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GOE 180 (MVA H.26) AIRFOIL (goe180-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 180 (MVA H.26) AIRFOIL (goe180-il)
Reynolds number: 50,000
Max Cl/Cd: 40.55 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe180-il-50000-n5.txt
Download as CSV file: xf-goe180-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 180 (MVA H.26) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3412   0.10035   0.09367  -0.0258   1.0000   0.1127
  -7.500  -0.3527   0.09919   0.09267  -0.0277   1.0000   0.1153
  -7.250  -0.3596   0.09763   0.09123  -0.0324   1.0000   0.1163
  -7.000  -0.3531   0.09328   0.08697  -0.0307   1.0000   0.1175
  -6.750  -0.3453   0.08956   0.08329  -0.0281   1.0000   0.1196
  -6.500  -0.3412   0.08666   0.08043  -0.0274   1.0000   0.1224
  -6.250  -0.3394   0.08414   0.07797  -0.0285   1.0000   0.1276
  -6.000  -0.3389   0.08166   0.07552  -0.0350   1.0000   0.1323
  -5.750  -0.3333   0.07836   0.07232  -0.0296   1.0000   0.1368
  -5.500  -0.3275   0.07581   0.06977  -0.0316   1.0000   0.1444
  -5.250  -0.3019   0.06731   0.06089  -0.0422   1.0000   0.0847
  -4.750  -0.2699   0.05791   0.05120  -0.0474   1.0000   0.0728
  -4.500  -0.2558   0.05519   0.04842  -0.0476   1.0000   0.0742
  -4.250  -0.2372   0.05204   0.04512  -0.0491   1.0000   0.0752
  -4.000  -0.1960   0.04631   0.03854  -0.0558   0.9976   0.0712
  -3.750  -0.1530   0.04227   0.03411  -0.0611   0.9900   0.0708
  -3.500  -0.1105   0.03889   0.03034  -0.0659   0.9817   0.0728
  -3.250  -0.0695   0.03652   0.02771  -0.0698   0.9723   0.0757
  -3.000  -0.0251   0.03368   0.02431  -0.0738   0.9634   0.0759
  -2.750   0.0178   0.03137   0.02148  -0.0772   0.9535   0.0766
  -2.500   0.0584   0.02950   0.01919  -0.0798   0.9423   0.0780
  -2.250   0.0993   0.02808   0.01736  -0.0823   0.9309   0.0826
  -2.000   0.1418   0.02673   0.01558  -0.0848   0.9203   0.0864
  -1.750   0.1834   0.02545   0.01418  -0.0871   0.9100   0.0897
  -1.500   0.2223   0.02449   0.01304  -0.0887   0.8975   0.0943
  -1.250   0.2607   0.02365   0.01193  -0.0901   0.8842   0.1009
  -1.000   0.2975   0.02289   0.01116  -0.0915   0.8700   0.1140
  -0.750   0.3330   0.02213   0.01048  -0.0927   0.8549   0.1416
  -0.500   0.3674   0.02115   0.00990  -0.0938   0.8393   0.2248
  -0.250   0.3953   0.01874   0.00952  -0.0928   0.8235   1.0000
   0.000   0.4277   0.01879   0.00914  -0.0932   0.8066   1.0000
   0.250   0.4593   0.01886   0.00888  -0.0934   0.7900   1.0000
   0.500   0.4900   0.01895   0.00869  -0.0935   0.7739   1.0000
   0.750   0.5192   0.01910   0.00860  -0.0934   0.7576   1.0000
   1.000   0.5484   0.01926   0.00855  -0.0933   0.7425   1.0000
   1.250   0.5773   0.01944   0.00853  -0.0931   0.7283   1.0000
   1.500   0.6054   0.01968   0.00861  -0.0929   0.7144   1.0000
   1.750   0.6333   0.01997   0.00876  -0.0928   0.7011   1.0000
   2.000   0.6609   0.02028   0.00896  -0.0926   0.6885   1.0000
   2.250   0.6885   0.02059   0.00916  -0.0924   0.6762   1.0000
   2.500   0.7160   0.02089   0.00935  -0.0921   0.6636   1.0000
   2.750   0.7430   0.02117   0.00954  -0.0916   0.6499   1.0000
   3.000   0.7691   0.02146   0.00973  -0.0910   0.6348   1.0000
   3.250   0.7948   0.02175   0.00994  -0.0903   0.6194   1.0000
   3.500   0.8207   0.02207   0.01021  -0.0896   0.6051   1.0000
   3.750   0.8468   0.02244   0.01056  -0.0891   0.5928   1.0000
   4.000   0.8719   0.02289   0.01104  -0.0886   0.5809   1.0000
   4.250   0.8973   0.02334   0.01154  -0.0881   0.5695   1.0000
   4.500   0.9232   0.02376   0.01197  -0.0876   0.5584   1.0000
   4.750   0.9488   0.02419   0.01243  -0.0871   0.5468   1.0000
   5.000   0.9727   0.02469   0.01303  -0.0864   0.5342   1.0000
   5.250   0.9967   0.02519   0.01364  -0.0857   0.5214   1.0000
   5.500   1.0207   0.02569   0.01422  -0.0849   0.5085   1.0000
   5.750   1.0443   0.02617   0.01479  -0.0840   0.4945   1.0000
   6.000   1.0667   0.02662   0.01535  -0.0829   0.4782   1.0000
   6.250   1.0881   0.02704   0.01586  -0.0816   0.4604   1.0000
   6.500   1.1092   0.02745   0.01633  -0.0803   0.4421   1.0000
   6.750   1.1302   0.02787   0.01682  -0.0790   0.4242   1.0000
   7.000   1.1506   0.02839   0.01749  -0.0777   0.4070   1.0000
   7.250   1.1704   0.02903   0.01829  -0.0764   0.3900   1.0000
   7.500   1.1902   0.02970   0.01912  -0.0751   0.3738   1.0000
   7.750   1.2097   0.03042   0.01999  -0.0739   0.3581   1.0000
   8.000   1.2288   0.03116   0.02091  -0.0725   0.3429   1.0000
   8.250   1.2474   0.03194   0.02183  -0.0712   0.3283   1.0000
   8.500   1.2657   0.03277   0.02279  -0.0698   0.3147   1.0000
   8.750   1.2840   0.03364   0.02379  -0.0684   0.3024   1.0000
   9.000   1.3031   0.03456   0.02482  -0.0671   0.2916   1.0000
   9.250   1.3204   0.03575   0.02628  -0.0657   0.2808   1.0000
   9.500   1.3367   0.03691   0.02762  -0.0642   0.2695   1.0000
   9.750   1.3452   0.03789   0.02865  -0.0618   0.2521   1.0000
  10.000   1.3466   0.03894   0.02960  -0.0587   0.2315   1.0000
  10.250   1.3420   0.04044   0.03119  -0.0553   0.2119   1.0000
  10.500   1.3363   0.04214   0.03302  -0.0521   0.1949   1.0000
  10.750   1.3312   0.04415   0.03522  -0.0495   0.1783   1.0000
  11.000   1.3255   0.04650   0.03773  -0.0476   0.1612   1.0000
  11.250   1.3182   0.04931   0.04062  -0.0462   0.1445   1.0000
  11.500   1.3088   0.05275   0.04415  -0.0454   0.1270   1.0000
  11.750   1.2973   0.05681   0.04821  -0.0452   0.1108   1.0000
  12.000   1.2854   0.06130   0.05275  -0.0455   0.0953   1.0000
  12.250   1.2740   0.06603   0.05754  -0.0460   0.0823   1.0000
  12.500   1.2627   0.07090   0.06243  -0.0468   0.0740   1.0000
  12.750   1.2511   0.07594   0.06747  -0.0479   0.0684   1.0000
  13.000   1.2405   0.08093   0.07248  -0.0489   0.0641   1.0000
  13.250   1.2306   0.08591   0.07753  -0.0500   0.0603   1.0000
  13.500   1.2202   0.09099   0.08262  -0.0514   0.0575   1.0000
  13.750   1.2115   0.09586   0.08751  -0.0525   0.0549   1.0000
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