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GOE 375 AIRFOIL (goe375-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 375 AIRFOIL (goe375-il)
Reynolds number: 100,000
Max Cl/Cd: 46.62 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe375-il-100000.txt
Download as CSV file: xf-goe375-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 375 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3557   0.09783   0.09302  -0.0112   1.0000   0.0329
  -7.750  -0.3533   0.09537   0.09063  -0.0125   1.0000   0.0337
  -7.500  -0.3523   0.09322   0.08856  -0.0138   1.0000   0.0342
  -7.250  -0.3478   0.09100   0.08639  -0.0169   1.0000   0.0346
  -7.000  -0.3383   0.08977   0.08517  -0.0248   1.0000   0.0351
  -6.750  -0.3276   0.08678   0.08218  -0.0282   1.0000   0.0353
  -6.500  -0.3255   0.08116   0.07669  -0.0227   1.0000   0.0361
  -6.250  -0.3190   0.07766   0.07324  -0.0218   1.0000   0.0372
  -6.000  -0.3102   0.07456   0.07016  -0.0226   1.0000   0.0383
  -5.750  -0.2999   0.07155   0.06717  -0.0240   1.0000   0.0393
  -5.500  -0.2880   0.06861   0.06424  -0.0255   1.0000   0.0406
  -5.250  -0.2726   0.06584   0.06143  -0.0278   1.0000   0.0423
  -5.000  -0.2448   0.06489   0.06016  -0.0327   1.0000   0.0438
  -4.750  -0.2350   0.06126   0.05653  -0.0326   1.0000   0.0444
  -4.500  -0.2336   0.05725   0.05267  -0.0302   1.0000   0.0455
  -4.250  -0.2271   0.05451   0.04997  -0.0289   1.0000   0.0471
  -4.000  -0.2162   0.05213   0.04754  -0.0283   1.0000   0.0493
  -3.750  -0.1996   0.05011   0.04537  -0.0285   1.0000   0.0526
  -3.500  -0.1771   0.04838   0.04331  -0.0294   1.0000   0.0558
  -3.250  -0.1710   0.04501   0.04008  -0.0281   1.0000   0.0586
  -2.750  -0.1372   0.04070   0.03550  -0.0279   1.0000   0.0717
  -2.500  -0.1138   0.04030   0.03465  -0.0279   1.0000   0.0827
  -2.250  -0.0788   0.03658   0.03089  -0.0317   0.9942   0.0981
  -2.000  -0.0348   0.03346   0.02767  -0.0369   0.9847   0.1278
  -1.500   0.0385   0.02781   0.02227  -0.0444   0.9602   0.3037
  -1.250   0.0740   0.02474   0.01954  -0.0456   0.9463   0.4007
  -1.000   0.1237   0.02233   0.01704  -0.0488   0.9322   0.4484
  -0.750   0.2057   0.02100   0.01461  -0.0575   0.9191   0.3278
  -0.500   0.2729   0.02044   0.01299  -0.0606   0.9049   0.1950
  -0.250   0.3222   0.01925   0.01133  -0.0617   0.8882   0.1477
   0.000   0.3651   0.01816   0.00999  -0.0625   0.8691   0.1305
   0.250   0.3990   0.01743   0.00910  -0.0618   0.8439   0.1204
   0.500   0.4302   0.01699   0.00843  -0.0606   0.8162   0.1112
   0.750   0.4569   0.01632   0.00772  -0.0591   0.7856   0.1075
   1.000   0.4816   0.01583   0.00716  -0.0573   0.7527   0.1048
   1.250   0.5058   0.01551   0.00669  -0.0555   0.7169   0.1071
   1.500   0.5303   0.01531   0.00625  -0.0539   0.6794   0.1074
   1.750   0.5551   0.01524   0.00591  -0.0524   0.6418   0.1073
   2.000   0.5797   0.01533   0.00567  -0.0511   0.6054   0.1084
   2.250   0.6042   0.01555   0.00557  -0.0498   0.5705   0.1112
   2.500   0.6286   0.01581   0.00560  -0.0487   0.5377   0.1197
   2.750   0.6699   0.01445   0.00582  -0.0515   0.5023   1.0000
   3.000   0.6936   0.01495   0.00603  -0.0504   0.4745   1.0000
   3.250   0.7174   0.01546   0.00626  -0.0493   0.4498   1.0000
   3.500   0.7413   0.01596   0.00651  -0.0484   0.4279   1.0000
   3.750   0.7655   0.01646   0.00681  -0.0476   0.4083   1.0000
   4.000   0.7896   0.01696   0.00719  -0.0468   0.3901   1.0000
   4.250   0.8139   0.01746   0.00756  -0.0461   0.3740   1.0000
   4.500   0.8382   0.01798   0.00796  -0.0454   0.3592   1.0000
   4.750   0.8626   0.01853   0.00841  -0.0447   0.3459   1.0000
   5.000   0.8872   0.01912   0.00894  -0.0441   0.3339   1.0000
   5.500   0.9360   0.02033   0.01005  -0.0429   0.3108   1.0000
   5.750   0.9599   0.02099   0.01073  -0.0423   0.2997   1.0000
   6.000   0.9843   0.02171   0.01142  -0.0417   0.2900   1.0000
   6.250   1.0088   0.02245   0.01217  -0.0412   0.2810   1.0000
   6.500   1.0325   0.02333   0.01319  -0.0406   0.2726   1.0000
   6.750   1.0575   0.02420   0.01398  -0.0402   0.2657   1.0000
   7.000   1.0802   0.02520   0.01523  -0.0395   0.2583   1.0000
   7.250   1.1047   0.02608   0.01613  -0.0390   0.2518   1.0000
   7.500   1.1268   0.02721   0.01751  -0.0383   0.2454   1.0000
   7.750   1.1498   0.02827   0.01873  -0.0377   0.2400   1.0000
   8.000   1.1748   0.02955   0.01998  -0.0375   0.2359   1.0000
   8.250   1.1931   0.03103   0.02198  -0.0363   0.2312   1.0000
   8.500   1.2145   0.03222   0.02338  -0.0356   0.2261   1.0000
   8.750   1.2368   0.03311   0.02432  -0.0350   0.2196   1.0000
   9.000   1.2572   0.03326   0.02459  -0.0340   0.2099   1.0000
   9.250   1.2756   0.03369   0.02525  -0.0329   0.2006   1.0000
   9.500   1.3012   0.03368   0.02507  -0.0325   0.1928   1.0000
   9.750   1.3151   0.03449   0.02638  -0.0309   0.1855   1.0000
  10.000   1.3348   0.03382   0.02573  -0.0297   0.1747   1.0000
  10.250   1.3530   0.03292   0.02487  -0.0283   0.1635   1.0000
  10.500   1.3640   0.03207   0.02432  -0.0260   0.1494   1.0000
  10.750   1.3726   0.03146   0.02406  -0.0235   0.1288   1.0000
  11.000   1.3795   0.03204   0.02471  -0.0213   0.0882   1.0000
  11.250   1.3758   0.03449   0.02687  -0.0184   0.0595   1.0000
  11.500   1.3663   0.03704   0.02938  -0.0150   0.0526   1.0000
  11.750   1.3577   0.03960   0.03209  -0.0123   0.0489   1.0000
  12.000   1.3470   0.04256   0.03519  -0.0104   0.0468   1.0000
  12.250   1.3330   0.04621   0.03897  -0.0097   0.0453   1.0000
  12.500   1.3180   0.05048   0.04339  -0.0101   0.0444   1.0000
  12.750   1.3030   0.05530   0.04836  -0.0114   0.0438   1.0000
  13.000   1.2903   0.06034   0.05356  -0.0132   0.0433   1.0000
  13.250   1.2774   0.06583   0.05923  -0.0156   0.0427   1.0000
  13.500   1.2652   0.07135   0.06492  -0.0179   0.0422   1.0000
  13.750   1.2541   0.07682   0.07054  -0.0201   0.0417   1.0000
  14.000   1.2434   0.08225   0.07611  -0.0223   0.0410   1.0000
  14.250   1.2341   0.08748   0.08148  -0.0243   0.0403   1.0000
  14.500   1.2249   0.09279   0.08692  -0.0264   0.0395   1.0000
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