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GOE 497 AIRFOIL (goe497-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 497 AIRFOIL (goe497-il)
Reynolds number: 50,000
Max Cl/Cd: 34.83 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe497-il-50000-n5.txt
Download as CSV file: xf-goe497-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 497 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3579   0.10754   0.10063  -0.0379   1.0000   0.0897
  -8.750  -0.3681   0.10526   0.09843  -0.0365   1.0000   0.0893
  -8.500  -0.3795   0.10302   0.09626  -0.0351   1.0000   0.0889
  -8.250  -0.3873   0.10003   0.09333  -0.0355   0.9982   0.0890
  -8.000  -0.3850   0.09536   0.08866  -0.0403   0.9909   0.0898
  -7.750  -0.3862   0.09015   0.08346  -0.0460   0.9827   0.0907
  -7.500  -0.3857   0.08338   0.07667  -0.0539   0.9735   0.0914
  -7.250  -0.3845   0.07501   0.06825  -0.0637   0.9640   0.0917
  -7.000  -0.3803   0.06322   0.05621  -0.0783   0.9552   0.0925
  -6.750  -0.3576   0.06354   0.05657  -0.0769   0.9491   0.0947
  -6.500  -0.3338   0.05842   0.05124  -0.0843   0.9436   0.0982
  -6.250  -0.3189   0.05009   0.04233  -0.0942   0.9352   0.1014
  -6.000  -0.2854   0.04264   0.03384  -0.1042   0.9305   0.1061
  -5.750  -0.2585   0.04191   0.03314  -0.1049   0.9252   0.1100
  -5.500  -0.2320   0.03996   0.03088  -0.1069   0.9190   0.1154
  -5.250  -0.1972   0.03734   0.02769  -0.1105   0.9147   0.1218
  -5.000  -0.1663   0.03665   0.02696  -0.1118   0.9100   0.1283
  -4.750  -0.1396   0.03509   0.02494  -0.1130   0.9035   0.1364
  -4.500  -0.1086   0.03457   0.02447  -0.1141   0.8985   0.1443
  -4.250  -0.0734   0.03371   0.02340  -0.1162   0.8946   0.1553
  -4.000  -0.0509   0.03313   0.02259  -0.1159   0.8871   0.1662
  -3.750  -0.0188   0.03276   0.02222  -0.1171   0.8821   0.1791
  -3.500   0.0140   0.03240   0.02180  -0.1184   0.8774   0.1937
  -3.250   0.0361   0.03226   0.02162  -0.1179   0.8697   0.2071
  -3.000   0.0712   0.03198   0.02128  -0.1193   0.8647   0.2256
  -2.750   0.0972   0.03184   0.02108  -0.1192   0.8563   0.2425
  -2.500   0.1327   0.03149   0.02063  -0.1205   0.8492   0.2628
  -2.250   0.1618   0.03127   0.02033  -0.1207   0.8404   0.2824
  -2.000   0.1957   0.03098   0.02001  -0.1216   0.8331   0.3023
  -1.750   0.2256   0.03086   0.01987  -0.1218   0.8256   0.3221
  -1.500   0.2542   0.03080   0.01978  -0.1219   0.8179   0.3422
  -1.250   0.2934   0.03056   0.01947  -0.1236   0.8136   0.3669
  -1.000   0.3113   0.03079   0.01969  -0.1221   0.8034   0.3853
  -0.750   0.3474   0.03061   0.01951  -0.1232   0.7984   0.4096
  -0.500   0.3682   0.03081   0.01972  -0.1221   0.7891   0.4299
  -0.250   0.4020   0.03067   0.01953  -0.1229   0.7831   0.4559
   0.000   0.4281   0.03069   0.01959  -0.1225   0.7753   0.4774
   0.250   0.4568   0.03062   0.01955  -0.1224   0.7677   0.5008
   0.500   0.4967   0.03022   0.01917  -0.1239   0.7637   0.5286
   0.750   0.5119   0.03053   0.01955  -0.1221   0.7522   0.5502
   1.000   0.5503   0.03008   0.01919  -0.1232   0.7478   0.5831
   1.250   0.5658   0.03036   0.01961  -0.1213   0.7364   0.6120
   1.500   0.6018   0.02979   0.01926  -0.1219   0.7317   0.6616
   1.750   0.6141   0.02988   0.01967  -0.1191   0.7203   0.7295
   2.000   0.6503   0.02915   0.01912  -0.1195   0.7152   1.0000
   2.250   0.6684   0.02980   0.01964  -0.1184   0.7034   1.0000
   2.500   0.7095   0.02959   0.01927  -0.1201   0.6987   1.0000
   2.750   0.7262   0.03027   0.01987  -0.1187   0.6866   1.0000
   3.000   0.7670   0.03000   0.01950  -0.1202   0.6821   1.0000
   3.250   0.7819   0.03079   0.02025  -0.1185   0.6698   1.0000
   3.500   0.8106   0.03102   0.02043  -0.1184   0.6619   1.0000
   3.750   0.8372   0.03128   0.02067  -0.1181   0.6527   1.0000
   4.000   0.8600   0.03166   0.02103  -0.1172   0.6423   1.0000
   4.250   0.8977   0.03123   0.02056  -0.1177   0.6343   1.0000
   4.500   0.9175   0.03155   0.02087  -0.1162   0.6211   1.0000
   4.750   0.9439   0.03156   0.02086  -0.1155   0.6096   1.0000
   5.000   0.9795   0.03116   0.02045  -0.1157   0.6004   1.0000
   5.250   0.9941   0.03190   0.02123  -0.1139   0.5881   1.0000
   5.500   1.0218   0.03208   0.02143  -0.1135   0.5791   1.0000
   5.750   1.0449   0.03245   0.02184  -0.1125   0.5690   1.0000
   6.000   1.0602   0.03318   0.02263  -0.1108   0.5579   1.0000
   6.250   1.0976   0.03289   0.02236  -0.1114   0.5502   1.0000
   6.500   1.1063   0.03388   0.02346  -0.1089   0.5379   1.0000
   6.750   1.1247   0.03448   0.02412  -0.1074   0.5274   1.0000
   7.000   1.1579   0.03437   0.02405  -0.1076   0.5187   1.0000
   7.250   1.1679   0.03538   0.02516  -0.1053   0.5070   1.0000
   7.500   1.1892   0.03584   0.02571  -0.1041   0.4965   1.0000
   7.750   1.2225   0.03568   0.02560  -0.1042   0.4867   1.0000
   8.000   1.2333   0.03670   0.02673  -0.1020   0.4747   1.0000
   8.250   1.2539   0.03727   0.02739  -0.1008   0.4636   1.0000
   8.500   1.2825   0.03729   0.02743  -0.1002   0.4513   1.0000
   8.750   1.3049   0.03746   0.02760  -0.0989   0.4363   1.0000
   9.000   1.3192   0.03796   0.02809  -0.0967   0.4198   1.0000
   9.250   1.3265   0.03884   0.02903  -0.0939   0.4035   1.0000
   9.500   1.3296   0.04007   0.03033  -0.0911   0.3878   1.0000
   9.750   1.3317   0.04154   0.03191  -0.0884   0.3735   1.0000
  10.000   1.3349   0.04304   0.03351  -0.0860   0.3596   1.0000
  10.250   1.3385   0.04455   0.03512  -0.0838   0.3459   1.0000
  10.500   1.3420   0.04611   0.03677  -0.0817   0.3322   1.0000
  10.750   1.3458   0.04771   0.03847  -0.0798   0.3186   1.0000
  11.000   1.3500   0.04933   0.04014  -0.0780   0.3050   1.0000
  11.250   1.3544   0.05097   0.04180  -0.0763   0.2913   1.0000
  11.500   1.3567   0.05291   0.04380  -0.0748   0.2775   1.0000
  11.750   1.3581   0.05508   0.04601  -0.0733   0.2637   1.0000
  12.000   1.3595   0.05734   0.04831  -0.0720   0.2501   1.0000
  12.250   1.3611   0.05968   0.05067  -0.0708   0.2368   1.0000
  12.500   1.3633   0.06203   0.05302  -0.0697   0.2240   1.0000
  12.750   1.3677   0.06417   0.05510  -0.0686   0.2119   1.0000
  13.000   1.3635   0.06761   0.05873  -0.0680   0.2004   1.0000
  13.250   1.3627   0.07068   0.06188  -0.0674   0.1901   1.0000
  13.500   1.3663   0.07313   0.06431  -0.0667   0.1807   1.0000
  13.750   1.3599   0.07725   0.06866  -0.0668   0.1721   1.0000
  14.000   1.3632   0.07994   0.07135  -0.0664   0.1648   1.0000
  14.250   1.3587   0.08401   0.07565  -0.0667   0.1580   1.0000
  14.500   1.3643   0.08638   0.07800  -0.0664   0.1519   1.0000
  14.750   1.3562   0.09124   0.08312  -0.0672   0.1463   1.0000
  15.000   1.3613   0.09378   0.08568  -0.0671   0.1408   1.0000
  15.250   1.3572   0.09810   0.09017  -0.0679   0.1362   1.0000
  15.500   1.3482   0.10336   0.09565  -0.0694   0.1318   1.0000
  15.750   1.3658   0.10363   0.09575  -0.0683   0.1258   1.0000
  16.000   1.3424   0.11169   0.10417  -0.0716   0.1225   1.0000
  16.250   1.3223   0.11943   0.11216  -0.0750   0.1189   1.0000
  16.500   1.3418   0.11875   0.11131  -0.0737   0.1115   1.0000
  16.750   1.3091   0.12951   0.12240  -0.0794   0.1093   1.0000
  17.000   1.2548   0.14651   0.13971  -0.0894   0.1086   1.0000
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