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GOE 368 AIRFOIL (goe368-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 368 AIRFOIL (goe368-il)
Reynolds number: 100,000
Max Cl/Cd: 49.76 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe368-il-100000.txt
Download as CSV file: xf-goe368-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4055   0.10573   0.10101  -0.0019   1.0000   0.0875
  -8.250  -0.4142   0.10498   0.10037  -0.0060   1.0000   0.0911
  -8.000  -0.4274   0.10452   0.10005  -0.0105   1.0000   0.0917
  -7.750  -0.3942   0.09656   0.09201  -0.0052   1.0000   0.0960
  -7.500  -0.3892   0.09382   0.08932  -0.0058   1.0000   0.1005
  -7.250  -0.3987   0.09272   0.08835  -0.0098   1.0000   0.1040
  -7.000  -0.4004   0.09037   0.08607  -0.0185   1.0000   0.1053
  -6.750  -0.3850   0.08487   0.08061  -0.0115   1.0000   0.1075
  -6.500  -0.3750   0.08157   0.07734  -0.0112   1.0000   0.1106
  -6.250  -0.3672   0.07853   0.07431  -0.0141   1.0000   0.1151
  -6.000  -0.3576   0.07534   0.07112  -0.0249   1.0000   0.1192
  -5.750  -0.3475   0.07111   0.06693  -0.0221   1.0000   0.1205
  -5.500  -0.3357   0.06762   0.06347  -0.0218   1.0000   0.1224
  -5.250  -0.3222   0.06415   0.06000  -0.0232   1.0000   0.1246
  -5.000  -0.3064   0.06051   0.05634  -0.0258   1.0000   0.1268
  -4.750  -0.2708   0.04243   0.03743  -0.0431   1.0000   0.0683
  -4.500  -0.2531   0.03953   0.03451  -0.0424   1.0000   0.0647
  -4.250  -0.2264   0.02767   0.02130  -0.0466   1.0000   0.0549
  -4.000  -0.2031   0.02410   0.01709  -0.0463   1.0000   0.0551
  -3.750  -0.1797   0.02138   0.01390  -0.0458   1.0000   0.0571
  -3.500  -0.1563   0.01953   0.01184  -0.0448   1.0000   0.0593
  -3.250  -0.1330   0.01813   0.01025  -0.0438   1.0000   0.0616
  -3.000  -0.1102   0.01703   0.00900  -0.0426   1.0000   0.0658
  -2.750  -0.0889   0.01629   0.00831  -0.0415   1.0000   0.0749
  -2.500  -0.0689   0.01598   0.00811  -0.0402   1.0000   0.0953
  -2.250  -0.0522   0.01683   0.00909  -0.0385   1.0000   0.1514
  -2.000  -0.0014   0.01921   0.01140  -0.0439   0.9834   0.2143
  -1.750   0.0490   0.01961   0.01184  -0.0488   0.9652   0.2569
  -1.500   0.1008   0.01864   0.01068  -0.0534   0.9487   0.2591
  -1.250   0.1513   0.01783   0.00974  -0.0574   0.9311   0.2640
  -1.000   0.1978   0.01713   0.00882  -0.0604   0.9100   0.2684
  -0.750   0.2407   0.01643   0.00798  -0.0624   0.8857   0.2727
  -0.500   0.2773   0.01587   0.00733  -0.0631   0.8571   0.2784
  -0.250   0.3078   0.01558   0.00683  -0.0625   0.8247   0.2852
   0.000   0.3344   0.01529   0.00648  -0.0613   0.7915   0.2933
   0.250   0.3594   0.01508   0.00619  -0.0599   0.7590   0.3044
   0.500   0.3837   0.01487   0.00592  -0.0584   0.7259   0.3179
   0.750   0.4082   0.01468   0.00567  -0.0570   0.6938   0.3344
   1.000   0.4328   0.01454   0.00544  -0.0557   0.6631   0.3571
   1.250   0.4569   0.01432   0.00529  -0.0546   0.6337   0.4026
   1.500   0.4925   0.01310   0.00514  -0.0551   0.6029   1.0000
   1.750   0.5174   0.01342   0.00516  -0.0541   0.5746   1.0000
   2.000   0.5422   0.01370   0.00521  -0.0531   0.5472   1.0000
   2.250   0.5671   0.01397   0.00529  -0.0522   0.5210   1.0000
   2.500   0.5919   0.01426   0.00538  -0.0513   0.4957   1.0000
   2.750   0.6166   0.01462   0.00554  -0.0505   0.4720   1.0000
   3.000   0.6413   0.01504   0.00575  -0.0496   0.4489   1.0000
   3.250   0.6661   0.01554   0.00608  -0.0489   0.4266   1.0000
   3.500   0.6910   0.01609   0.00645  -0.0483   0.4069   1.0000
   3.750   0.7162   0.01669   0.00693  -0.0477   0.3897   1.0000
   4.000   0.7416   0.01727   0.00746  -0.0471   0.3737   1.0000
   4.250   0.7671   0.01788   0.00799  -0.0466   0.3601   1.0000
   4.500   0.7927   0.01847   0.00852  -0.0462   0.3482   1.0000
   4.750   0.8181   0.01905   0.00916  -0.0457   0.3369   1.0000
   5.000   0.8438   0.01969   0.00990  -0.0452   0.3277   1.0000
   5.250   0.8698   0.02036   0.01053  -0.0449   0.3206   1.0000
   5.500   0.8950   0.02105   0.01140  -0.0444   0.3127   1.0000
   5.750   0.9190   0.02128   0.01164  -0.0437   0.2998   1.0000
   6.000   0.9424   0.02138   0.01179  -0.0429   0.2857   1.0000
   6.250   0.9665   0.02164   0.01208  -0.0423   0.2748   1.0000
   6.500   0.9908   0.02194   0.01245  -0.0417   0.2652   1.0000
   6.750   1.0125   0.02181   0.01237  -0.0407   0.2480   1.0000
   7.000   1.0349   0.02184   0.01256  -0.0398   0.2328   1.0000
   7.250   1.0579   0.02204   0.01294  -0.0389   0.2205   1.0000
   7.500   1.0804   0.02210   0.01324  -0.0380   0.2024   1.0000
   7.750   1.1027   0.02216   0.01342  -0.0372   0.1729   1.0000
   8.000   1.1249   0.02275   0.01389  -0.0363   0.1052   1.0000
   8.250   1.1334   0.02562   0.01613  -0.0346   0.0470   1.0000
   8.500   1.1505   0.02719   0.01790  -0.0331   0.0427   1.0000
   8.750   1.1660   0.02882   0.01985  -0.0316   0.0403   1.0000
   9.000   1.1783   0.03063   0.02191  -0.0300   0.0387   1.0000
   9.250   1.1857   0.03272   0.02423  -0.0281   0.0372   1.0000
   9.500   1.1873   0.03508   0.02677  -0.0258   0.0359   1.0000
   9.750   1.1925   0.03696   0.02880  -0.0238   0.0350   1.0000
  10.000   1.1952   0.03886   0.03083  -0.0214   0.0342   1.0000
  10.250   1.1972   0.04086   0.03293  -0.0191   0.0339   1.0000
  10.500   1.2030   0.04294   0.03508  -0.0172   0.0339   1.0000
  10.750   1.2150   0.04510   0.03729  -0.0155   0.0339   1.0000
  11.000   1.2348   0.04755   0.03981  -0.0141   0.0342   1.0000
  11.250   1.2576   0.05070   0.04309  -0.0132   0.0347   1.0000
  11.500   1.2799   0.05494   0.04756  -0.0129   0.0354   1.0000
  11.750   1.2929   0.05845   0.05131  -0.0120   0.0361   1.0000
  12.000   1.2864   0.06050   0.05367  -0.0099   0.0367   1.0000
  12.250   1.2745   0.06334   0.05683  -0.0089   0.0373   1.0000
  12.500   1.2596   0.06718   0.06101  -0.0091   0.0380   1.0000
  12.750   1.2437   0.07181   0.06594  -0.0105   0.0386   1.0000
  13.000   1.2230   0.07732   0.07174  -0.0133   0.0390   1.0000
  13.250   1.2018   0.08355   0.07821  -0.0171   0.0393   1.0000
  13.500   1.1797   0.09054   0.08542  -0.0218   0.0395   1.0000
  13.750   1.1556   0.09850   0.09358  -0.0275   0.0397   1.0000
  14.000   1.1312   0.10713   0.10233  -0.0338   0.0397   1.0000
  14.250   1.1034   0.11721   0.11256  -0.0412   0.0398   1.0000
  14.500   1.0724   0.12912   0.12459  -0.0498   0.0399   1.0000
  14.750   1.0331   0.14498   0.14052  -0.0607   0.0405   1.0000
  15.000   1.0019   0.16075   0.15624  -0.0699   0.0424   1.0000
  15.250   0.9950   0.16930   0.16476  -0.0740   0.0442   1.0000
  15.500   0.9989   0.17387   0.16932  -0.0753   0.0456   1.0000
  15.750   0.9787   0.19091   0.18623  -0.0848   0.0543   1.0000
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