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GOE 414 AIRFOIL (goe414-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 414 AIRFOIL (goe414-il)
Reynolds number: 500,000
Max Cl/Cd: 97.01 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe414-il-500000-n5.txt
Download as CSV file: xf-goe414-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 414 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.5531   0.06504   0.06246  -0.0891   0.9811   0.0093
 -12.500  -0.6606   0.03520   0.03199  -0.1204   0.9538   0.0085
 -12.250  -0.6619   0.03060   0.02708  -0.1233   0.9445   0.0086
 -12.000  -0.6541   0.02797   0.02423  -0.1237   0.9365   0.0089
 -11.750  -0.6409   0.02614   0.02220  -0.1236   0.9292   0.0091
 -11.500  -0.6245   0.02468   0.02058  -0.1234   0.9223   0.0094
 -11.250  -0.6059   0.02345   0.01917  -0.1231   0.9169   0.0097
 -11.000  -0.5861   0.02237   0.01794  -0.1228   0.9107   0.0101
 -10.750  -0.5654   0.02135   0.01675  -0.1225   0.9056   0.0106
 -10.500  -0.5438   0.02042   0.01565  -0.1222   0.9004   0.0111
 -10.250  -0.5219   0.01952   0.01458  -0.1218   0.8946   0.0115
 -10.000  -0.4998   0.01860   0.01354  -0.1214   0.8892   0.0122
  -9.750  -0.4762   0.01796   0.01281  -0.1211   0.8822   0.0128
  -9.500  -0.4519   0.01737   0.01209  -0.1208   0.8758   0.0135
  -9.250  -0.4274   0.01679   0.01139  -0.1206   0.8689   0.0143
  -9.000  -0.4026   0.01623   0.01068  -0.1203   0.8624   0.0150
  -8.750  -0.3778   0.01568   0.01005  -0.1200   0.8557   0.0160
  -8.500  -0.3517   0.01535   0.00965  -0.1199   0.8488   0.0171
  -8.250  -0.3255   0.01501   0.00922  -0.1198   0.8425   0.0184
  -8.000  -0.2993   0.01465   0.00874  -0.1196   0.8362   0.0196
  -7.750  -0.2732   0.01426   0.00823  -0.1194   0.8300   0.0205
  -7.500  -0.2476   0.01378   0.00770  -0.1192   0.8224   0.0219
  -7.250  -0.2212   0.01350   0.00732  -0.1191   0.8145   0.0233
  -7.000  -0.1947   0.01321   0.00694  -0.1189   0.8058   0.0248
  -6.750  -0.1679   0.01294   0.00656  -0.1188   0.7985   0.0260
  -6.500  -0.1408   0.01273   0.00625  -0.1187   0.7908   0.0268
  -6.250  -0.1153   0.01219   0.00562  -0.1184   0.7829   0.0288
  -6.000  -0.0890   0.01187   0.00522  -0.1183   0.7735   0.0304
  -5.750  -0.0623   0.01161   0.00487  -0.1181   0.7634   0.0320
  -5.500  -0.0356   0.01138   0.00453  -0.1179   0.7525   0.0334
  -5.250  -0.0090   0.01120   0.00423  -0.1177   0.7400   0.0346
  -5.000   0.0174   0.01100   0.00392  -0.1174   0.7263   0.0363
  -4.500   0.0703   0.01063   0.00339  -0.1169   0.6989   0.0418
  -4.250   0.0968   0.01046   0.00319  -0.1167   0.6871   0.0488
  -4.000   0.1233   0.01033   0.00306  -0.1165   0.6761   0.0653
  -3.750   0.1500   0.01027   0.00295  -0.1163   0.6658   0.0753
  -3.500   0.1771   0.01022   0.00284  -0.1162   0.6560   0.0814
  -3.250   0.2041   0.01017   0.00274  -0.1161   0.6473   0.0870
  -3.000   0.2311   0.01016   0.00265  -0.1160   0.6387   0.0908
  -2.750   0.2583   0.01012   0.00256  -0.1159   0.6307   0.0945
  -2.250   0.3123   0.01006   0.00243  -0.1157   0.6145   0.1063
  -1.750   0.3663   0.01000   0.00232  -0.1155   0.5991   0.1201
  -1.500   0.3930   0.00998   0.00228  -0.1153   0.5915   0.1300
  -1.250   0.4202   0.00993   0.00225  -0.1153   0.5837   0.1434
  -1.000   0.4466   0.00990   0.00223  -0.1151   0.5755   0.1632
  -0.750   0.4733   0.00978   0.00222  -0.1151   0.5665   0.2016
  -0.500   0.4994   0.00971   0.00225  -0.1149   0.5571   0.2489
  -0.250   0.5257   0.00970   0.00227  -0.1147   0.5462   0.2791
   0.000   0.5521   0.00972   0.00230  -0.1145   0.5341   0.3028
   0.250   0.5780   0.00975   0.00234  -0.1143   0.5207   0.3266
   0.500   0.6034   0.00981   0.00239  -0.1139   0.5052   0.3523
   0.750   0.6282   0.00988   0.00245  -0.1135   0.4888   0.3797
   1.000   0.6528   0.00997   0.00254  -0.1130   0.4739   0.4108
   1.250   0.6774   0.00999   0.00263  -0.1126   0.4617   0.4610
   1.500   0.6917   0.00912   0.00285  -0.1099   0.4535   0.8384
   2.000   0.7756   0.00935   0.00315  -0.1163   0.4402   1.0000
   2.250   0.8001   0.00948   0.00324  -0.1157   0.4360   1.0000
   2.500   0.8244   0.00962   0.00335  -0.1152   0.4320   1.0000
   2.750   0.8484   0.00978   0.00346  -0.1145   0.4278   1.0000
   3.000   0.8727   0.00994   0.00359  -0.1139   0.4240   1.0000
   3.250   0.8976   0.01007   0.00371  -0.1135   0.4203   1.0000
   3.500   0.9222   0.01022   0.00384  -0.1130   0.4170   1.0000
   3.750   0.9465   0.01039   0.00399  -0.1125   0.4136   1.0000
   4.000   0.9704   0.01059   0.00415  -0.1118   0.4103   1.0000
   4.250   0.9956   0.01072   0.00430  -0.1115   0.4076   1.0000
   4.750   1.0453   0.01101   0.00463  -0.1107   0.4022   1.0000
   5.000   1.0694   0.01120   0.00481  -0.1101   0.3990   1.0000
   5.250   1.0924   0.01142   0.00501  -0.1094   0.3938   1.0000
   5.500   1.1166   0.01157   0.00519  -0.1089   0.3869   1.0000
   5.750   1.1386   0.01182   0.00540  -0.1080   0.3798   1.0000
   6.000   1.1622   0.01198   0.00559  -0.1074   0.3708   1.0000
   6.250   1.1836   0.01221   0.00581  -0.1064   0.3612   1.0000
   6.500   1.2040   0.01245   0.00604  -0.1052   0.3504   1.0000
   6.750   1.2233   0.01274   0.00629  -0.1039   0.3352   1.0000
   7.000   1.2404   0.01314   0.00660  -0.1022   0.3097   1.0000
   7.250   1.2458   0.01415   0.00728  -0.0986   0.2562   1.0000
   7.500   1.2512   0.01526   0.00817  -0.0953   0.2181   1.0000
   7.750   1.2570   0.01641   0.00909  -0.0922   0.1788   1.0000
   8.000   1.2458   0.01859   0.01080  -0.0868   0.0979   1.0000
   8.250   1.2351   0.02085   0.01271  -0.0819   0.0266   1.0000
   8.500   1.2459   0.02185   0.01371  -0.0799   0.0183   1.0000
   8.750   1.2584   0.02276   0.01466  -0.0783   0.0156   1.0000
   9.000   1.2718   0.02364   0.01559  -0.0768   0.0141   1.0000
   9.250   1.2849   0.02456   0.01659  -0.0754   0.0131   1.0000
   9.500   1.2968   0.02558   0.01768  -0.0739   0.0123   1.0000
   9.750   1.3070   0.02676   0.01892  -0.0723   0.0115   1.0000
  10.000   1.3147   0.02816   0.02040  -0.0706   0.0108   1.0000
  10.250   1.3225   0.02960   0.02192  -0.0690   0.0103   1.0000
  10.500   1.3319   0.03095   0.02334  -0.0676   0.0099   1.0000
  10.750   1.3399   0.03245   0.02491  -0.0663   0.0094   1.0000
  11.000   1.3468   0.03409   0.02664  -0.0650   0.0089   1.0000
  11.250   1.3525   0.03589   0.02851  -0.0637   0.0086   1.0000
  11.500   1.3568   0.03787   0.03056  -0.0624   0.0083   1.0000
  11.750   1.3600   0.04005   0.03282  -0.0613   0.0080   1.0000
  12.000   1.3605   0.04258   0.03544  -0.0602   0.0078   1.0000
  12.250   1.3575   0.04557   0.03853  -0.0591   0.0076   1.0000
  12.500   1.3566   0.04846   0.04152  -0.0583   0.0074   1.0000
  12.750   1.3573   0.05125   0.04440  -0.0577   0.0073   1.0000
  13.000   1.3571   0.05420   0.04745  -0.0572   0.0071   1.0000
  13.250   1.3561   0.05728   0.05063  -0.0567   0.0070   1.0000
  13.500   1.3545   0.06050   0.05394  -0.0564   0.0068   1.0000
  13.750   1.3528   0.06378   0.05733  -0.0562   0.0066   1.0000
  14.000   1.3508   0.06716   0.06081  -0.0560   0.0064   1.0000
  14.250   1.3494   0.07049   0.06421  -0.0560   0.0062   1.0000
  14.500   1.3471   0.07398   0.06779  -0.0560   0.0061   1.0000
  14.750   1.3452   0.07747   0.07136  -0.0561   0.0059   1.0000
  15.000   1.3430   0.08106   0.07502  -0.0563   0.0058   1.0000
  15.250   1.3404   0.08472   0.07876  -0.0566   0.0057   1.0000
  15.500   1.3371   0.08849   0.08261  -0.0569   0.0056   1.0000
  15.750   1.3333   0.09236   0.08655  -0.0573   0.0055   1.0000
  16.000   1.3288   0.09632   0.09059  -0.0577   0.0054   1.0000
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