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GOE 412 AIRFOIL (goe412-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 412 AIRFOIL (goe412-il)
Reynolds number: 500,000
Max Cl/Cd: 116.45 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe412-il-500000.txt
Download as CSV file: xf-goe412-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 412 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2023   0.08359   0.08120  -0.0903   0.9725   0.0404
  -9.500  -0.1899   0.08182   0.07942  -0.0902   0.9648   0.0408
  -9.250  -0.1803   0.08002   0.07762  -0.0899   0.9561   0.0413
  -9.000  -0.1758   0.07798   0.07557  -0.0894   0.9441   0.0420
  -8.750  -0.1731   0.07538   0.07295  -0.0898   0.9311   0.0428
  -8.500  -0.2155   0.05875   0.05625  -0.1106   0.9036   0.0472
  -8.250  -0.2811   0.03319   0.02952  -0.1236   0.8830   0.0406
  -8.000  -0.2607   0.03199   0.02832  -0.1234   0.8738   0.0412
  -7.750  -0.2592   0.02483   0.02036  -0.1228   0.8643   0.0370
  -7.500  -0.2448   0.02117   0.01606  -0.1219   0.8553   0.0362
  -7.250  -0.2226   0.01955   0.01412  -0.1214   0.8482   0.0362
  -7.000  -0.1988   0.01835   0.01268  -0.1210   0.8406   0.0364
  -6.500  -0.1482   0.01663   0.01061  -0.1204   0.8276   0.0373
  -6.250  -0.1222   0.01590   0.00972  -0.1202   0.8213   0.0379
  -6.000  -0.0959   0.01519   0.00886  -0.1200   0.8156   0.0382
  -5.750  -0.0694   0.01455   0.00811  -0.1198   0.8096   0.0385
  -5.500  -0.0426   0.01401   0.00744  -0.1196   0.8042   0.0388
  -5.250  -0.0157   0.01352   0.00686  -0.1194   0.7988   0.0392
  -5.000   0.0114   0.01309   0.00635  -0.1193   0.7932   0.0396
  -4.750   0.0387   0.01274   0.00591  -0.1191   0.7881   0.0399
  -4.500   0.0650   0.01211   0.00523  -0.1189   0.7832   0.0409
  -4.250   0.0919   0.01170   0.00481  -0.1188   0.7778   0.0421
  -4.000   0.1193   0.01142   0.00449  -0.1187   0.7729   0.0431
  -3.750   0.1472   0.01120   0.00420  -0.1187   0.7683   0.0442
  -3.500   0.1748   0.01096   0.00395  -0.1186   0.7632   0.0454
  -3.250   0.2027   0.01077   0.00371  -0.1186   0.7582   0.0467
  -3.000   0.2306   0.01056   0.00347  -0.1186   0.7538   0.0495
  -2.750   0.2586   0.01040   0.00332  -0.1186   0.7489   0.0539
  -2.500   0.2864   0.01019   0.00320  -0.1186   0.7438   0.0687
  -2.250   0.3143   0.01001   0.00309  -0.1186   0.7392   0.0937
  -2.000   0.3425   0.00994   0.00304  -0.1187   0.7347   0.1126
  -1.750   0.3705   0.00986   0.00301  -0.1187   0.7295   0.1277
  -1.500   0.3985   0.00977   0.00294  -0.1187   0.7243   0.1420
  -1.250   0.4266   0.00971   0.00286  -0.1188   0.7190   0.1577
  -1.000   0.4541   0.00957   0.00280  -0.1187   0.7127   0.1763
  -0.750   0.4813   0.00937   0.00274  -0.1187   0.7063   0.2263
  -0.500   0.5084   0.00920   0.00274  -0.1186   0.6995   0.2953
  -0.250   0.5354   0.00903   0.00271  -0.1185   0.6925   0.3447
   0.000   0.5623   0.00884   0.00269  -0.1185   0.6866   0.4164
   0.250   0.5862   0.00832   0.00274  -0.1179   0.6797   0.6033
   0.500   0.6235   0.00755   0.00288  -0.1193   0.6733   0.9709
   0.750   0.6781   0.00760   0.00288  -0.1252   0.6667   1.0000
   1.000   0.7036   0.00766   0.00288  -0.1247   0.6603   1.0000
   1.250   0.7294   0.00775   0.00288  -0.1243   0.6546   1.0000
   1.500   0.7549   0.00780   0.00291  -0.1238   0.6481   1.0000
   1.750   0.7804   0.00788   0.00293  -0.1233   0.6420   1.0000
   2.000   0.8059   0.00796   0.00298  -0.1228   0.6356   1.0000
   2.250   0.8311   0.00804   0.00301  -0.1223   0.6280   1.0000
   2.500   0.8564   0.00813   0.00306  -0.1218   0.6206   1.0000
   2.750   0.8818   0.00822   0.00312  -0.1213   0.6129   1.0000
   3.000   0.9072   0.00833   0.00319  -0.1208   0.6061   1.0000
   3.250   0.9326   0.00842   0.00327  -0.1203   0.5979   1.0000
   3.500   0.9577   0.00855   0.00335  -0.1198   0.5900   1.0000
   3.750   0.9829   0.00866   0.00345  -0.1193   0.5810   1.0000
   4.000   1.0077   0.00879   0.00354  -0.1188   0.5717   1.0000
   4.250   1.0316   0.00896   0.00365  -0.1180   0.5597   1.0000
   4.500   1.0554   0.00911   0.00377  -0.1173   0.5460   1.0000
   4.750   1.0790   0.00928   0.00391  -0.1165   0.5323   1.0000
   5.000   1.1028   0.00947   0.00406  -0.1158   0.5199   1.0000
   5.250   1.1261   0.00968   0.00423  -0.1150   0.5074   1.0000
   5.500   1.1487   0.00991   0.00442  -0.1141   0.4938   1.0000
   5.750   1.1708   0.01016   0.00463  -0.1131   0.4791   1.0000
   6.000   1.1923   0.01044   0.00485  -0.1120   0.4633   1.0000
   6.250   1.2131   0.01074   0.00510  -0.1108   0.4461   1.0000
   6.500   1.2329   0.01108   0.00538  -0.1094   0.4279   1.0000
   6.750   1.2518   0.01146   0.00569  -0.1079   0.4092   1.0000
   7.000   1.2693   0.01187   0.00603  -0.1062   0.3905   1.0000
   7.500   1.2977   0.01285   0.00684  -0.1015   0.3504   1.0000
   7.750   1.3107   0.01342   0.00732  -0.0990   0.3293   1.0000
   8.000   1.3235   0.01405   0.00785  -0.0967   0.3094   1.0000
   8.250   1.3368   0.01468   0.00841  -0.0945   0.2909   1.0000
   8.500   1.3498   0.01536   0.00900  -0.0923   0.2691   1.0000
   8.750   1.3606   0.01617   0.00971  -0.0899   0.2466   1.0000
   9.000   1.3723   0.01697   0.01042  -0.0877   0.2273   1.0000
   9.250   1.3841   0.01780   0.01118  -0.0856   0.2117   1.0000
   9.500   1.3960   0.01865   0.01198  -0.0836   0.2001   1.0000
   9.750   1.4086   0.01947   0.01279  -0.0818   0.1909   1.0000
  10.000   1.4214   0.02032   0.01363  -0.0801   0.1835   1.0000
  10.250   1.4341   0.02119   0.01451  -0.0784   0.1768   1.0000
  10.500   1.4460   0.02214   0.01547  -0.0768   0.1708   1.0000
  10.750   1.4597   0.02300   0.01636  -0.0754   0.1643   1.0000
  11.250   1.4845   0.02498   0.01839  -0.0726   0.1507   1.0000
  11.500   1.4944   0.02618   0.01958  -0.0710   0.1414   1.0000
  11.750   1.5054   0.02733   0.02071  -0.0696   0.1271   1.0000
  12.000   1.5019   0.02962   0.02272  -0.0671   0.0891   1.0000
  12.250   1.5009   0.03178   0.02483  -0.0649   0.0765   1.0000
  12.500   1.5028   0.03377   0.02683  -0.0631   0.0662   1.0000
  12.750   1.5003   0.03622   0.02920  -0.0611   0.0484   1.0000
  13.000   1.4920   0.03924   0.03206  -0.0589   0.0308   1.0000
  13.250   1.4908   0.04177   0.03459  -0.0573   0.0259   1.0000
  13.500   1.4935   0.04399   0.03688  -0.0561   0.0239   1.0000
  13.750   1.4940   0.04647   0.03942  -0.0549   0.0224   1.0000
  14.000   1.4947   0.04901   0.04205  -0.0538   0.0214   1.0000
  14.250   1.4970   0.05146   0.04459  -0.0530   0.0206   1.0000
  14.500   1.4979   0.05410   0.04732  -0.0522   0.0199   1.0000
  14.750   1.4968   0.05701   0.05032  -0.0515   0.0193   1.0000
  15.000   1.4930   0.06032   0.05371  -0.0509   0.0187   1.0000
  15.250   1.4855   0.06418   0.05766  -0.0504   0.0182   1.0000
  15.500   1.4821   0.06764   0.06122  -0.0501   0.0178   1.0000
  15.750   1.4804   0.07091   0.06461  -0.0499   0.0174   1.0000
  16.000   1.4771   0.07447   0.06827  -0.0498   0.0171   1.0000
  16.250   1.4727   0.07824   0.07214  -0.0499   0.0168   1.0000
  16.500   1.4674   0.08219   0.07620  -0.0501   0.0165   1.0000
  16.750   1.4614   0.08628   0.08038  -0.0505   0.0162   1.0000
  17.000   1.4547   0.09053   0.08473  -0.0510   0.0159   1.0000
  17.250   1.4472   0.09496   0.08925  -0.0516   0.0157   1.0000
  17.500   1.4393   0.09952   0.09389  -0.0524   0.0155   1.0000
  17.750   1.4305   0.10422   0.09868  -0.0533   0.0153   1.0000
  18.000   1.4213   0.10896   0.10350  -0.0543   0.0151   1.0000
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