Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 769 AIRFOIL (goe769-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 769 AIRFOIL (goe769-il)
Reynolds number: 500,000
Max Cl/Cd: 85.24 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe769-il-500000-n5.txt
Download as CSV file: xf-goe769-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 769 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7105   0.03771   0.03423  -0.0721   1.0000   0.0256
 -11.000  -0.7210   0.03328   0.02947  -0.0725   0.9994   0.0256
 -10.750  -0.6993   0.02987   0.02579  -0.0761   0.9774   0.0257
 -10.500  -0.6594   0.02736   0.02306  -0.0813   0.9424   0.0259
 -10.250  -0.6212   0.02559   0.02101  -0.0850   0.8832   0.0261
 -10.000  -0.6032   0.02461   0.01972  -0.0839   0.8290   0.0263
  -9.750  -0.5854   0.02375   0.01862  -0.0826   0.7923   0.0264
  -9.500  -0.5663   0.02289   0.01753  -0.0814   0.7639   0.0265
  -9.250  -0.5459   0.02208   0.01653  -0.0804   0.7412   0.0267
  -9.000  -0.5246   0.02129   0.01555  -0.0795   0.7221   0.0269
  -8.750  -0.5024   0.02056   0.01465  -0.0786   0.7060   0.0271
  -8.500  -0.4795   0.01988   0.01381  -0.0778   0.6915   0.0273
  -8.250  -0.4558   0.01924   0.01303  -0.0770   0.6784   0.0276
  -8.000  -0.4318   0.01863   0.01226  -0.0763   0.6671   0.0279
  -7.750  -0.4073   0.01803   0.01152  -0.0756   0.6564   0.0281
  -7.500  -0.3825   0.01746   0.01080  -0.0749   0.6472   0.0284
  -7.250  -0.3573   0.01692   0.01013  -0.0742   0.6373   0.0286
  -7.000  -0.3318   0.01643   0.00951  -0.0735   0.6283   0.0288
  -6.750  -0.3058   0.01598   0.00895  -0.0729   0.6193   0.0290
  -6.500  -0.2803   0.01550   0.00837  -0.0723   0.6110   0.0292
  -6.250  -0.2542   0.01502   0.00786  -0.0717   0.6033   0.0295
  -6.000  -0.2279   0.01464   0.00742  -0.0711   0.5944   0.0298
  -5.750  -0.2014   0.01431   0.00703  -0.0706   0.5856   0.0301
  -5.500  -0.1746   0.01400   0.00666  -0.0700   0.5758   0.0305
  -5.250  -0.1478   0.01371   0.00631  -0.0695   0.5671   0.0309
  -5.000  -0.1207   0.01342   0.00597  -0.0690   0.5577   0.0313
  -4.750  -0.0938   0.01318   0.00564  -0.0684   0.5484   0.0317
  -4.500  -0.0665   0.01292   0.00533  -0.0679   0.5379   0.0322
  -4.250  -0.0394   0.01272   0.00505  -0.0674   0.5266   0.0326
  -4.000  -0.0124   0.01248   0.00476  -0.0669   0.5140   0.0332
  -3.750   0.0147   0.01229   0.00452  -0.0664   0.5002   0.0339
  -3.500   0.0417   0.01216   0.00431  -0.0659   0.4836   0.0347
  -3.250   0.0687   0.01205   0.00411  -0.0653   0.4668   0.0356
  -3.000   0.0958   0.01195   0.00392  -0.0648   0.4532   0.0365
  -2.750   0.1231   0.01182   0.00374  -0.0643   0.4412   0.0374
  -2.500   0.1504   0.01171   0.00359  -0.0638   0.4309   0.0386
  -2.250   0.1778   0.01163   0.00346  -0.0634   0.4211   0.0401
  -2.000   0.2052   0.01155   0.00334  -0.0629   0.4122   0.0418
  -1.750   0.2326   0.01147   0.00324  -0.0625   0.4024   0.0443
  -1.500   0.2600   0.01141   0.00315  -0.0620   0.3945   0.0477
  -1.250   0.2876   0.01134   0.00308  -0.0616   0.3867   0.0527
  -0.750   0.3425   0.01127   0.00300  -0.0608   0.3715   0.0670
  -0.500   0.3699   0.01127   0.00299  -0.0603   0.3634   0.0745
  -0.250   0.3974   0.01127   0.00299  -0.0599   0.3573   0.0816
   0.000   0.4251   0.01126   0.00299  -0.0596   0.3506   0.0887
   0.250   0.4524   0.01130   0.00300  -0.0591   0.3432   0.0958
   0.500   0.4799   0.01131   0.00301  -0.0587   0.3366   0.1031
   0.750   0.5073   0.01133   0.00303  -0.0584   0.3295   0.1105
   1.000   0.5343   0.01138   0.00307  -0.0579   0.3230   0.1206
   1.250   0.5618   0.01138   0.00311  -0.0575   0.3171   0.1330
   1.500   0.5888   0.01142   0.00315  -0.0571   0.3098   0.1462
   1.750   0.6157   0.01145   0.00320  -0.0567   0.3031   0.1634
   2.250   0.6686   0.01142   0.00337  -0.0558   0.2888   0.2547
   2.500   0.6949   0.01133   0.00346  -0.0553   0.2826   0.3258
   2.750   0.7190   0.01109   0.00358  -0.0546   0.2749   0.4803
   3.500   0.8307   0.01053   0.00406  -0.0599   0.2504   1.0000
   3.750   0.8555   0.01074   0.00419  -0.0591   0.2437   1.0000
   4.000   0.8802   0.01095   0.00433  -0.0583   0.2377   1.0000
   4.250   0.9052   0.01115   0.00448  -0.0575   0.2320   1.0000
   4.500   0.9297   0.01139   0.00465  -0.0567   0.2267   1.0000
   4.750   0.9545   0.01160   0.00482  -0.0560   0.2226   1.0000
   5.000   0.9795   0.01181   0.00499  -0.0553   0.2183   1.0000
   5.250   1.0040   0.01205   0.00519  -0.0545   0.2139   1.0000
   5.500   1.0279   0.01233   0.00541  -0.0537   0.2097   1.0000
   5.750   1.0529   0.01253   0.00560  -0.0530   0.2070   1.0000
   6.000   1.0776   0.01275   0.00581  -0.0523   0.2039   1.0000
   6.250   1.1018   0.01300   0.00603  -0.0516   0.2005   1.0000
   6.500   1.1254   0.01329   0.00628  -0.0508   0.1971   1.0000
   6.750   1.1491   0.01357   0.00654  -0.0500   0.1942   1.0000
   7.000   1.1734   0.01380   0.00677  -0.0492   0.1918   1.0000
   7.250   1.1973   0.01405   0.00702  -0.0485   0.1892   1.0000
   7.500   1.2206   0.01432   0.00729  -0.0477   0.1865   1.0000
   7.750   1.2431   0.01464   0.00759  -0.0468   0.1838   1.0000
   8.000   1.2648   0.01500   0.00792  -0.0458   0.1809   1.0000
   8.250   1.2881   0.01525   0.00819  -0.0450   0.1789   1.0000
   8.500   1.3106   0.01553   0.00849  -0.0441   0.1766   1.0000
   8.750   1.3325   0.01584   0.00880  -0.0431   0.1743   1.0000
   9.000   1.3534   0.01618   0.00915  -0.0420   0.1720   1.0000
   9.250   1.3733   0.01656   0.00952  -0.0408   0.1698   1.0000
   9.500   1.3918   0.01699   0.00994  -0.0394   0.1675   1.0000
   9.750   1.4121   0.01730   0.01029  -0.0383   0.1658   1.0000
  10.000   1.4303   0.01764   0.01067  -0.0368   0.1638   1.0000
  10.250   1.4465   0.01802   0.01107  -0.0350   0.1617   1.0000
  10.500   1.4613   0.01846   0.01152  -0.0331   0.1598   1.0000
  10.750   1.4751   0.01895   0.01203  -0.0311   0.1579   1.0000
  11.000   1.4876   0.01954   0.01263  -0.0291   0.1561   1.0000
  11.250   1.5006   0.02013   0.01325  -0.0274   0.1545   1.0000
  11.500   1.5153   0.02069   0.01386  -0.0259   0.1531   1.0000
  11.750   1.5291   0.02132   0.01454  -0.0244   0.1515   1.0000
  12.000   1.5420   0.02204   0.01531  -0.0230   0.1498   1.0000
  12.250   1.5536   0.02288   0.01619  -0.0217   0.1479   1.0000
  12.500   1.5638   0.02387   0.01721  -0.0204   0.1462   1.0000
  12.750   1.5726   0.02503   0.01840  -0.0193   0.1445   1.0000
  13.000   1.5805   0.02634   0.01974  -0.0182   0.1430   1.0000
  13.250   1.5921   0.02744   0.02092  -0.0175   0.1419   1.0000
  13.500   1.6026   0.02868   0.02223  -0.0169   0.1405   1.0000
  13.750   1.6120   0.03007   0.02368  -0.0163   0.1391   1.0000
  14.000   1.6203   0.03158   0.02526  -0.0158   0.1377   1.0000
  14.250   1.6269   0.03331   0.02703  -0.0154   0.1362   1.0000
  14.500   1.6318   0.03523   0.02901  -0.0151   0.1347   1.0000
  14.750   1.6348   0.03738   0.03120  -0.0149   0.1333   1.0000
  15.000   1.6363   0.03969   0.03356  -0.0147   0.1319   1.0000
  15.250   1.6421   0.04162   0.03558  -0.0146   0.1309   1.0000
  15.500   1.6466   0.04369   0.03774  -0.0146   0.1298   1.0000
  15.750   1.6496   0.04595   0.04007  -0.0146   0.1283   1.0000
  16.000   1.6510   0.04842   0.04262  -0.0147   0.1270   1.0000
  16.250   1.6504   0.05118   0.04544  -0.0150   0.1255   1.0000
  16.500   1.6485   0.05415   0.04847  -0.0154   0.1242   1.0000
  16.750   1.6443   0.05745   0.05183  -0.0160   0.1227   1.0000
  17.000   1.6398   0.06087   0.05529  -0.0166   0.1212   1.0000
  17.250   1.6408   0.06367   0.05820  -0.0172   0.1201   1.0000
  17.500   1.6395   0.06685   0.06147  -0.0180   0.1185   1.0000
  17.750   1.6369   0.07021   0.06492  -0.0188   0.1173   1.0000
  18.000   1.6321   0.07393   0.06870  -0.0199   0.1155   1.0000
  18.250   1.6274   0.07763   0.07248  -0.0210   0.1145   1.0000
  18.500   1.6197   0.08183   0.07673  -0.0223   0.1131   1.0000
  18.750   1.6121   0.08603   0.08098  -0.0237   0.1118   1.0000
  19.000   1.6094   0.08958   0.08463  -0.0249   0.1109   1.0000
<< Back to GOE 769 AIRFOIL (goe769-il)

Polar data table (+)

Polar graphs


<< Back to GOE 769 AIRFOIL (goe769-il)