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GOE 363 AIRFOIL (goe363-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 363 AIRFOIL (goe363-il)
Reynolds number: 1,000,000
Max Cl/Cd: 110.52 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe363-il-1000000.txt
Download as CSV file: xf-goe363-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 363 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2672   0.11300   0.11142  -0.0379   1.0000   0.0142
 -10.500  -0.2615   0.10917   0.10761  -0.0398   0.9986   0.0142
  -9.750  -0.4516   0.02464   0.02192  -0.1133   0.9180   0.0138
  -9.500  -0.4312   0.02229   0.01924  -0.1140   0.9072   0.0141
  -9.250  -0.4132   0.01917   0.01569  -0.1147   0.8963   0.0147
  -9.000  -0.3864   0.01897   0.01546  -0.1146   0.8881   0.0151
  -8.750  -0.3590   0.01903   0.01550  -0.1144   0.8807   0.0154
  -8.500  -0.3319   0.01882   0.01523  -0.1143   0.8731   0.0158
  -8.250  -0.3057   0.01831   0.01459  -0.1142   0.8660   0.0163
  -8.000  -0.2799   0.01738   0.01347  -0.1142   0.8599   0.0170
  -7.750  -0.2534   0.01669   0.01259  -0.1142   0.8541   0.0175
  -7.500  -0.2291   0.01520   0.01082  -0.1142   0.8486   0.0182
  -7.250  -0.2017   0.01490   0.01050  -0.1141   0.8435   0.0187
  -7.000  -0.1740   0.01471   0.01026  -0.1140   0.8381   0.0192
  -6.750  -0.1467   0.01442   0.00987  -0.1139   0.8322   0.0198
  -6.500  -0.1191   0.01405   0.00942  -0.1138   0.8265   0.0206
  -6.250  -0.0913   0.01384   0.00908  -0.1137   0.8207   0.0214
  -6.000  -0.0642   0.01316   0.00823  -0.1135   0.8154   0.0222
  -5.750  -0.0375   0.01234   0.00736  -0.1135   0.8097   0.0230
  -5.500  -0.0098   0.01208   0.00703  -0.1133   0.8043   0.0237
  -5.250   0.0181   0.01177   0.00667  -0.1132   0.7985   0.0245
  -5.000   0.0460   0.01152   0.00635  -0.1131   0.7916   0.0255
  -4.750   0.0740   0.01133   0.00607  -0.1129   0.7852   0.0263
  -4.500   0.1025   0.01118   0.00586  -0.1128   0.7789   0.0268
  -4.250   0.1290   0.01014   0.00470  -0.1126   0.7725   0.0279
  -4.000   0.1569   0.00978   0.00433  -0.1125   0.7651   0.0290
  -3.750   0.1846   0.00953   0.00403  -0.1123   0.7564   0.0299
  -3.500   0.2127   0.00925   0.00371  -0.1122   0.7468   0.0308
  -3.250   0.2406   0.00902   0.00341  -0.1120   0.7376   0.0316
  -3.000   0.2687   0.00883   0.00317  -0.1118   0.7270   0.0324
  -2.750   0.2966   0.00871   0.00300  -0.1117   0.7124   0.0330
  -2.500   0.3237   0.00842   0.00259  -0.1113   0.6919   0.0338
  -2.250   0.3503   0.00824   0.00226  -0.1109   0.6637   0.0351
  -2.000   0.3767   0.00821   0.00208  -0.1105   0.6291   0.0364
  -1.750   0.4026   0.00828   0.00198  -0.1100   0.5913   0.0377
  -1.500   0.4290   0.00835   0.00191  -0.1096   0.5625   0.0393
  -1.000   0.4830   0.00844   0.00177  -0.1090   0.5241   0.0434
  -0.750   0.5103   0.00844   0.00173  -0.1087   0.5084   0.0499
  -0.250   0.5646   0.00836   0.00181  -0.1084   0.4783   0.1390
   0.000   0.5921   0.00844   0.00184  -0.1083   0.4624   0.1482
   0.250   0.6193   0.00854   0.00187  -0.1081   0.4435   0.1553
   0.500   0.6457   0.00871   0.00192  -0.1078   0.4128   0.1624
   0.750   0.6706   0.00902   0.00202  -0.1073   0.3661   0.1694
   1.000   0.6957   0.00932   0.00215  -0.1068   0.3301   0.1779
   1.250   0.7216   0.00951   0.00227  -0.1065   0.3074   0.1945
   1.500   0.7479   0.00957   0.00241  -0.1063   0.2915   0.2568
   1.750   0.7743   0.00958   0.00255  -0.1061   0.2790   0.3436
   2.000   0.7995   0.00834   0.00279  -0.1058   0.2700   1.0000
   2.250   0.8261   0.00854   0.00290  -0.1056   0.2615   1.0000
   2.500   0.8531   0.00869   0.00299  -0.1054   0.2554   1.0000
   2.750   0.8797   0.00888   0.00311  -0.1051   0.2491   1.0000
   3.000   0.9066   0.00903   0.00322  -0.1049   0.2447   1.0000
   3.250   0.9336   0.00918   0.00333  -0.1047   0.2407   1.0000
   3.500   0.9602   0.00936   0.00346  -0.1045   0.2366   1.0000
   3.750   0.9866   0.00955   0.00361  -0.1043   0.2319   1.0000
   4.000   1.0136   0.00968   0.00373  -0.1041   0.2293   1.0000
   4.250   1.0403   0.00983   0.00386  -0.1039   0.2264   1.0000
   4.500   1.0667   0.01001   0.00401  -0.1037   0.2233   1.0000
   4.750   1.0928   0.01021   0.00418  -0.1034   0.2199   1.0000
   5.000   1.1190   0.01040   0.00435  -0.1032   0.2166   1.0000
   5.250   1.1456   0.01053   0.00449  -0.1030   0.2144   1.0000
   5.500   1.1718   0.01070   0.00465  -0.1028   0.2105   1.0000
   5.750   1.1973   0.01093   0.00483  -0.1024   0.2052   1.0000
   6.000   1.2231   0.01112   0.00501  -0.1022   0.2004   1.0000
   6.250   1.2489   0.01130   0.00518  -0.1019   0.1951   1.0000
   6.500   1.2737   0.01157   0.00540  -0.1015   0.1885   1.0000
   6.750   1.2990   0.01177   0.00558  -0.1012   0.1812   1.0000
   7.000   1.3227   0.01210   0.00583  -0.1006   0.1672   1.0000
   7.250   1.3426   0.01272   0.00625  -0.0995   0.1395   1.0000
   7.500   1.3629   0.01329   0.00671  -0.0985   0.1258   1.0000
   7.750   1.3847   0.01372   0.00710  -0.0976   0.1188   1.0000
   8.000   1.4058   0.01418   0.00752  -0.0967   0.1124   1.0000
   8.250   1.4283   0.01452   0.00786  -0.0960   0.1082   1.0000
   8.500   1.4484   0.01502   0.00831  -0.0949   0.1012   1.0000
   8.750   1.4686   0.01548   0.00873  -0.0939   0.0908   1.0000
   9.000   1.4594   0.01781   0.01062  -0.0884   0.0190   1.0000
   9.250   1.4744   0.01849   0.01132  -0.0865   0.0149   1.0000
   9.500   1.4912   0.01904   0.01192  -0.0850   0.0138   1.0000
   9.750   1.5070   0.01966   0.01260  -0.0834   0.0130   1.0000
  10.000   1.5212   0.02039   0.01338  -0.0816   0.0123   1.0000
  10.250   1.5332   0.02129   0.01436  -0.0796   0.0115   1.0000
  10.500   1.5458   0.02215   0.01529  -0.0778   0.0110   1.0000
  10.750   1.5595   0.02295   0.01614  -0.0763   0.0106   1.0000
  11.000   1.5719   0.02385   0.01710  -0.0746   0.0102   1.0000
  11.250   1.5830   0.02488   0.01818  -0.0730   0.0098   1.0000
  11.500   1.5928   0.02603   0.01940  -0.0713   0.0094   1.0000
  11.750   1.6003   0.02739   0.02084  -0.0695   0.0091   1.0000
  12.000   1.6023   0.02926   0.02282  -0.0674   0.0087   1.0000
  12.250   1.6033   0.03129   0.02497  -0.0654   0.0085   1.0000
  12.500   1.6111   0.03279   0.02654  -0.0642   0.0084   1.0000
  12.750   1.6167   0.03452   0.02835  -0.0629   0.0082   1.0000
  13.000   1.6203   0.03650   0.03043  -0.0617   0.0080   1.0000
  13.250   1.6219   0.03873   0.03274  -0.0605   0.0078   1.0000
  13.500   1.6225   0.04113   0.03524  -0.0594   0.0076   1.0000
  13.750   1.6216   0.04380   0.03801  -0.0586   0.0074   1.0000
  14.000   1.6200   0.04666   0.04096  -0.0580   0.0073   1.0000
  14.250   1.6166   0.04988   0.04427  -0.0576   0.0071   1.0000
  14.500   1.6112   0.05353   0.04803  -0.0576   0.0070   1.0000
  14.750   1.6031   0.05774   0.05236  -0.0579   0.0069   1.0000
  15.000   1.5918   0.06260   0.05733  -0.0586   0.0068   1.0000
  15.250   1.5775   0.06812   0.06299  -0.0597   0.0067   1.0000
  15.500   1.5605   0.07422   0.06923  -0.0611   0.0067   1.0000
  15.750   1.5414   0.08070   0.07584  -0.0628   0.0067   1.0000
  16.000   1.5197   0.08775   0.08304  -0.0648   0.0066   1.0000
  16.250   1.4979   0.09497   0.09040  -0.0669   0.0066   1.0000
  16.500   1.4751   0.10249   0.09806  -0.0693   0.0066   1.0000
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