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GOE 494 AIRFOIL (goe494-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 494 AIRFOIL (goe494-il)
Reynolds number: 200,000
Max Cl/Cd: 95.59 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe494-il-200000-n5.txt
Download as CSV file: xf-goe494-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3361   0.10254   0.09907  -0.0304   1.0000   0.0225
  -8.000  -0.3394   0.10090   0.09749  -0.0295   1.0000   0.0227
  -7.750  -0.3459   0.09946   0.09612  -0.0279   1.0000   0.0228
  -7.500  -0.3415   0.09684   0.09353  -0.0296   0.9978   0.0229
  -7.250  -0.3258   0.09293   0.08962  -0.0342   0.9927   0.0229
  -6.750  -0.2942   0.08309   0.07978  -0.0409   0.9842   0.0174
  -6.250  -0.2398   0.07068   0.06733  -0.0611   0.9707   0.0137
  -6.000  -0.2092   0.06504   0.06165  -0.0698   0.9670   0.0138
  -5.750  -0.1921   0.06225   0.05887  -0.0725   0.9608   0.0151
  -5.500  -0.1632   0.05954   0.05612  -0.0774   0.9571   0.0173
  -5.250  -0.1218   0.05375   0.05024  -0.0883   0.9541   0.0180
  -5.000  -0.0838   0.04795   0.04433  -0.0979   0.9471   0.0185
  -4.750  -0.0292   0.04026   0.03639  -0.1119   0.9439   0.0204
  -4.500   0.0435   0.02751   0.02270  -0.1300   0.9421   0.0237
  -4.250   0.0753   0.02507   0.02008  -0.1333   0.9382   0.0262
  -4.000   0.1093   0.02275   0.01736  -0.1360   0.9334   0.0301
  -3.750   0.1475   0.02017   0.01408  -0.1388   0.9302   0.0330
  -3.500   0.1829   0.01810   0.01162  -0.1413   0.9276   0.0364
  -3.250   0.2124   0.01693   0.01016  -0.1419   0.9217   0.0377
  -3.000   0.2445   0.01590   0.00886  -0.1430   0.9172   0.0388
  -2.750   0.2777   0.01523   0.00798  -0.1441   0.9139   0.0414
  -2.250   0.3370   0.01373   0.00614  -0.1449   0.9027   0.0407
  -2.000   0.3682   0.01309   0.00539  -0.1455   0.8983   0.0402
  -1.750   0.3959   0.01261   0.00485  -0.1454   0.8912   0.0397
  -1.500   0.4267   0.01214   0.00431  -0.1460   0.8862   0.0394
  -1.250   0.4541   0.01181   0.00395  -0.1458   0.8777   0.0392
  -1.000   0.4840   0.01148   0.00357  -0.1461   0.8706   0.0392
  -0.750   0.5115   0.01127   0.00330  -0.1459   0.8616   0.0394
  -0.500   0.5399   0.01109   0.00306  -0.1459   0.8546   0.0399
  -0.250   0.5679   0.01096   0.00288  -0.1459   0.8476   0.0406
   0.000   0.5959   0.01085   0.00274  -0.1458   0.8409   0.0420
   0.500   0.6518   0.01035   0.00265  -0.1459   0.8277   0.1746
   0.750   0.6790   0.01004   0.00281  -0.1459   0.8208   0.3407
   1.000   0.7063   0.00993   0.00291  -0.1458   0.8146   0.4100
   1.250   0.7310   0.00935   0.00306  -0.1452   0.8078   0.6782
   1.750   0.7853   0.00904   0.00309  -0.1443   0.7913   1.0000
   2.250   0.8387   0.00922   0.00325  -0.1434   0.7677   1.0000
   2.500   0.8649   0.00932   0.00333  -0.1428   0.7522   1.0000
   2.750   0.8902   0.00946   0.00341  -0.1418   0.7288   1.0000
   3.000   0.9149   0.00964   0.00353  -0.1408   0.7033   1.0000
   3.250   0.9387   0.00982   0.00369  -0.1396   0.6711   1.0000
   3.500   0.9607   0.01007   0.00381  -0.1381   0.6115   1.0000
   3.750   0.9740   0.01103   0.00406  -0.1350   0.4774   1.0000
   4.000   0.9791   0.01319   0.00498  -0.1313   0.2517   1.0000
   4.250   0.9889   0.01529   0.00603  -0.1288   0.0650   1.0000
   4.500   1.0079   0.01641   0.00701  -0.1273   0.0344   1.0000
   4.750   1.0296   0.01717   0.00784  -0.1261   0.0250   1.0000
   5.000   1.0497   0.01817   0.00896  -0.1246   0.0210   1.0000
   5.250   1.0712   0.01892   0.00987  -0.1234   0.0175   1.0000
   5.500   1.0907   0.01994   0.01099  -0.1219   0.0154   1.0000
   5.750   1.1089   0.02120   0.01233  -0.1202   0.0140   1.0000
   6.000   1.1251   0.02308   0.01428  -0.1181   0.0126   1.0000
   6.250   1.1452   0.02474   0.01604  -0.1167   0.0112   1.0000
   6.500   1.1677   0.02639   0.01783  -0.1156   0.0105   1.0000
   6.750   1.1913   0.02843   0.02011  -0.1146   0.0099   1.0000
   7.000   1.2152   0.03078   0.02271  -0.1135   0.0095   1.0000
   7.250   1.2380   0.03346   0.02570  -0.1123   0.0092   1.0000
   7.500   1.2581   0.03605   0.02862  -0.1108   0.0088   1.0000
   7.750   1.2755   0.03774   0.03050  -0.1095   0.0081   1.0000
   8.000   1.2892   0.04001   0.03298  -0.1080   0.0074   1.0000
   8.250   1.2978   0.04436   0.03779  -0.1054   0.0071   1.0000
   8.500   1.3058   0.04796   0.04183  -0.1026   0.0070   1.0000
   8.750   1.3097   0.05184   0.04612  -0.0996   0.0070   1.0000
   9.000   1.3093   0.05586   0.05052  -0.0964   0.0070   1.0000
   9.250   1.3044   0.05990   0.05490  -0.0931   0.0070   1.0000
   9.500   1.2949   0.06376   0.05905  -0.0895   0.0070   1.0000
   9.750   1.2798   0.06727   0.06279  -0.0856   0.0070   1.0000
  10.000   1.2630   0.07100   0.06672  -0.0824   0.0071   1.0000
  10.250   1.2451   0.07519   0.07110  -0.0803   0.0071   1.0000
  10.500   1.2278   0.07968   0.07579  -0.0792   0.0072   1.0000
  10.750   1.2119   0.08426   0.08056  -0.0792   0.0072   1.0000
  11.000   1.1967   0.08929   0.08577  -0.0801   0.0072   1.0000
  11.250   1.1792   0.09534   0.09198  -0.0824   0.0073   1.0000
  11.500   1.1627   0.10218   0.09899  -0.0860   0.0073   1.0000
  11.750   1.1458   0.11078   0.10775  -0.0915   0.0075   1.0000
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