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

GOE 679 AIRFOIL (goe679-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 679 AIRFOIL (goe679-il)
Reynolds number: 500,000
Max Cl/Cd: 72.43 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe679-il-500000-n5.txt
Download as CSV file: xf-goe679-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 679 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
  ------ -------- --------- --------- -------- -------- --------
 -19.250  -0.4433   0.19246   0.18959  -0.0248   1.0000   0.0237
 -18.750  -0.7019   0.12506   0.12149  -0.0566   1.0000   0.0300
 -18.500  -0.7294   0.11682   0.11309  -0.0607   1.0000   0.0301
 -18.250  -0.7512   0.10983   0.10596  -0.0642   1.0000   0.0303
 -18.000  -0.7658   0.10430   0.10034  -0.0667   1.0000   0.0303
 -17.750  -0.7788   0.09917   0.09512  -0.0690   1.0000   0.0304
 -17.500  -0.7906   0.09437   0.09023  -0.0710   1.0000   0.0305
 -17.250  -0.8009   0.08993   0.08571  -0.0728   1.0000   0.0306
 -17.000  -0.8056   0.08546   0.08117  -0.0756   0.9996   0.0306
 -16.750  -0.8063   0.08085   0.07649  -0.0795   0.9986   0.0308
 -16.500  -0.8049   0.07678   0.07237  -0.0829   0.9975   0.0310
 -16.250  -0.8071   0.07241   0.06795  -0.0865   0.9962   0.0310
 -16.000  -0.8099   0.06798   0.06345  -0.0902   0.9949   0.0312
 -15.750  -0.8150   0.06339   0.05878  -0.0939   0.9938   0.0312
 -15.500  -0.8200   0.05860   0.05392  -0.0980   0.9927   0.0314
 -15.250  -0.8295   0.05371   0.04895  -0.1014   0.9907   0.0315
 -15.000  -0.8348   0.04888   0.04402  -0.1053   0.9884   0.0316
 -14.750  -0.8375   0.04397   0.03900  -0.1100   0.9860   0.0317
 -14.500  -0.8351   0.03947   0.03437  -0.1151   0.9839   0.0319
 -14.250  -0.8283   0.03570   0.03048  -0.1199   0.9821   0.0321
 -14.000  -0.8210   0.03275   0.02741  -0.1231   0.9800   0.0323
 -13.750  -0.8233   0.03053   0.02510  -0.1230   0.9750   0.0324
 -13.500  -0.8139   0.02879   0.02327  -0.1237   0.9719   0.0326
 -13.250  -0.7987   0.02739   0.02179  -0.1245   0.9697   0.0329
 -13.000  -0.7888   0.02622   0.02054  -0.1237   0.9663   0.0330
 -12.750  -0.7842   0.02529   0.01954  -0.1211   0.9602   0.0333
 -12.500  -0.7671   0.02435   0.01853  -0.1207   0.9572   0.0335
 -12.250  -0.7462   0.02349   0.01760  -0.1206   0.9552   0.0337
 -12.000  -0.7483   0.02291   0.01697  -0.1156   0.9466   0.0339
 -11.750  -0.7268   0.02211   0.01611  -0.1152   0.9435   0.0341
 -11.250  -0.6948   0.02076   0.01465  -0.1118   0.9325   0.0345
 -11.000  -0.6743   0.01992   0.01377  -0.1110   0.9284   0.0350
 -10.750  -0.6492   0.01916   0.01297  -0.1110   0.9259   0.0353
 -10.500  -0.6425   0.01868   0.01246  -0.1071   0.9149   0.0356
 -10.250  -0.6161   0.01803   0.01178  -0.1070   0.9110   0.0360
 -10.000  -0.6008   0.01756   0.01127  -0.1047   0.9009   0.0364
  -9.750  -0.5714   0.01697   0.01063  -0.1052   0.8958   0.0369
  -9.500  -0.5432   0.01641   0.01002  -0.1053   0.8855   0.0374
  -9.250  -0.4972   0.01575   0.00927  -0.1091   0.8746   0.0382
  -9.000  -0.4447   0.01510   0.00853  -0.1142   0.8601   0.0392
  -8.750  -0.4001   0.01458   0.00794  -0.1179   0.8465   0.0402
  -8.500  -0.3584   0.01417   0.00745  -0.1209   0.8338   0.0415
  -8.250  -0.3245   0.01387   0.00704  -0.1222   0.8206   0.0427
  -8.000  -0.2979   0.01360   0.00670  -0.1219   0.8078   0.0438
  -7.750  -0.2735   0.01334   0.00637  -0.1212   0.7961   0.0454
  -7.500  -0.2497   0.01314   0.00609  -0.1204   0.7846   0.0474
  -7.250  -0.2281   0.01290   0.00581  -0.1190   0.7752   0.0499
  -6.750  -0.1846   0.01245   0.00530  -0.1164   0.7570   0.0583
  -6.500  -0.1641   0.01221   0.00506  -0.1148   0.7472   0.0656
  -6.250  -0.1431   0.01197   0.00483  -0.1134   0.7386   0.0764
  -6.000  -0.1222   0.01175   0.00465  -0.1119   0.7300   0.0879
  -5.500  -0.0788   0.01147   0.00436  -0.1091   0.7128   0.1062
  -5.250  -0.0571   0.01138   0.00424  -0.1076   0.7032   0.1130
  -5.000  -0.0354   0.01127   0.00413  -0.1062   0.6942   0.1192
  -4.750  -0.0139   0.01121   0.00402  -0.1046   0.6845   0.1244
  -4.500   0.0077   0.01111   0.00392  -0.1031   0.6753   0.1296
  -4.250   0.0284   0.01106   0.00382  -0.1014   0.6643   0.1344
  -4.000   0.0482   0.01099   0.00372  -0.0995   0.6528   0.1387
  -3.750   0.0660   0.01094   0.00362  -0.0972   0.6400   0.1438
  -3.500   0.0853   0.01091   0.00354  -0.0952   0.6264   0.1492
  -3.250   0.1035   0.01084   0.00347  -0.0931   0.6129   0.1563
  -3.000   0.1215   0.01084   0.00340  -0.0908   0.5974   0.1618
  -2.750   0.1387   0.01084   0.00334  -0.0884   0.5804   0.1670
  -2.250   0.1754   0.01089   0.00325  -0.0841   0.5477   0.1780
  -2.000   0.1941   0.01090   0.00323  -0.0820   0.5337   0.1843
  -1.750   0.2129   0.01094   0.00322  -0.0800   0.5204   0.1903
  -1.500   0.2326   0.01100   0.00322  -0.0782   0.5074   0.1954
  -1.250   0.2530   0.01103   0.00323  -0.0765   0.4962   0.2020
  -0.750   0.2946   0.01114   0.00327  -0.0733   0.4762   0.2152
  -0.500   0.3148   0.01120   0.00331  -0.0716   0.4671   0.2237
  -0.250   0.3363   0.01125   0.00334  -0.0702   0.4587   0.2314
   0.000   0.3564   0.01131   0.00340  -0.0685   0.4496   0.2409
   0.250   0.3772   0.01140   0.00345  -0.0669   0.4414   0.2493
   0.500   0.3984   0.01144   0.00351  -0.0655   0.4336   0.2598
   0.750   0.4182   0.01155   0.00358  -0.0637   0.4259   0.2704
   1.000   0.4402   0.01157   0.00364  -0.0625   0.4200   0.2824
   1.250   0.4618   0.01164   0.00371  -0.0611   0.4137   0.2929
   1.500   0.4815   0.01173   0.00380  -0.0594   0.4074   0.3062
   1.750   0.5029   0.01178   0.00388  -0.0580   0.4024   0.3197
   2.250   0.5442   0.01189   0.00406  -0.0550   0.3913   0.3542
   2.750   0.5842   0.01195   0.00428  -0.0518   0.3812   0.4125
   3.000   0.6033   0.01195   0.00440  -0.0500   0.3758   0.4562
   3.250   0.6199   0.01195   0.00455  -0.0478   0.3705   0.5141
   3.500   0.6343   0.01183   0.00471  -0.0451   0.3661   0.6055
   3.750   0.6464   0.01161   0.00487  -0.0418   0.3615   0.7197
   4.250   0.8537   0.01205   0.00578  -0.0742   0.3415   0.9842
   4.500   0.8855   0.01242   0.00609  -0.0752   0.3350   0.9990
   4.750   0.9085   0.01265   0.00627  -0.0745   0.3291   1.0000
   5.000   0.9259   0.01282   0.00641  -0.0724   0.3235   1.0000
   5.250   0.9415   0.01305   0.00660  -0.0701   0.3173   1.0000
   5.500   0.9580   0.01328   0.00679  -0.0680   0.3123   1.0000
   5.750   0.9763   0.01348   0.00698  -0.0663   0.3068   1.0000
   6.000   0.9933   0.01374   0.00720  -0.0643   0.3009   1.0000
   6.250   1.0096   0.01403   0.00745  -0.0623   0.2955   1.0000
   6.500   1.0280   0.01428   0.00769  -0.0607   0.2900   1.0000
   6.750   1.0450   0.01459   0.00797  -0.0588   0.2837   1.0000
   7.000   1.0616   0.01493   0.00827  -0.0570   0.2780   1.0000
   7.250   1.0794   0.01525   0.00857  -0.0554   0.2722   1.0000
   7.500   1.0955   0.01564   0.00893  -0.0535   0.2661   1.0000
   7.750   1.1123   0.01602   0.00929  -0.0519   0.2608   1.0000
   8.000   1.1293   0.01641   0.00966  -0.0503   0.2548   1.0000
   8.250   1.1444   0.01689   0.01010  -0.0484   0.2489   1.0000
   8.500   1.1611   0.01732   0.01053  -0.0469   0.2438   1.0000
   8.750   1.1773   0.01778   0.01098  -0.0453   0.2383   1.0000
   9.000   1.1925   0.01831   0.01149  -0.0436   0.2337   1.0000
   9.250   1.2078   0.01885   0.01202  -0.0420   0.2300   1.0000
   9.500   1.2249   0.01933   0.01251  -0.0407   0.2264   1.0000
   9.750   1.2403   0.01990   0.01308  -0.0393   0.2220   1.0000
  10.000   1.2534   0.02060   0.01376  -0.0376   0.2175   1.0000
  10.250   1.2684   0.02123   0.01440  -0.0362   0.2144   1.0000
  10.500   1.2844   0.02183   0.01502  -0.0349   0.2114   1.0000
  10.750   1.2995   0.02249   0.01570  -0.0337   0.2081   1.0000
  11.000   1.3132   0.02325   0.01647  -0.0323   0.2053   1.0000
  11.250   1.3253   0.02412   0.01734  -0.0309   0.2022   1.0000
  11.500   1.3387   0.02494   0.01818  -0.0296   0.1996   1.0000
  11.750   1.3538   0.02568   0.01896  -0.0286   0.1972   1.0000
  12.000   1.3674   0.02653   0.01985  -0.0275   0.1946   1.0000
  12.250   1.3805   0.02744   0.02078  -0.0263   0.1923   1.0000
  12.500   1.3919   0.02848   0.02184  -0.0252   0.1899   1.0000
  12.750   1.4019   0.02963   0.02301  -0.0240   0.1873   1.0000
  13.000   1.4133   0.03072   0.02413  -0.0229   0.1852   1.0000
  13.250   1.4266   0.03169   0.02516  -0.0221   0.1834   1.0000
  13.500   1.4381   0.03281   0.02632  -0.0211   0.1807   1.0000
  13.750   1.4490   0.03401   0.02756  -0.0202   0.1786   1.0000
  14.000   1.4574   0.03541   0.02899  -0.0193   0.1762   1.0000
  14.250   1.4652   0.03688   0.03049  -0.0183   0.1741   1.0000
  14.500   1.4724   0.03844   0.03208  -0.0175   0.1719   1.0000
  14.750   1.4831   0.03974   0.03345  -0.0168   0.1701   1.0000
  15.000   1.4927   0.04115   0.03492  -0.0162   0.1682   1.0000
  15.250   1.5002   0.04278   0.03660  -0.0155   0.1656   1.0000
  15.500   1.5065   0.04452   0.03839  -0.0149   0.1635   1.0000
  15.750   1.5099   0.04659   0.04049  -0.0142   0.1611   1.0000
  16.000   1.5129   0.04872   0.04266  -0.0137   0.1591   1.0000
  16.250   1.5206   0.05044   0.04446  -0.0133   0.1575   1.0000
  16.500   1.5270   0.05233   0.04641  -0.0130   0.1556   1.0000
  16.750   1.5320   0.05436   0.04851  -0.0127   0.1534   1.0000
  17.000   1.5336   0.05678   0.05099  -0.0124   0.1510   1.0000
  17.250   1.5327   0.05951   0.05376  -0.0123   0.1485   1.0000
  17.500   1.5323   0.06222   0.05652  -0.0122   0.1463   1.0000
  17.750   1.5361   0.06452   0.05890  -0.0122   0.1441   1.0000
  18.000   1.5360   0.06728   0.06173  -0.0122   0.1407   1.0000
  18.250   1.5331   0.07037   0.06487  -0.0124   0.1377   1.0000
  18.500   1.5262   0.07398   0.06853  -0.0127   0.1348   1.0000
  18.750   1.5258   0.07687   0.07150  -0.0130   0.1317   1.0000
  19.000   1.5191   0.08055   0.07522  -0.0135   0.1270   1.0000
  19.250   1.5106   0.08446   0.07918  -0.0141   0.1242   1.0000
<< Back to GOE 679 AIRFOIL (goe679-il)

Polar data table (+)

Polar graphs


<< Back to GOE 679 AIRFOIL (goe679-il)