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GOE 474 AIRFOIL (goe474-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 474 AIRFOIL (goe474-il)
Reynolds number: 50,000
Max Cl/Cd: 38.4 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe474-il-50000.txt
Download as CSV file: xf-goe474-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 474 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4286   0.09790   0.09098  -0.0186   1.0000   0.1994
  -7.750  -0.4288   0.09528   0.08843  -0.0183   1.0000   0.2069
  -7.500  -0.4554   0.09525   0.08861  -0.0210   1.0000   0.2101
  -7.250  -0.4307   0.08946   0.08279  -0.0172   1.0000   0.2187
  -7.000  -0.4535   0.08896   0.08246  -0.0212   1.0000   0.2246
  -6.750  -0.4379   0.08433   0.07786  -0.0174   1.0000   0.2368
  -6.500  -0.4335   0.08103   0.07462  -0.0160   1.0000   0.2479
  -6.250  -0.4337   0.07813   0.07180  -0.0152   1.0000   0.2602
  -6.000  -0.4342   0.07532   0.06908  -0.0143   1.0000   0.2735
  -5.750  -0.4339   0.07254   0.06636  -0.0131   1.0000   0.2879
  -5.500  -0.4324   0.06975   0.06361  -0.0114   1.0000   0.3044
  -5.250  -0.4376   0.06769   0.06159  -0.0110   1.0000   0.3274
  -5.000  -0.4310   0.06445   0.05843  -0.0064   1.0000   0.3479
  -4.250  -0.3577   0.04689   0.03931  -0.0327   1.0000   0.1802
  -4.000  -0.3364   0.04221   0.03422  -0.0335   1.0000   0.1636
  -3.750  -0.3157   0.03850   0.03007  -0.0336   1.0000   0.1588
  -3.500  -0.2940   0.03570   0.02673  -0.0334   1.0000   0.1647
  -3.250  -0.2729   0.03312   0.02381  -0.0328   1.0000   0.1708
  -3.000  -0.2493   0.03076   0.02094  -0.0321   1.0000   0.1782
  -2.750  -0.2267   0.02894   0.01870  -0.0314   1.0000   0.1963
  -2.500  -0.2045   0.02706   0.01669  -0.0304   1.0000   0.2181
  -2.250  -0.1812   0.02553   0.01485  -0.0296   1.0000   0.2538
  -2.000  -0.1607   0.02451   0.01392  -0.0286   1.0000   0.2935
  -1.750  -0.1395   0.02370   0.01304  -0.0276   1.0000   0.3241
  -1.500  -0.1150   0.02301   0.01214  -0.0270   1.0000   0.3424
  -1.250  -0.0889   0.02244   0.01149  -0.0268   1.0000   0.3624
  -1.000  -0.0632   0.02200   0.01097  -0.0265   1.0000   0.3822
  -0.750  -0.0384   0.02155   0.01057  -0.0262   1.0000   0.4052
  -0.500  -0.0147   0.02105   0.01026  -0.0257   1.0000   0.4450
  -0.250   0.0230   0.01885   0.00983  -0.0272   1.0000   1.0000
   0.000   0.0460   0.01922   0.00959  -0.0265   1.0000   1.0000
   0.250   0.0662   0.01959   0.00961  -0.0257   1.0000   1.0000
   0.500   0.0858   0.01998   0.00975  -0.0248   1.0000   1.0000
   0.750   0.1051   0.02039   0.00996  -0.0240   1.0000   1.0000
   1.000   0.1242   0.02084   0.01025  -0.0233   1.0000   1.0000
   1.250   0.1432   0.02131   0.01061  -0.0225   1.0000   1.0000
   1.500   0.1620   0.02182   0.01102  -0.0219   1.0000   1.0000
   1.750   0.1807   0.02237   0.01149  -0.0212   1.0000   1.0000
   2.000   0.1991   0.02295   0.01202  -0.0207   1.0000   1.0000
   2.250   0.2173   0.02358   0.01262  -0.0202   1.0000   1.0000
   2.500   0.2352   0.02426   0.01329  -0.0197   1.0000   1.0000
   2.750   0.2527   0.02499   0.01404  -0.0193   1.0000   1.0000
   3.000   0.2698   0.02580   0.01487  -0.0190   1.0000   1.0000
   3.250   0.3277   0.02746   0.01665  -0.0266   0.9793   1.0000
   3.500   0.3921   0.02891   0.01830  -0.0346   0.9512   1.0000
   3.750   0.4728   0.02982   0.01948  -0.0442   0.9143   1.0000
   4.000   0.5391   0.02985   0.01985  -0.0499   0.8755   1.0000
   4.250   0.6142   0.02912   0.01954  -0.0558   0.8389   1.0000
   4.500   0.6987   0.02687   0.01786  -0.0606   0.7978   1.0000
   4.750   0.7505   0.02460   0.01597  -0.0592   0.7465   1.0000
   5.000   0.7930   0.02227   0.01384  -0.0556   0.6741   1.0000
   5.250   0.8194   0.02134   0.01249  -0.0504   0.5546   1.0000
   5.500   0.8382   0.02244   0.01267  -0.0466   0.4488   1.0000
   5.750   0.8616   0.02426   0.01393  -0.0451   0.3841   1.0000
   6.000   0.8865   0.02601   0.01545  -0.0441   0.3412   1.0000
   6.250   0.9121   0.02773   0.01704  -0.0433   0.3091   1.0000
   6.500   0.9352   0.02938   0.01864  -0.0421   0.2802   1.0000
   6.750   0.9558   0.03098   0.02020  -0.0407   0.2516   1.0000
   7.000   0.9753   0.03277   0.02204  -0.0390   0.2240   1.0000
   7.250   0.9935   0.03482   0.02413  -0.0373   0.1962   1.0000
   7.500   1.0100   0.03732   0.02689  -0.0352   0.1718   1.0000
   7.750   1.0294   0.04015   0.02961  -0.0339   0.1517   1.0000
   8.000   1.0433   0.04295   0.03275  -0.0318   0.1368   1.0000
   8.250   1.0544   0.04638   0.03676  -0.0292   0.1283   1.0000
   8.500   1.0641   0.04994   0.04067  -0.0271   0.1209   1.0000
   8.750   1.0697   0.05341   0.04459  -0.0247   0.1150   1.0000
   9.000   1.0853   0.05756   0.04870  -0.0237   0.1106   1.0000
   9.250   1.0827   0.06218   0.05385  -0.0211   0.1103   1.0000
   9.500   1.0754   0.06694   0.05904  -0.0187   0.1102   1.0000
   9.750   1.0670   0.07176   0.06418  -0.0167   0.1103   1.0000
  10.000   1.0549   0.07666   0.06933  -0.0150   0.1105   1.0000
  10.250   0.9822   0.08297   0.07608  -0.0134   0.1200   1.0000
  10.500   0.9623   0.08871   0.08187  -0.0142   0.1220   1.0000
  10.750   0.9035   0.10080   0.09394  -0.0237   0.1332   1.0000
  11.000   0.8962   0.10809   0.10120  -0.0268   0.1364   1.0000
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