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GOE 494 AIRFOIL (goe494-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 494 AIRFOIL (goe494-il)
Reynolds number: 100,000
Max Cl/Cd: 69.52 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe494-il-100000.txt
Download as CSV file: xf-goe494-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3513   0.09905   0.09429  -0.0281   1.0000   0.0577
  -7.250  -0.3634   0.09861   0.09396  -0.0264   1.0000   0.0584
  -7.000  -0.3712   0.09816   0.09366  -0.0278   1.0000   0.0590
  -6.750  -0.3725   0.09715   0.09272  -0.0311   1.0000   0.0594
  -6.500  -0.3691   0.09489   0.09053  -0.0347   1.0000   0.0597
  -6.250  -0.3712   0.08888   0.08450  -0.0224   1.0000   0.0630
  -6.000  -0.3708   0.08674   0.08241  -0.0212   1.0000   0.0662
  -5.750  -0.3697   0.08473   0.08045  -0.0222   1.0000   0.0696
  -5.500  -0.3467   0.08341   0.07910  -0.0376   1.0000   0.0730
  -5.250  -0.3501   0.07914   0.07491  -0.0335   1.0000   0.0741
  -5.000  -0.3529   0.07642   0.07224  -0.0281   1.0000   0.0762
  -4.750  -0.3464   0.07390   0.06973  -0.0277   1.0000   0.0799
  -4.500  -0.3030   0.06938   0.06507  -0.0444   1.0000   0.0876
  -4.250  -0.3073   0.06679   0.06255  -0.0383   1.0000   0.0897
  -4.000  -0.2937   0.06414   0.05988  -0.0390   1.0000   0.0961
  -3.750  -0.2289   0.05924   0.05462  -0.0581   1.0000   0.1150
  -3.500  -0.2376   0.05680   0.05234  -0.0504   1.0000   0.1179
  -3.250  -0.2097   0.05361   0.04907  -0.0546   1.0000   0.1318
  -3.000  -0.1804   0.05056   0.04591  -0.0586   1.0000   0.1459
  -2.750  -0.1535   0.04787   0.04315  -0.0613   1.0000   0.1613
  -2.500  -0.1133   0.04498   0.04009  -0.0672   0.9986   0.1872
  -2.250  -0.0710   0.04302   0.03797  -0.0721   0.9946   0.2254
  -2.000  -0.0324   0.04042   0.03528  -0.0761   0.9904   0.2567
  -1.750   0.0892   0.02829   0.02107  -0.0981   0.9931   0.1111
  -1.500   0.1343   0.02592   0.01804  -0.1017   0.9897   0.1051
  -1.250   0.1773   0.02449   0.01601  -0.1044   0.9859   0.0978
  -1.000   0.2186   0.02344   0.01463  -0.1070   0.9826   0.0950
  -0.750   0.2526   0.02273   0.01368  -0.1083   0.9772   0.0945
  -0.500   0.2902   0.02224   0.01308  -0.1102   0.9727   0.0962
  -0.250   0.3269   0.02198   0.01276  -0.1121   0.9683   0.1017
   0.000   0.3585   0.02170   0.01258  -0.1133   0.9622   0.1117
   0.250   0.3982   0.02157   0.01245  -0.1158   0.9578   0.1226
   0.500   0.4337   0.02121   0.01255  -0.1177   0.9524   0.2299
   0.750   0.4657   0.01985   0.01279  -0.1186   0.9472   1.0000
   1.000   0.5053   0.02030   0.01299  -0.1211   0.9422   1.0000
   1.250   0.5322   0.02070   0.01327  -0.1214   0.9339   1.0000
   1.500   0.5737   0.02110   0.01357  -0.1242   0.9291   1.0000
   1.750   0.5979   0.02153   0.01396  -0.1240   0.9200   1.0000
   2.000   0.6379   0.02189   0.01430  -0.1266   0.9146   1.0000
   2.250   0.6639   0.02232   0.01477  -0.1266   0.9053   1.0000
   2.500   0.6972   0.02270   0.01520  -0.1279   0.8978   1.0000
   2.750   0.7352   0.02289   0.01546  -0.1298   0.8896   1.0000
   3.000   0.7743   0.02279   0.01547  -0.1314   0.8773   1.0000
   3.250   0.8265   0.02197   0.01488  -0.1343   0.8632   1.0000
   3.500   0.8756   0.02112   0.01425  -0.1366   0.8502   1.0000
   3.750   0.9461   0.01754   0.01098  -0.1383   0.8197   1.0000
   4.000   0.9840   0.01547   0.00902  -0.1356   0.7770   1.0000
   4.250   1.0081   0.01450   0.00797  -0.1313   0.7023   1.0000
   4.500   1.0090   0.01568   0.00743  -0.1234   0.3839   1.0000
   4.750   1.0058   0.01942   0.00912  -0.1187   0.0997   1.0000
   5.000   1.0220   0.02104   0.01051  -0.1164   0.0740   1.0000
   5.250   1.0397   0.02240   0.01199  -0.1143   0.0652   1.0000
   5.500   1.0542   0.02437   0.01393  -0.1119   0.0609   1.0000
   5.750   1.0758   0.02608   0.01569  -0.1102   0.0587   1.0000
   6.000   1.1008   0.02789   0.01754  -0.1092   0.0541   1.0000
   6.250   1.1294   0.03021   0.01989  -0.1088   0.0515   1.0000
   6.500   1.1609   0.03287   0.02274  -0.1083   0.0517   1.0000
   6.750   1.1909   0.03590   0.02629  -0.1073   0.0540   1.0000
   7.000   1.2179   0.03974   0.03059  -0.1059   0.0576   1.0000
   7.250   1.2400   0.04375   0.03500  -0.1044   0.0590   1.0000
  10.500   0.9372   0.13192   0.12813  -0.0989   0.1730   1.0000
  10.750   0.9407   0.13632   0.13256  -0.0990   0.1679   1.0000
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