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

GOE 476 AIRFOIL (goe476-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 476 AIRFOIL (goe476-il)
Reynolds number: 500,000
Max Cl/Cd: 101.73 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe476-il-500000-n5.txt
Download as CSV file: xf-goe476-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 476 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
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.7907   0.03838   0.03486  -0.1178   0.9841   0.0390
 -13.500  -0.8027   0.03337   0.02954  -0.1216   0.9721   0.0393
 -13.250  -0.7985   0.03082   0.02678  -0.1220   0.9620   0.0396
 -13.000  -0.7806   0.02873   0.02449  -0.1235   0.9547   0.0400
 -12.750  -0.7612   0.02698   0.02254  -0.1245   0.9462   0.0403
 -12.500  -0.7345   0.02541   0.02076  -0.1264   0.9393   0.0408
 -12.250  -0.7091   0.02410   0.01924  -0.1276   0.9298   0.0412
 -12.000  -0.6794   0.02293   0.01790  -0.1294   0.9204   0.0416
 -11.750  -0.6528   0.02212   0.01702  -0.1300   0.9073   0.0420
 -11.500  -0.6265   0.02141   0.01621  -0.1304   0.8933   0.0424
 -11.250  -0.6023   0.02077   0.01544  -0.1303   0.8782   0.0427
 -11.000  -0.5799   0.02023   0.01477  -0.1297   0.8629   0.0431
 -10.500  -0.5390   0.01920   0.01348  -0.1274   0.8347   0.0439
 -10.250  -0.5188   0.01871   0.01285  -0.1262   0.8232   0.0443
 -10.000  -0.4984   0.01823   0.01223  -0.1250   0.8118   0.0447
  -9.750  -0.4776   0.01777   0.01164  -0.1238   0.8014   0.0452
  -9.250  -0.4346   0.01694   0.01053  -0.1214   0.7809   0.0461
  -9.000  -0.4132   0.01654   0.01000  -0.1203   0.7707   0.0465
  -8.750  -0.3915   0.01612   0.00954  -0.1191   0.7602   0.0471
  -8.500  -0.3692   0.01579   0.00913  -0.1181   0.7508   0.0476
  -8.250  -0.3460   0.01549   0.00876  -0.1171   0.7411   0.0480
  -8.000  -0.3230   0.01521   0.00839  -0.1161   0.7319   0.0485
  -7.750  -0.2996   0.01492   0.00803  -0.1152   0.7221   0.0491
  -7.500  -0.2763   0.01465   0.00766  -0.1142   0.7130   0.0497
  -7.250  -0.2523   0.01437   0.00731  -0.1133   0.7041   0.0503
  -7.000  -0.2287   0.01414   0.00696  -0.1124   0.6954   0.0509
  -6.750  -0.2044   0.01391   0.00664  -0.1115   0.6853   0.0516
  -6.500  -0.1811   0.01366   0.00630  -0.1105   0.6759   0.0523
  -6.250  -0.1572   0.01340   0.00600  -0.1096   0.6671   0.0530
  -6.000  -0.1330   0.01320   0.00575  -0.1088   0.6601   0.0537
  -5.750  -0.1078   0.01300   0.00551  -0.1081   0.6546   0.0544
  -5.500  -0.0826   0.01281   0.00527  -0.1074   0.6489   0.0552
  -5.250  -0.0577   0.01264   0.00504  -0.1067   0.6433   0.0561
  -5.000  -0.0324   0.01248   0.00482  -0.1060   0.6384   0.0569
  -4.750  -0.0065   0.01233   0.00462  -0.1054   0.6338   0.0578
  -4.500   0.0186   0.01211   0.00440  -0.1047   0.6293   0.0589
  -4.250   0.0439   0.01196   0.00423  -0.1041   0.6250   0.0600
  -4.000   0.0693   0.01184   0.00407  -0.1034   0.6207   0.0612
  -3.750   0.0954   0.01170   0.00392  -0.1029   0.6166   0.0624
  -3.500   0.1214   0.01157   0.00377  -0.1023   0.6122   0.0636
  -3.250   0.1471   0.01147   0.00363  -0.1017   0.6079   0.0647
  -3.000   0.1724   0.01134   0.00349  -0.1010   0.6041   0.0665
  -2.750   0.1984   0.01124   0.00338  -0.1005   0.6006   0.0683
  -2.500   0.2247   0.01113   0.00328  -0.1000   0.5970   0.0704
  -2.250   0.2507   0.01104   0.00318  -0.0994   0.5931   0.0724
  -2.000   0.2763   0.01094   0.00309  -0.0988   0.5891   0.0749
  -1.750   0.3019   0.01088   0.00301  -0.0982   0.5851   0.0779
  -1.500   0.3278   0.01081   0.00294  -0.0976   0.5813   0.0813
  -1.250   0.3537   0.01071   0.00288  -0.0971   0.5771   0.0863
  -1.000   0.3793   0.01064   0.00284  -0.0964   0.5727   0.0927
  -0.750   0.4047   0.01059   0.00281  -0.0958   0.5686   0.1007
  -0.250   0.4563   0.01053   0.00281  -0.0946   0.5609   0.1212
   0.000   0.4820   0.01050   0.00283  -0.0940   0.5563   0.1304
   0.250   0.5071   0.01051   0.00282  -0.0933   0.5505   0.1372
   0.500   0.5319   0.01051   0.00283  -0.0925   0.5455   0.1438
   0.750   0.5576   0.01050   0.00284  -0.0919   0.5400   0.1493
   1.000   0.5822   0.01050   0.00285  -0.0911   0.5339   0.1549
   1.250   0.6062   0.01052   0.00286  -0.0902   0.5283   0.1608
   1.500   0.6312   0.01053   0.00288  -0.0895   0.5213   0.1662
   1.750   0.6550   0.01054   0.00290  -0.0885   0.5148   0.1725
   2.000   0.6789   0.01056   0.00294  -0.0876   0.5092   0.1803
   2.250   0.7032   0.01057   0.00298  -0.0868   0.5034   0.1908
   2.500   0.7261   0.01058   0.00304  -0.0857   0.4969   0.2069
   2.750   0.7488   0.01058   0.00310  -0.0846   0.4908   0.2301
   3.250   0.7919   0.01052   0.00326  -0.0819   0.4780   0.3204
   3.500   0.8056   0.01005   0.00341  -0.0792   0.4726   0.5513
   4.000   0.9729   0.00999   0.00426  -0.1033   0.4544   0.9920
   4.250   1.0153   0.01018   0.00440  -0.1065   0.4470   0.9976
   4.500   1.0505   0.01038   0.00455  -0.1082   0.4401   1.0000
   4.750   1.0702   0.01052   0.00468  -0.1065   0.4337   1.0000
   5.000   1.0864   0.01074   0.00483  -0.1041   0.4248   1.0000
   5.250   1.1041   0.01091   0.00498  -0.1020   0.4155   1.0000
   5.500   1.1184   0.01115   0.00516  -0.0993   0.4049   1.0000
   5.750   1.1344   0.01135   0.00533  -0.0969   0.3945   1.0000
   6.000   1.1482   0.01158   0.00552  -0.0941   0.3852   1.0000
   6.250   1.1603   0.01177   0.00569  -0.0909   0.3756   1.0000
   6.500   1.1718   0.01199   0.00588  -0.0877   0.3662   1.0000
   6.750   1.1826   0.01224   0.00609  -0.0844   0.3554   1.0000
   7.000   1.1945   0.01252   0.00633  -0.0813   0.3418   1.0000
   7.250   1.2027   0.01293   0.00665  -0.0777   0.3226   1.0000
   7.500   1.2069   0.01352   0.00710  -0.0735   0.2937   1.0000
   7.750   1.2075   0.01433   0.00774  -0.0690   0.2637   1.0000
   8.250   1.2190   0.01583   0.00904  -0.0621   0.2294   1.0000
   8.500   1.2286   0.01650   0.00968  -0.0594   0.2195   1.0000
   8.750   1.2390   0.01718   0.01033  -0.0569   0.2113   1.0000
   9.000   1.2509   0.01783   0.01098  -0.0548   0.2054   1.0000
   9.250   1.2644   0.01844   0.01159  -0.0530   0.2003   1.0000
   9.500   1.2761   0.01917   0.01233  -0.0510   0.1952   1.0000
   9.750   1.2873   0.01997   0.01313  -0.0491   0.1907   1.0000
  10.000   1.3017   0.02063   0.01382  -0.0476   0.1866   1.0000
  10.250   1.3139   0.02144   0.01464  -0.0460   0.1814   1.0000
  10.500   1.3235   0.02245   0.01566  -0.0442   0.1760   1.0000
  10.750   1.3361   0.02331   0.01654  -0.0428   0.1709   1.0000
  11.000   1.3467   0.02433   0.01756  -0.0413   0.1647   1.0000
  11.250   1.3559   0.02547   0.01871  -0.0398   0.1595   1.0000
  11.500   1.3664   0.02658   0.01984  -0.0384   0.1530   1.0000
  11.750   1.3736   0.02794   0.02118  -0.0369   0.1465   1.0000
  12.000   1.3825   0.02923   0.02248  -0.0357   0.1400   1.0000
  12.250   1.3884   0.03079   0.02403  -0.0343   0.1336   1.0000
  12.500   1.3962   0.03224   0.02550  -0.0331   0.1274   1.0000
  12.750   1.4004   0.03402   0.02728  -0.0318   0.1208   1.0000
  13.000   1.4074   0.03561   0.02889  -0.0308   0.1154   1.0000
  13.250   1.4101   0.03762   0.03089  -0.0297   0.1090   1.0000
  13.500   1.4151   0.03946   0.03275  -0.0287   0.1024   1.0000
  13.750   1.4172   0.04160   0.03489  -0.0277   0.0953   1.0000
  14.000   1.4185   0.04386   0.03714  -0.0267   0.0876   1.0000
  14.250   1.4194   0.04622   0.03949  -0.0259   0.0795   1.0000
  14.500   1.4195   0.04866   0.04193  -0.0251   0.0727   1.0000
  14.750   1.4202   0.05110   0.04437  -0.0244   0.0682   1.0000
  15.000   1.4212   0.05357   0.04686  -0.0238   0.0650   1.0000
  15.250   1.4230   0.05600   0.04932  -0.0233   0.0630   1.0000
  15.500   1.4260   0.05833   0.05170  -0.0228   0.0614   1.0000
  15.750   1.4289   0.06069   0.05412  -0.0224   0.0602   1.0000
  16.000   1.4313   0.06315   0.05664  -0.0221   0.0592   1.0000
  16.250   1.4328   0.06575   0.05929  -0.0219   0.0582   1.0000
  16.500   1.4330   0.06852   0.06210  -0.0217   0.0570   1.0000
  16.750   1.4317   0.07150   0.06514  -0.0216   0.0560   1.0000
  17.000   1.4338   0.07411   0.06781  -0.0215   0.0552   1.0000
  17.250   1.4356   0.07680   0.07058  -0.0216   0.0546   1.0000
  17.500   1.4379   0.07944   0.07329  -0.0216   0.0536   1.0000
  17.750   1.4381   0.08237   0.07629  -0.0218   0.0528   1.0000
  18.000   1.4383   0.08530   0.07927  -0.0220   0.0518   1.0000
  18.250   1.4370   0.08847   0.08252  -0.0223   0.0512   1.0000
  18.500   1.4353   0.09171   0.08581  -0.0226   0.0505   1.0000
<< Back to GOE 476 AIRFOIL (goe476-il)

Polar data table (+)

Polar graphs


<< Back to GOE 476 AIRFOIL (goe476-il)