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GOE 368 AIRFOIL (goe368-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 368 AIRFOIL (goe368-il)
Reynolds number: 1,000,000
Max Cl/Cd: 98.59 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe368-il-1000000.txt
Download as CSV file: xf-goe368-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 368 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4109   0.08179   0.08031  -0.0100   1.0000   0.0094
  -7.500  -0.4134   0.07847   0.07703  -0.0108   1.0000   0.0094
  -7.250  -0.4109   0.07431   0.07289  -0.0138   1.0000   0.0094
  -7.000  -0.4183   0.06611   0.06471  -0.0206   1.0000   0.0098
  -6.750  -0.4107   0.06131   0.05989  -0.0247   1.0000   0.0100
  -6.500  -0.3989   0.05740   0.05597  -0.0278   1.0000   0.0102
  -6.250  -0.3856   0.05295   0.05148  -0.0311   1.0000   0.0104
  -6.000  -0.3712   0.04696   0.04541  -0.0351   1.0000   0.0105
  -5.250  -0.2750   0.01674   0.01318  -0.0551   0.9865   0.0082
  -5.000  -0.2409   0.01416   0.01020  -0.0566   0.9796   0.0084
  -4.500  -0.1652   0.01221   0.00784  -0.0605   0.9463   0.0095
  -4.250  -0.1333   0.01049   0.00572  -0.0612   0.8747   0.0099
  -4.000  -0.1098   0.00988   0.00481  -0.0600   0.8265   0.0104
  -3.750  -0.0843   0.00960   0.00438  -0.0593   0.7994   0.0113
  -3.250  -0.0323   0.00892   0.00338  -0.0580   0.7386   0.0130
  -3.000  -0.0066   0.00876   0.00299  -0.0572   0.6916   0.0139
  -2.750   0.0194   0.00850   0.00249  -0.0566   0.6553   0.0149
  -2.500   0.0461   0.00818   0.00199  -0.0561   0.6339   0.0173
  -2.250   0.0732   0.00802   0.00174  -0.0557   0.6193   0.0204
  -2.000   0.1005   0.00782   0.00145  -0.0553   0.6059   0.0282
  -1.750   0.1268   0.00740   0.00128  -0.0550   0.5926   0.1116
  -1.500   0.1543   0.00743   0.00125  -0.0548   0.5769   0.1213
  -1.250   0.1818   0.00744   0.00123  -0.0545   0.5583   0.1287
  -1.000   0.2093   0.00750   0.00118  -0.0542   0.5341   0.1322
  -0.750   0.2363   0.00753   0.00112  -0.0539   0.5021   0.1386
  -0.500   0.2631   0.00767   0.00112  -0.0536   0.4641   0.1442
  -0.250   0.2901   0.00777   0.00109  -0.0533   0.4362   0.1470
   0.000   0.3172   0.00782   0.00108  -0.0530   0.4164   0.1525
   0.250   0.3445   0.00788   0.00109  -0.0528   0.4002   0.1577
   0.500   0.3719   0.00793   0.00109  -0.0525   0.3860   0.1644
   0.750   0.3993   0.00799   0.00112  -0.0523   0.3728   0.1717
   1.000   0.4267   0.00804   0.00114  -0.0521   0.3597   0.1794
   1.250   0.4541   0.00812   0.00118  -0.0519   0.3459   0.1866
   1.500   0.4814   0.00818   0.00122  -0.0517   0.3324   0.1940
   1.750   0.5087   0.00827   0.00126  -0.0515   0.3188   0.2006
   2.000   0.5360   0.00835   0.00131  -0.0513   0.3054   0.2079
   2.250   0.5632   0.00844   0.00137  -0.0510   0.2915   0.2148
   2.500   0.5903   0.00853   0.00144  -0.0508   0.2775   0.2233
   2.750   0.6174   0.00864   0.00153  -0.0506   0.2632   0.2326
   3.000   0.6443   0.00875   0.00163  -0.0504   0.2489   0.2458
   3.250   0.6711   0.00884   0.00174  -0.0502   0.2354   0.2728
   3.500   0.7008   0.00745   0.00197  -0.0510   0.2202   1.0000
   3.750   0.7270   0.00767   0.00211  -0.0507   0.2044   1.0000
   4.000   0.7534   0.00787   0.00224  -0.0503   0.1942   1.0000
   4.250   0.7800   0.00805   0.00237  -0.0500   0.1857   1.0000
   4.500   0.8064   0.00824   0.00251  -0.0497   0.1759   1.0000
   4.750   0.8326   0.00846   0.00268  -0.0494   0.1650   1.0000
   5.000   0.8587   0.00871   0.00284  -0.0490   0.1497   1.0000
   5.250   0.8786   0.00992   0.00351  -0.0480   0.0578   1.0000
   5.500   0.9017   0.01071   0.00415  -0.0472   0.0149   1.0000
   5.750   0.9276   0.01102   0.00455  -0.0467   0.0125   1.0000
   6.000   0.9532   0.01136   0.00495  -0.0463   0.0118   1.0000
   6.250   0.9785   0.01174   0.00539  -0.0458   0.0109   1.0000
   6.500   1.0034   0.01219   0.00588  -0.0452   0.0097   1.0000
   6.750   1.0278   0.01271   0.00647  -0.0446   0.0090   1.0000
   7.000   1.0512   0.01339   0.00724  -0.0439   0.0084   1.0000
   7.250   1.0711   0.01462   0.00863  -0.0427   0.0077   1.0000
   7.500   1.0917   0.01561   0.00974  -0.0416   0.0074   1.0000
   7.750   1.1154   0.01613   0.01031  -0.0409   0.0070   1.0000
   8.000   1.1361   0.01703   0.01129  -0.0399   0.0068   1.0000
   8.250   1.1563   0.01794   0.01228  -0.0388   0.0065   1.0000
   8.500   1.1769   0.01873   0.01314  -0.0378   0.0060   1.0000
   8.750   1.1956   0.01973   0.01421  -0.0366   0.0058   1.0000
   9.000   1.2120   0.02095   0.01551  -0.0351   0.0057   1.0000
   9.250   1.2279   0.02220   0.01683  -0.0336   0.0056   1.0000
   9.500   1.2436   0.02340   0.01808  -0.0322   0.0054   1.0000
   9.750   1.2582   0.02467   0.01942  -0.0307   0.0052   1.0000
  10.000   1.2712   0.02608   0.02087  -0.0291   0.0050   1.0000
  10.250   1.2816   0.02792   0.02276  -0.0272   0.0049   1.0000
  10.500   1.2919   0.03185   0.02673  -0.0256   0.0046   1.0000
  10.750   1.3066   0.03451   0.02951  -0.0244   0.0046   1.0000
  11.000   1.3189   0.03645   0.03157  -0.0229   0.0047   1.0000
  11.250   1.3257   0.03740   0.03267  -0.0206   0.0048   1.0000
  13.000   1.2582   0.06102   0.05772  -0.0126   0.0056   1.0000
  13.250   1.2479   0.06548   0.06231  -0.0147   0.0055   1.0000
  13.500   1.2364   0.07045   0.06741  -0.0173   0.0055   1.0000
  13.750   1.2201   0.07662   0.07374  -0.0208   0.0055   1.0000
  14.000   1.2086   0.08224   0.07947  -0.0243   0.0055   1.0000
  14.250   1.1920   0.08919   0.08656  -0.0286   0.0055   1.0000
  14.500   1.1748   0.09669   0.09421  -0.0335   0.0055   1.0000
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