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GOE 140 (MVA H.17) AIRFOIL (goe140-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 140 (MVA H.17) AIRFOIL (goe140-il)
Reynolds number: 500,000
Max Cl/Cd: 96.45 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe140-il-500000-n5.txt
Download as CSV file: xf-goe140-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 140 (MVA H.17) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3109   0.09590   0.09380  -0.0203   1.0000   0.0108
  -8.250  -0.3087   0.09201   0.08994  -0.0221   1.0000   0.0111
  -8.000  -0.3054   0.08641   0.08435  -0.0267   0.9811   0.0116
  -7.750  -0.2876   0.08355   0.08147  -0.0304   0.9543   0.0119
  -7.500  -0.2713   0.08076   0.07863  -0.0338   0.9210   0.0122
  -7.250  -0.2586   0.07815   0.07592  -0.0362   0.8856   0.0127
  -7.000  -0.2452   0.07497   0.07261  -0.0396   0.8561   0.0134
  -6.750  -0.2295   0.07048   0.06800  -0.0450   0.8330   0.0143
  -6.500  -0.2083   0.06300   0.06037  -0.0551   0.8155   0.0154
  -6.250  -0.1883   0.06112   0.05838  -0.0571   0.7970   0.0157
  -6.000  -0.1666   0.05902   0.05619  -0.0596   0.7790   0.0162
  -5.750  -0.1424   0.05610   0.05314  -0.0634   0.7617   0.0172
  -5.500  -0.1147   0.05177   0.04864  -0.0687   0.7451   0.0182
  -5.250  -0.0767   0.04404   0.04060  -0.0779   0.7307   0.0203
  -5.000  -0.0539   0.04296   0.03941  -0.0786   0.7112   0.0207
  -4.750  -0.0288   0.04130   0.03760  -0.0800   0.6915   0.0214
  -4.500  -0.0003   0.03866   0.03475  -0.0824   0.6726   0.0219
  -4.250   0.0294   0.03581   0.03167  -0.0847   0.6544   0.0226
  -4.000   0.0601   0.03302   0.02862  -0.0867   0.6371   0.0237
  -3.750   0.0919   0.02995   0.02524  -0.0886   0.6204   0.0246
  -3.500   0.1228   0.02726   0.02225  -0.0900   0.6040   0.0251
  -3.250   0.1533   0.02490   0.01958  -0.0910   0.5880   0.0254
  -3.000   0.1835   0.02310   0.01750  -0.0917   0.5714   0.0260
  -2.750   0.2136   0.02139   0.01549  -0.0922   0.5544   0.0264
  -2.500   0.2450   0.01764   0.01120  -0.0935   0.5388   0.0269
  -2.250   0.2746   0.01588   0.00908  -0.0941   0.5218   0.0275
  -2.000   0.3034   0.01492   0.00785  -0.0944   0.5036   0.0279
  -1.750   0.3321   0.01416   0.00686  -0.0947   0.4871   0.0282
  -1.500   0.3607   0.01352   0.00601  -0.0949   0.4724   0.0284
  -1.250   0.3892   0.01314   0.00548  -0.0950   0.4592   0.0290
  -1.000   0.4175   0.01282   0.00503  -0.0951   0.4466   0.0296
  -0.500   0.4744   0.01201   0.00396  -0.0953   0.4237   0.0299
  -0.250   0.5028   0.01174   0.00360  -0.0955   0.4146   0.0301
   0.000   0.5312   0.01154   0.00332  -0.0956   0.4057   0.0306
   0.250   0.5597   0.01138   0.00310  -0.0957   0.3978   0.0311
   0.500   0.5881   0.01128   0.00294  -0.0958   0.3898   0.0320
   0.750   0.6166   0.01119   0.00281  -0.0959   0.3827   0.0329
   1.000   0.6449   0.01116   0.00273  -0.0961   0.3753   0.0338
   1.250   0.6733   0.01114   0.00267  -0.0962   0.3687   0.0346
   1.500   0.7015   0.01115   0.00264  -0.0963   0.3616   0.0354
   1.750   0.7297   0.01119   0.00264  -0.0964   0.3553   0.0360
   2.000   0.7579   0.01121   0.00264  -0.0965   0.3484   0.0390
   2.250   0.7859   0.01127   0.00270  -0.0965   0.3409   0.0435
   2.500   0.8139   0.01135   0.00280  -0.0966   0.3321   0.0565
   2.750   0.8417   0.01146   0.00289  -0.0966   0.3246   0.0697
   3.000   0.8694   0.01156   0.00299  -0.0967   0.3177   0.0771
   3.250   0.8971   0.01167   0.00309  -0.0967   0.3120   0.0851
   3.500   0.9249   0.01176   0.00320  -0.0968   0.3069   0.0910
   3.750   0.9525   0.01187   0.00334  -0.0968   0.3019   0.1040
   4.250   1.0017   0.01057   0.00374  -0.0960   0.2906   1.0000
   4.500   1.0287   0.01080   0.00390  -0.0960   0.2806   1.0000
   4.750   1.0556   0.01103   0.00407  -0.0959   0.2703   1.0000
   5.000   1.0827   0.01124   0.00425  -0.0959   0.2615   1.0000
   5.250   1.1092   0.01150   0.00445  -0.0958   0.2494   1.0000
   5.500   1.1355   0.01180   0.00468  -0.0957   0.2366   1.0000
   5.750   1.1613   0.01214   0.00493  -0.0956   0.2197   1.0000
   6.000   1.1797   0.01352   0.00573  -0.0947   0.1252   1.0000
   6.250   1.1976   0.01497   0.00680  -0.0936   0.0568   1.0000
   6.500   1.2182   0.01597   0.00764  -0.0927   0.0162   1.0000
   6.750   1.2424   0.01644   0.00815  -0.0923   0.0138   1.0000
   7.000   1.2664   0.01691   0.00869  -0.0918   0.0122   1.0000
   7.250   1.2903   0.01736   0.00921  -0.0913   0.0115   1.0000
   7.500   1.3135   0.01786   0.00978  -0.0907   0.0107   1.0000
   7.750   1.3360   0.01842   0.01041  -0.0901   0.0098   1.0000
   8.000   1.3564   0.01917   0.01125  -0.0892   0.0089   1.0000
   8.250   1.3773   0.01982   0.01198  -0.0883   0.0085   1.0000
   8.500   1.3975   0.02050   0.01274  -0.0873   0.0081   1.0000
   8.750   1.4163   0.02127   0.01359  -0.0862   0.0077   1.0000
   9.000   1.4335   0.02212   0.01452  -0.0849   0.0074   1.0000
   9.250   1.4491   0.02303   0.01550  -0.0834   0.0070   1.0000
   9.500   1.4631   0.02399   0.01653  -0.0817   0.0067   1.0000
   9.750   1.4732   0.02511   0.01772  -0.0795   0.0064   1.0000
  10.000   1.4742   0.02655   0.01928  -0.0759   0.0062   1.0000
  10.250   1.4815   0.02767   0.02049  -0.0735   0.0060   1.0000
  10.500   1.4852   0.02916   0.02209  -0.0711   0.0058   1.0000
  10.750   1.4867   0.03100   0.02405  -0.0689   0.0057   1.0000
  11.000   1.4867   0.03321   0.02638  -0.0673   0.0055   1.0000
  11.250   1.4859   0.03578   0.02906  -0.0662   0.0054   1.0000
  11.500   1.4839   0.03872   0.03213  -0.0656   0.0053   1.0000
  11.750   1.4808   0.04205   0.03557  -0.0654   0.0052   1.0000
  12.000   1.4769   0.04568   0.03932  -0.0655   0.0051   1.0000
  12.250   1.4718   0.04962   0.04338  -0.0660   0.0050   1.0000
  12.500   1.4659   0.05376   0.04764  -0.0665   0.0049   1.0000
  12.750   1.4592   0.05805   0.05206  -0.0672   0.0049   1.0000
  13.000   1.4523   0.06242   0.05653  -0.0679   0.0048   1.0000
  13.250   1.4447   0.06684   0.06105  -0.0686   0.0047   1.0000
  13.500   1.4374   0.07125   0.06556  -0.0693   0.0047   1.0000
  13.750   1.4306   0.07565   0.07005  -0.0701   0.0046   1.0000
  14.000   1.4242   0.08000   0.07448  -0.0708   0.0046   1.0000
  14.250   1.4186   0.08427   0.07883  -0.0716   0.0045   1.0000
  14.500   1.4138   0.08845   0.08309  -0.0724   0.0045   1.0000
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