1.500   0.2091   0.02098   0.01250  -0.0734   0.6633   0.5825
  -1.250   0.2340   0.02116   0.01279  -0.0729   0.6587   0.6078
  -1.000   0.2587   0.02134   0.01308  -0.0725   0.6533   0.6346
  -0.750   0.2844   0.02135   0.01322  -0.0718   0.6486   0.6610
  -0.500   0.3117   0.02131   0.01324  -0.0714   0.6446   0.6917
  -0.250   0.3355   0.02148   0.01361  -0.0705   0.6402   0.7308
   0.000   0.3569   0.02170   0.01415  -0.0690   0.6353   0.7910
   0.250   0.3887   0.02183   0.01448  -0.0686   0.6303   0.8823
   0.500   0.4585   0.02189   0.01435  -0.0755   0.6248   0.9627
   0.750   0.5373   0.02232   0.01468  -0.0863   0.6159   1.0000
   1.000   0.5537   0.02251   0.01472  -0.0850   0.6105   1.0000
   1.250   0.5766   0.02259   0.01458  -0.0840   0.6057   1.0000
   1.500   0.5914   0.02319   0.01519  -0.0825   0.5986   1.0000
   1.750   0.6127   0.02343   0.01532  -0.0814   0.5921   1.0000
   2.000   0.6392   0.02347   0.01516  -0.0808   0.5869   1.0000
   2.250   0.6554   0.02413   0.01585  -0.0793   0.5800   1.0000
   2.500   0.6768   0.02455   0.01622  -0.0784   0.5741   1.0000
   2.750   0.7027   0.02477   0.01633  -0.0779   0.5696   1.0000
   3.000   0.7265   0.02525   0.01674  -0.0773   0.5650   1.0000
   3.250   0.7420   0.02611   0.01769  -0.0759   0.5581   1.0000
   3.500   0.7673   0.02641   0.01793  -0.0754   0.5528   1.0000
   3.750   0.7971   0.02652   0.01791  -0.0753   0.5486   1.0000
   4.000   0.8106   0.02757   0.01908  -0.0737   0.5412   1.0000
   4.250   0.8344   0.02796   0.01946  -0.0731   0.5349   1.0000
   4.500   0.8654   0.02794   0.01932  -0.0732   0.5302   1.0000
   4.750   0.8799   0.02892   0.02041  -0.0716   0.5223   1.0000
   5.000   0.9046   0.02919   0.02066  -0.0710   0.5153   1.0000
   5.250   0.9386   0.02897   0.02031  -0.0714   0.5105   1.0000
   5.500   0.9489   0.03007   0.02157  -0.0693   0.5008   1.0000
   5.750   0.9788   0.02996   0.02140  -0.0692   0.4944   1.0000
   6.000   1.0045   0.03023   0.02164  -0.0687   0.4877   1.0000
   6.250   1.0215   0.03082   0.02232  -0.0673   0.4784   1.0000
   6.500   1.0578   0.03041   0.02177  -0.0679   0.4732   1.0000
   6.750   1.0664   0.03146   0.02300  -0.0655   0.4623   1.0000
   7.000   1.1006   0.03104   0.02248  -0.0659   0.4562   1.0000
   7.250   1.1130   0.03189   0.02345  -0.0639   0.4464   1.0000
   7.500   1.1436   0.03160   0.02310  -0.0639   0.4395   1.0000
   7.750   1.1611   0.03214   0.02369  -0.0625   0.4311   1.0000
   8.000   1.1859   0.03208   0.02364  -0.0618   0.4232   1.0000
   8.250   1.2127   0.03195   0.02346  -0.0614   0.4162   1.0000
   8.500   1.2279   0.03237   0.02395  -0.0596   0.4074   1.0000
   8.750   1.2655   0.03152   0.02296  -0.0604   0.4014   1.0000
   9.000   1.2679   0.03269   0.02433  -0.0573   0.3924   1.0000
   9.250   1.3056   0.03186   0.02334  -0.0580   0.3866   1.0000
   9.500   1.3067   0.03318   0.02487  -0.0549   0.3788   1.0000
   9.750   1.3332   0.03295   0.02459  -0.0544   0.3724   1.0000
  10.000   1.3490   0.03340   0.02508  -0.0529   0.3659   1.0000
  10.250   1.3575   0.03414   0.02592  -0.0505   0.3591   1.0000
  10.500   1.3965   0.03345   0.02507  -0.0516   0.3536   1.0000
  10.750   1.3839   0.03529   0.02717  -0.0469   0.3479   1.0000
  11.000   1.3937   0.03604   0.02798  -0.0448   0.3425   1.0000
  11.250   1.4275   0.03558   0.02742  -0.0452   0.3366   1.0000
  11.500   1.4103   0.03780   0.02988  -0.0407   0.3316   1.0000
  11.750   1.4238   0.03834   0.03044  -0.0393   0.3256   1.0000
  12.000   1.4462   0.03851   0.03058  -0.0386   0.3201   1.0000
  12.250   1.4277   0.04127   0.03357  -0.0352   0.3152   1.0000
  12.500   1.4445   0.04172   0.03404  -0.0343   0.3093   1.0000
  12.750   1.4560   0.04260   0.03494  -0.0331   0.3037   1.0000
  13.000   1.4354   0.04614   0.03870  -0.0309   0.2990   1.0000
  13.250   1.4614   0.04579   0.03830  -0.0304   0.2924   1.0000
  13.500   1.4563   0.04827   0.04090  -0.0291   0.2874   1.0000
  13.750   1.4313   0.05286   0.04571  -0.0280   0.2828   1.0000
  14.000   1.4789   0.05019   0.04285  -0.0274   0.2745   1.0000
  14.250   1.4415   0.05625   0.04921  -0.0267   0.2708   1.0000
  14.500   1.4142   0.06176   0.05492  -0.0266   0.2659   1.0000
  14.750   1.4546   0.05934   0.05237  -0.0256   0.2577   1.0000
  15.000   1.4067   0.06762   0.06094  -0.0264   0.2539   1.0000
  15.250   1.4525   0.06414   0.05728  -0.0249   0.2435   1.0000
  15.500   1.4014   0.07329   0.06674  -0.0265   0.2399   1.0000
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