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GOE 503 AIRFOIL (goe503-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 503 AIRFOIL (goe503-il)
Reynolds number: 200,000
Max Cl/Cd: 68.47 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe503-il-200000.txt
Download as CSV file: xf-goe503-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 503 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.0189   0.09087   0.08752  -0.1079   0.9430   0.0673
  -9.500   0.0015   0.08838   0.08502  -0.1081   0.9344   0.0689
  -9.250  -0.2258   0.03911   0.03509  -0.1384   0.9008   0.0396
  -9.000  -0.2448   0.03309   0.02829  -0.1364   0.8881   0.0402
  -8.750  -0.2291   0.02968   0.02437  -0.1367   0.8823   0.0421
  -8.500  -0.2092   0.02909   0.02379  -0.1356   0.8725   0.0438
  -8.250  -0.1844   0.02701   0.02128  -0.1361   0.8667   0.0469
  -8.000  -0.1743   0.02512   0.01899  -0.1335   0.8563   0.0491
  -7.750  -0.1409   0.02425   0.01809  -0.1349   0.8506   0.0530
  -7.500  -0.1263   0.02305   0.01656  -0.1326   0.8404   0.0576
  -7.250  -0.0929   0.02268   0.01615  -0.1338   0.8343   0.0642
  -7.000  -0.0750   0.02200   0.01539  -0.1320   0.8245   0.0694
  -6.750  -0.0436   0.02172   0.01481  -0.1326   0.8180   0.0764
  -6.500  -0.0238   0.02132   0.01449  -0.1312   0.8081   0.0810
  -6.250   0.0079   0.02106   0.01395  -0.1318   0.8015   0.0873
  -6.000   0.0260   0.02048   0.01330  -0.1300   0.7918   0.0915
  -5.750   0.0577   0.02046   0.01320  -0.1308   0.7852   0.0977
  -5.500   0.0759   0.02012   0.01262  -0.1288   0.7756   0.1025
  -5.250   0.1068   0.01959   0.01207  -0.1295   0.7689   0.1075
  -5.000   0.1266   0.01921   0.01157  -0.1278   0.7596   0.1114
  -4.750   0.1572   0.01873   0.01076  -0.1281   0.7531   0.1155
  -4.500   0.1772   0.01812   0.01017  -0.1266   0.7442   0.1201
  -4.250   0.2069   0.01779   0.00971  -0.1269   0.7374   0.1255
  -4.000   0.2283   0.01754   0.00929  -0.1254   0.7288   0.1308
  -3.750   0.2564   0.01713   0.00889  -0.1255   0.7219   0.1380
  -3.500   0.2793   0.01700   0.00863  -0.1244   0.7143   0.1465
  -3.250   0.3048   0.01681   0.00847  -0.1239   0.7070   0.1552
  -3.000   0.3304   0.01667   0.00824  -0.1233   0.7002   0.1651
  -2.750   0.3529   0.01667   0.00820  -0.1221   0.6926   0.1749
  -2.500   0.3825   0.01658   0.00804  -0.1224   0.6869   0.1856
  -2.250   0.4014   0.01656   0.00799  -0.1206   0.6790   0.1953
  -2.000   0.4280   0.01648   0.00788  -0.1203   0.6728   0.2056
  -1.750   0.4519   0.01641   0.00779  -0.1195   0.6665   0.2162
  -1.500   0.4742   0.01643   0.00774  -0.1183   0.6596   0.2280
  -1.250   0.5027   0.01634   0.00762  -0.1184   0.6544   0.2416
  -1.000   0.5221   0.01630   0.00765  -0.1168   0.6476   0.2535
  -0.750   0.5466   0.01622   0.00755  -0.1161   0.6416   0.2664
  -0.500   0.5756   0.01619   0.00742  -0.1163   0.6368   0.2801
  -0.250   0.5930   0.01614   0.00748  -0.1143   0.6299   0.2909
   0.000   0.6183   0.01607   0.00740  -0.1138   0.6245   0.3036
   0.250   0.6447   0.01604   0.00735  -0.1135   0.6196   0.3181
   0.500   0.6630   0.01604   0.00742  -0.1116   0.6132   0.3320
   0.750   0.6881   0.01598   0.00736  -0.1111   0.6081   0.3484
   1.000   0.7129   0.01593   0.00734  -0.1106   0.6033   0.3677
   1.250   0.7292   0.01588   0.00743  -0.1083   0.5973   0.3913
   1.500   0.7493   0.01566   0.00737  -0.1068   0.5923   0.4357
   1.750   0.9745   0.01535   0.00811  -0.1475   0.5824   0.9996
   2.000   0.9965   0.01547   0.00815  -0.1465   0.5772   1.0000
   2.250   1.0218   0.01561   0.00814  -0.1461   0.5728   1.0000
   2.500   1.0335   0.01580   0.00838  -0.1432   0.5670   1.0000
   2.750   1.0520   0.01595   0.00848  -0.1414   0.5616   1.0000
   3.000   1.0767   0.01610   0.00851  -0.1410   0.5572   1.0000
   3.250   1.0893   0.01634   0.00879  -0.1382   0.5519   1.0000
   3.500   1.1058   0.01651   0.00895  -0.1361   0.5464   1.0000
   3.750   1.1297   0.01668   0.00901  -0.1355   0.5418   1.0000
   4.000   1.1441   0.01694   0.00929  -0.1331   0.5368   1.0000
   4.250   1.1584   0.01716   0.00952  -0.1306   0.5314   1.0000
   4.500   1.1809   0.01733   0.00962  -0.1297   0.5266   1.0000
   4.750   1.1984   0.01760   0.00987  -0.1279   0.5218   1.0000
   5.000   1.2096   0.01784   0.01017  -0.1248   0.5162   1.0000
   5.250   1.2304   0.01803   0.01032  -0.1236   0.5114   1.0000
   5.500   1.2523   0.01830   0.01053  -0.1227   0.5067   1.0000
   5.750   1.2592   0.01857   0.01088  -0.1187   0.5010   1.0000
   6.000   1.2778   0.01873   0.01101  -0.1171   0.4955   1.0000
   6.250   1.2968   0.01896   0.01120  -0.1156   0.4900   1.0000
   6.500   1.3011   0.01917   0.01147  -0.1111   0.4834   1.0000
   6.750   1.3215   0.01930   0.01154  -0.1099   0.4777   1.0000
   7.000   1.3311   0.01959   0.01187  -0.1065   0.4721   1.0000
   7.250   1.3401   0.01986   0.01219  -0.1031   0.4666   1.0000
   7.500   1.3610   0.02007   0.01235  -0.1020   0.4618   1.0000
   7.750   1.3708   0.02038   0.01270  -0.0988   0.4568   1.0000
   8.000   1.3735   0.02065   0.01304  -0.0942   0.4513   1.0000
   8.250   1.3915   0.02086   0.01322  -0.0926   0.4462   1.0000
   8.500   1.4029   0.02119   0.01359  -0.0899   0.4411   1.0000
   8.750   1.4059   0.02155   0.01402  -0.0856   0.4352   1.0000
   9.000   1.4241   0.02179   0.01425  -0.0842   0.4302   1.0000
   9.250   1.4353   0.02221   0.01472  -0.0816   0.4251   1.0000
   9.500   1.4400   0.02267   0.01527  -0.0780   0.4194   1.0000
   9.750   1.4581   0.02291   0.01546  -0.0766   0.4138   1.0000
  10.000   1.4602   0.02348   0.01614  -0.0728   0.4075   1.0000
  10.250   1.4656   0.02392   0.01662  -0.0695   0.4006   1.0000
  10.500   1.4737   0.02441   0.01711  -0.0668   0.3937   1.0000
  10.750   1.4737   0.02511   0.01789  -0.0630   0.3863   1.0000
  11.000   1.4837   0.02564   0.01840  -0.0608   0.3792   1.0000
  11.250   1.4826   0.02660   0.01947  -0.0573   0.3719   1.0000
  11.500   1.4950   0.02715   0.01996  -0.0556   0.3649   1.0000
  11.750   1.4898   0.02843   0.02139  -0.0520   0.3570   1.0000
  12.000   1.5012   0.02910   0.02200  -0.0504   0.3499   1.0000
  12.250   1.4956   0.03064   0.02370  -0.0472   0.3419   1.0000
  12.500   1.5011   0.03169   0.02470  -0.0452   0.3339   1.0000
  12.750   1.4980   0.03337   0.02652  -0.0427   0.3259   1.0000
  13.000   1.5031   0.03461   0.02774  -0.0410   0.3184   1.0000
  13.250   1.4997   0.03654   0.02980  -0.0389   0.3101   1.0000
  13.500   1.5022   0.03811   0.03136  -0.0372   0.3025   1.0000
  13.750   1.4993   0.04022   0.03357  -0.0355   0.2941   1.0000
  14.000   1.4958   0.04244   0.03584  -0.0339   0.2849   1.0000
  14.250   1.4934   0.04467   0.03808  -0.0325   0.2763   1.0000
  14.500   1.4882   0.04730   0.04081  -0.0312   0.2670   1.0000
  14.750   1.4852   0.04975   0.04324  -0.0301   0.2588   1.0000
  15.000   1.4780   0.05281   0.04642  -0.0291   0.2489   1.0000
  15.250   1.4721   0.05580   0.04946  -0.0282   0.2399   1.0000
  15.500   1.4635   0.05911   0.05275  -0.0274   0.2301   1.0000
  15.750   1.4531   0.06284   0.05656  -0.0268   0.2189   1.0000
  16.000   1.4402   0.06692   0.06065  -0.0264   0.2066   1.0000
  16.250   1.4252   0.07137   0.06509  -0.0260   0.1933   1.0000
  16.500   1.4096   0.07596   0.06968  -0.0259   0.1800   1.0000
  16.750   1.3935   0.08075   0.07444  -0.0259   0.1665   1.0000
  17.000   1.3764   0.08578   0.07946  -0.0260   0.1521   1.0000
  17.250   1.3576   0.09111   0.08476  -0.0263   0.1355   1.0000
  17.500   1.3351   0.09703   0.09059  -0.0270   0.1101   1.0000
  17.750   1.3025   0.10446   0.09783  -0.0280   0.0777   1.0000
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