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GOE 494 AIRFOIL (goe494-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 494 AIRFOIL (goe494-il)
Reynolds number: 50,000
Max Cl/Cd: 44.5 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe494-il-50000.txt
Download as CSV file: xf-goe494-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 494 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3733   0.10754   0.10097  -0.0271   1.0000   0.1422
  -7.250  -0.3539   0.10106   0.09446  -0.0250   1.0000   0.1495
  -7.000  -0.3630   0.10038   0.09392  -0.0240   1.0000   0.1544
  -6.750  -0.3751   0.10122   0.09491  -0.0266   1.0000   0.1563
  -6.500  -0.3618   0.09517   0.08887  -0.0216   1.0000   0.1646
  -6.250  -0.3697   0.09520   0.08902  -0.0240   1.0000   0.1698
  -6.000  -0.3635   0.09088   0.08475  -0.0201   1.0000   0.1778
  -5.750  -0.3670   0.09140   0.08536  -0.0263   1.0000   0.1844
  -5.500  -0.3627   0.08674   0.08075  -0.0198   1.0000   0.1952
  -5.000  -0.3552   0.08251   0.07663  -0.0232   1.0000   0.2136
  -4.750  -0.3504   0.07959   0.07375  -0.0211   1.0000   0.2247
  -4.500  -0.3454   0.07656   0.07076  -0.0197   1.0000   0.2338
  -4.250  -0.3373   0.07390   0.06814  -0.0204   1.0000   0.2466
  -4.000  -0.3280   0.07120   0.06545  -0.0209   1.0000   0.2618
  -3.750  -0.3104   0.06880   0.06297  -0.0254   1.0000   0.2840
  -3.500  -0.3043   0.06576   0.05998  -0.0227   1.0000   0.3009
  -3.250  -0.2930   0.06313   0.05736  -0.0224   1.0000   0.3285
  -3.000  -0.2756   0.06097   0.05517  -0.0243   1.0000   0.3671
  -2.750  -0.2711   0.05774   0.05201  -0.0201   1.0000   0.3875
  -1.750   0.0509   0.03471   0.02591  -0.0908   1.0000   0.1701
  -1.500   0.0942   0.03173   0.02217  -0.0947   1.0000   0.1563
  -1.250   0.1255   0.02992   0.02005  -0.0960   1.0000   0.1528
  -1.000   0.1569   0.02851   0.01820  -0.0971   1.0000   0.1513
  -0.750   0.1858   0.02762   0.01685  -0.0977   1.0000   0.1573
  -0.500   0.2123   0.02697   0.01608  -0.0979   1.0000   0.1645
  -0.250   0.2404   0.02643   0.01515  -0.0980   1.0000   0.1694
   0.000   0.2669   0.02603   0.01464  -0.0980   1.0000   0.1786
   0.250   0.2936   0.02577   0.01430  -0.0980   1.0000   0.1953
   0.500   0.3222   0.02542   0.01418  -0.0984   1.0000   0.2441
   0.750   0.3433   0.02341   0.01391  -0.0970   1.0000   1.0000
   1.000   0.3648   0.02404   0.01411  -0.0965   1.0000   1.0000
   1.250   0.3856   0.02471   0.01450  -0.0961   1.0000   1.0000
   1.500   0.4059   0.02542   0.01500  -0.0958   1.0000   1.0000
   1.750   0.4259   0.02617   0.01561  -0.0954   1.0000   1.0000
   2.000   0.4454   0.02697   0.01630  -0.0951   1.0000   1.0000
   2.250   0.4646   0.02782   0.01706  -0.0948   1.0000   1.0000
   2.500   0.4833   0.02872   0.01792  -0.0946   1.0000   1.0000
   2.750   0.5017   0.02967   0.01884  -0.0943   1.0000   1.0000
   3.000   0.5196   0.03069   0.01986  -0.0941   1.0000   1.0000
   3.250   0.5372   0.03177   0.02096  -0.0939   1.0000   1.0000
   3.500   0.5543   0.03291   0.02218  -0.0938   1.0000   1.0000
   3.750   0.5851   0.03440   0.02376  -0.0964   0.9921   1.0000
   4.000   0.6289   0.03606   0.02558  -0.1012   0.9753   1.0000
   4.250   0.6811   0.03759   0.02739  -0.1070   0.9518   1.0000
   4.500   0.7377   0.03866   0.02877  -0.1125   0.9222   1.0000
   4.750   0.7888   0.03944   0.02991  -0.1167   0.8957   1.0000
   5.000   0.8401   0.04000   0.03091  -0.1203   0.8716   1.0000
   5.250   1.0266   0.02307   0.01343  -0.1107   0.3257   1.0000
   5.500   1.0203   0.02733   0.01597  -0.1060   0.1601   1.0000
   5.750   1.0337   0.02969   0.01804  -0.1033   0.1299   1.0000
   6.000   1.0557   0.03179   0.02008  -0.1015   0.1147   1.0000
   6.250   1.0888   0.03400   0.02220  -0.1012   0.1001   1.0000
   6.500   1.1350   0.03696   0.02528  -0.1021   0.0943   1.0000
   6.750   1.1734   0.04031   0.02896  -0.1021   0.0926   1.0000
   7.000   1.2028   0.04375   0.03290  -0.1012   0.0908   1.0000
   7.250   1.2273   0.04727   0.03673  -0.1001   0.0879   1.0000
   7.500   1.2468   0.05135   0.04151  -0.0980   0.0895   1.0000
   7.750   1.2624   0.05616   0.04698  -0.0958   0.0936   1.0000
   8.000   1.2794   0.06160   0.05270  -0.0944   0.0974   1.0000
   8.250   1.2779   0.06639   0.05856  -0.0907   0.1053   1.0000
   8.500   1.2864   0.07210   0.06468  -0.0889   0.1135   1.0000
   8.750   1.2888   0.07897   0.07201  -0.0873   0.1256   1.0000
   9.000   1.2569   0.08435   0.07806  -0.0847   0.1331   1.0000
   9.250   1.2491   0.09207   0.08611  -0.0847   0.1531   1.0000
   9.500   1.2123   0.09673   0.09097  -0.0835   0.1545   1.0000
   9.750   1.1780   0.10221   0.09651  -0.0842   0.1554   1.0000
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