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GOE 795 AIRFOIL (goe795-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 795 AIRFOIL (goe795-il)
Reynolds number: 50,000
Max Cl/Cd: 37.99 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe795-il-50000.txt
Download as CSV file: xf-goe795-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 795 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4527   0.10789   0.10092  -0.0190   1.0000   0.2141
  -8.500  -0.4328   0.10266   0.09565  -0.0174   1.0000   0.2223
  -8.250  -0.4574   0.10240   0.09558  -0.0189   1.0000   0.2283
  -8.000  -0.4352   0.09723   0.09037  -0.0171   1.0000   0.2391
  -7.750  -0.4333   0.09401   0.08722  -0.0164   1.0000   0.2479
  -7.500  -0.4564   0.09324   0.08664  -0.0162   1.0000   0.2557
  -7.250  -0.4523   0.08996   0.08342  -0.0145   1.0000   0.2690
  -7.000  -0.4545   0.08728   0.08083  -0.0132   1.0000   0.2831
  -6.750  -0.4614   0.08494   0.07860  -0.0124   1.0000   0.2978
  -6.500  -0.4414   0.08081   0.07446  -0.0087   1.0000   0.3183
  -6.250  -0.4486   0.07865   0.07242  -0.0070   1.0000   0.3381
  -6.000  -0.4482   0.07575   0.06961  -0.0048   1.0000   0.3564
  -5.750  -0.4431   0.07297   0.06687  -0.0019   1.0000   0.3780
  -5.500  -0.4404   0.07018   0.06416   0.0013   1.0000   0.4024
  -5.250  -0.4386   0.06763   0.06169   0.0051   1.0000   0.4307
  -4.750  -0.4170   0.04814   0.04058  -0.0325   1.0000   0.1598
  -4.500  -0.4001   0.04348   0.03543  -0.0323   1.0000   0.1442
  -4.250  -0.3839   0.04000   0.03169  -0.0313   1.0000   0.1392
  -4.000  -0.3655   0.03629   0.02727  -0.0304   1.0000   0.1340
  -3.750  -0.3464   0.03350   0.02402  -0.0291   1.0000   0.1346
  -3.500  -0.3267   0.03134   0.02152  -0.0277   1.0000   0.1401
  -3.250  -0.3075   0.02966   0.01953  -0.0263   1.0000   0.1541
  -3.000  -0.2874   0.02822   0.01771  -0.0249   1.0000   0.1723
  -2.750  -0.2662   0.02660   0.01597  -0.0236   1.0000   0.1897
  -2.500  -0.2424   0.02509   0.01427  -0.0226   1.0000   0.2076
  -2.250  -0.2193   0.02395   0.01302  -0.0216   1.0000   0.2416
  -2.000  -0.1923   0.02258   0.01172  -0.0211   1.0000   0.2865
  -1.750  -0.1665   0.02136   0.01080  -0.0207   1.0000   0.3605
  -1.500  -0.0921   0.01799   0.00941  -0.0276   1.0000   1.0000
  -1.250  -0.0744   0.01822   0.00917  -0.0262   1.0000   1.0000
  -1.000  -0.0571   0.01848   0.00909  -0.0249   1.0000   1.0000
  -0.750  -0.0398   0.01877   0.00909  -0.0236   1.0000   1.0000
  -0.500  -0.0225   0.01909   0.00912  -0.0225   1.0000   1.0000
  -0.250  -0.0052   0.01944   0.00926  -0.0213   1.0000   1.0000
   0.000   0.0122   0.01983   0.00945  -0.0203   1.0000   1.0000
   0.250   0.0297   0.02024   0.00969  -0.0194   1.0000   1.0000
   0.500   0.0471   0.02068   0.00999  -0.0185   1.0000   1.0000
   0.750   0.0646   0.02116   0.01032  -0.0176   1.0000   1.0000
   1.000   0.0819   0.02168   0.01073  -0.0169   1.0000   1.0000
   1.250   0.0992   0.02223   0.01119  -0.0162   1.0000   1.0000
   1.500   0.1164   0.02283   0.01171  -0.0155   1.0000   1.0000
   1.750   0.1334   0.02346   0.01229  -0.0150   1.0000   1.0000
   2.000   0.1501   0.02415   0.01293  -0.0144   1.0000   1.0000
   2.250   0.1719   0.02498   0.01374  -0.0151   0.9976   1.0000
   2.500   0.2290   0.02647   0.01525  -0.0225   0.9788   1.0000
   2.750   0.2795   0.02766   0.01652  -0.0282   0.9600   1.0000
   3.000   0.3318   0.02879   0.01773  -0.0340   0.9413   1.0000
   3.250   0.3744   0.02965   0.01871  -0.0379   0.9208   1.0000
   3.500   0.4287   0.03051   0.01977  -0.0434   0.9010   1.0000
   3.750   0.4666   0.03116   0.02059  -0.0458   0.8781   1.0000
   4.000   0.5130   0.03170   0.02135  -0.0493   0.8555   1.0000
   4.250   0.5693   0.03188   0.02187  -0.0538   0.8326   1.0000
   4.500   0.6314   0.03127   0.02162  -0.0578   0.8048   1.0000
   4.750   0.6887   0.03009   0.02081  -0.0599   0.7727   1.0000
   5.000   0.7451   0.02862   0.01979  -0.0611   0.7416   1.0000
   5.250   0.7989   0.02643   0.01795  -0.0603   0.7023   1.0000
   5.500   0.8385   0.02458   0.01626  -0.0574   0.6545   1.0000
   5.750   0.8615   0.02375   0.01550  -0.0533   0.6020   1.0000
   6.000   0.8798   0.02326   0.01500  -0.0488   0.5393   1.0000
   6.250   0.8920   0.02348   0.01486  -0.0439   0.4566   1.0000
   6.500   0.8975   0.02503   0.01555  -0.0386   0.3512   1.0000
   6.750   0.9065   0.02724   0.01706  -0.0349   0.2685   1.0000
   7.000   0.9291   0.02941   0.01880  -0.0334   0.2243   1.0000
   7.250   0.9586   0.03179   0.02105  -0.0330   0.1973   1.0000
   7.500   0.9802   0.03398   0.02337  -0.0316   0.1741   1.0000
   7.750   1.0013   0.03670   0.02616  -0.0303   0.1527   1.0000
   8.000   1.0196   0.03949   0.02895  -0.0288   0.1299   1.0000
   8.250   1.0332   0.04272   0.03250  -0.0264   0.1143   1.0000
   8.500   1.0461   0.04584   0.03582  -0.0242   0.1017   1.0000
   8.750   1.0515   0.04946   0.04014  -0.0209   0.0967   1.0000
   9.000   1.0580   0.05347   0.04459  -0.0182   0.0940   1.0000
   9.250   1.0720   0.05802   0.04916  -0.0170   0.0902   1.0000
   9.500   1.0689   0.06233   0.05389  -0.0141   0.0893   1.0000
   9.750   1.0589   0.06633   0.05836  -0.0109   0.0888   1.0000
  10.000   1.0491   0.07056   0.06290  -0.0084   0.0889   1.0000
  10.250   1.0350   0.07481   0.06742  -0.0059   0.0890   1.0000
  10.500   1.0197   0.07898   0.07177  -0.0038   0.0892   1.0000
  10.750   1.0056   0.08347   0.07636  -0.0021   0.0896   1.0000
  11.000   0.9379   0.09003   0.08325  -0.0036   0.1013   1.0000
  11.250   0.8777   0.10138   0.09466  -0.0135   0.1103   1.0000
  11.500   0.8664   0.10932   0.10255  -0.0173   0.1140   1.0000
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