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GOE 553 AIRFOIL (goe553-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 553 AIRFOIL (goe553-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.56 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe553-il-1000000-n5.txt
Download as CSV file: xf-goe553-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 553 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.8575   0.03092   0.02802  -0.0982   0.9931   0.0192
 -13.000  -0.8392   0.02892   0.02589  -0.1007   0.9862   0.0194
 -12.750  -0.8160   0.02754   0.02439  -0.1025   0.9798   0.0197
 -12.250  -0.7610   0.02413   0.02065  -0.1080   0.9647   0.0202
 -12.000  -0.7258   0.02264   0.01898  -0.1115   0.9546   0.0205
 -11.750  -0.6886   0.02150   0.01765  -0.1148   0.9381   0.0208
 -11.500  -0.6586   0.02059   0.01655  -0.1163   0.9144   0.0209
 -11.250  -0.6370   0.01971   0.01547  -0.1160   0.8881   0.0211
 -11.000  -0.6181   0.01884   0.01440  -0.1152   0.8594   0.0213
 -10.750  -0.5976   0.01830   0.01369  -0.1142   0.8284   0.0215
 -10.500  -0.5766   0.01789   0.01310  -0.1133   0.7939   0.0216
 -10.250  -0.5545   0.01761   0.01265  -0.1124   0.7587   0.0218
 -10.000  -0.5316   0.01733   0.01221  -0.1116   0.7284   0.0220
  -9.750  -0.5077   0.01704   0.01180  -0.1110   0.7051   0.0222
  -9.500  -0.4836   0.01667   0.01130  -0.1105   0.6870   0.0224
  -9.250  -0.4592   0.01621   0.01072  -0.1101   0.6727   0.0226
  -9.000  -0.4343   0.01580   0.01019  -0.1097   0.6610   0.0229
  -8.750  -0.4092   0.01534   0.00963  -0.1093   0.6507   0.0231
  -8.500  -0.3837   0.01491   0.00910  -0.1090   0.6422   0.0233
  -8.250  -0.3579   0.01450   0.00859  -0.1087   0.6342   0.0236
  -8.000  -0.3319   0.01412   0.00812  -0.1084   0.6273   0.0238
  -7.750  -0.3053   0.01378   0.00771  -0.1081   0.6214   0.0241
  -7.500  -0.2787   0.01345   0.00730  -0.1079   0.6156   0.0243
  -7.250  -0.2522   0.01314   0.00691  -0.1076   0.6099   0.0245
  -7.000  -0.2251   0.01282   0.00653  -0.1074   0.6053   0.0246
  -6.750  -0.1984   0.01246   0.00611  -0.1071   0.6000   0.0247
  -6.500  -0.1723   0.01200   0.00558  -0.1068   0.5947   0.0251
  -6.250  -0.1453   0.01167   0.00522  -0.1066   0.5899   0.0254
  -6.000  -0.1180   0.01140   0.00492  -0.1065   0.5849   0.0256
  -5.750  -0.0906   0.01117   0.00465  -0.1063   0.5794   0.0259
  -5.500  -0.0632   0.01097   0.00441  -0.1061   0.5741   0.0261
  -5.250  -0.0354   0.01075   0.00417  -0.1059   0.5699   0.0264
  -5.000  -0.0076   0.01056   0.00394  -0.1058   0.5651   0.0268
  -4.750   0.0201   0.01039   0.00374  -0.1056   0.5604   0.0272
  -4.500   0.0479   0.01023   0.00354  -0.1055   0.5557   0.0276
  -4.250   0.0760   0.01006   0.00334  -0.1054   0.5509   0.0279
  -4.000   0.1039   0.00990   0.00315  -0.1052   0.5456   0.0282
  -3.750   0.1318   0.00978   0.00298  -0.1051   0.5406   0.0285
  -3.500   0.1599   0.00964   0.00282  -0.1050   0.5360   0.0287
  -3.250   0.1879   0.00947   0.00262  -0.1049   0.5299   0.0292
  -3.000   0.2157   0.00934   0.00245  -0.1047   0.5234   0.0298
  -2.750   0.2439   0.00923   0.00232  -0.1046   0.5175   0.0303
  -2.500   0.2720   0.00914   0.00222  -0.1045   0.5108   0.0309
  -2.250   0.3000   0.00908   0.00212  -0.1044   0.5045   0.0316
  -2.000   0.3282   0.00901   0.00203  -0.1043   0.4974   0.0323
  -1.750   0.3560   0.00899   0.00196  -0.1041   0.4887   0.0331
  -1.500   0.3838   0.00896   0.00189  -0.1040   0.4767   0.0339
  -1.250   0.4115   0.00894   0.00183  -0.1038   0.4656   0.0354
  -1.000   0.4391   0.00895   0.00179  -0.1036   0.4544   0.0370
  -0.750   0.4669   0.00896   0.00177  -0.1034   0.4436   0.0388
  -0.500   0.4946   0.00896   0.00174  -0.1033   0.4349   0.0426
  -0.250   0.5223   0.00896   0.00173  -0.1031   0.4264   0.0500
   0.000   0.5497   0.00883   0.00173  -0.1030   0.4191   0.1001
   0.250   0.5773   0.00883   0.00174  -0.1029   0.4106   0.1219
   0.500   0.6043   0.00863   0.00175  -0.1028   0.4031   0.2124
   0.750   0.6312   0.00842   0.00177  -0.1027   0.3952   0.3131
   1.000   0.6577   0.00820   0.00184  -0.1026   0.3886   0.4353
   1.250   0.6851   0.00819   0.00192  -0.1024   0.3813   0.4795
   1.500   0.7121   0.00824   0.00202  -0.1022   0.3733   0.5191
   1.750   0.7395   0.00826   0.00211  -0.1020   0.3668   0.5524
   2.000   0.7666   0.00835   0.00220  -0.1018   0.3595   0.5726
   2.250   0.7940   0.00842   0.00228  -0.1016   0.3534   0.5872
   3.000   0.8757   0.00871   0.00256  -0.1010   0.3360   0.6187
   3.250   0.9028   0.00881   0.00266  -0.1008   0.3303   0.6291
   3.500   0.9296   0.00893   0.00278  -0.1006   0.3250   0.6392
   3.750   0.9566   0.00901   0.00288  -0.1004   0.3204   0.6546
   4.000   0.9833   0.00910   0.00301  -0.1001   0.3148   0.6727
   4.250   1.0097   0.00922   0.00314  -0.0998   0.3097   0.6879
   4.500   1.0363   0.00932   0.00327  -0.0996   0.3057   0.7039
   4.750   1.0626   0.00940   0.00340  -0.0992   0.3007   0.7240
   5.000   1.0881   0.00952   0.00356  -0.0988   0.2946   0.7513
   5.250   1.1131   0.00957   0.00372  -0.0982   0.2896   0.7927
   5.500   1.1448   0.00938   0.00387  -0.0991   0.2842   1.0000
   5.750   1.1705   0.00957   0.00404  -0.0987   0.2785   1.0000
   6.000   1.1962   0.00976   0.00420  -0.0983   0.2716   1.0000
   6.250   1.2207   0.01004   0.00441  -0.0978   0.2602   1.0000
   6.500   1.2447   0.01033   0.00464  -0.0972   0.2473   1.0000
   6.750   1.2676   0.01069   0.00491  -0.0964   0.2302   1.0000
   7.000   1.2881   0.01120   0.00527  -0.0953   0.2059   1.0000
   7.250   1.3087   0.01168   0.00564  -0.0942   0.1881   1.0000
   7.750   1.3523   0.01242   0.00629  -0.0924   0.1703   1.0000
   8.000   1.3742   0.01276   0.00661  -0.0915   0.1651   1.0000
   8.250   1.3965   0.01305   0.00691  -0.0906   0.1614   1.0000
   8.500   1.4192   0.01330   0.00717  -0.0898   0.1593   1.0000
   8.750   1.4411   0.01358   0.00747  -0.0889   0.1567   1.0000
   9.000   1.4619   0.01390   0.00779  -0.0879   0.1536   1.0000
   9.250   1.4818   0.01424   0.00813  -0.0867   0.1507   1.0000
   9.500   1.5001   0.01458   0.00849  -0.0852   0.1476   1.0000
   9.750   1.5187   0.01485   0.00880  -0.0837   0.1460   1.0000
  10.000   1.5366   0.01515   0.00912  -0.0821   0.1438   1.0000
  10.250   1.5524   0.01553   0.00951  -0.0802   0.1392   1.0000
  10.500   1.5651   0.01606   0.01003  -0.0780   0.1332   1.0000
  10.750   1.5807   0.01648   0.01046  -0.0762   0.1274   1.0000
  11.000   1.5898   0.01721   0.01112  -0.0736   0.1143   1.0000
  11.250   1.5770   0.01903   0.01270  -0.0684   0.0802   1.0000
  11.500   1.5795   0.02023   0.01388  -0.0655   0.0713   1.0000
  11.750   1.5848   0.02137   0.01502  -0.0632   0.0655   1.0000
  12.000   1.5903   0.02258   0.01626  -0.0612   0.0612   1.0000
  12.250   1.5968   0.02382   0.01753  -0.0594   0.0577   1.0000
  12.500   1.6035   0.02514   0.01888  -0.0578   0.0548   1.0000
  12.750   1.6085   0.02667   0.02043  -0.0564   0.0522   1.0000
  13.000   1.6152   0.02816   0.02198  -0.0552   0.0504   1.0000
  13.250   1.6222   0.02972   0.02358  -0.0542   0.0489   1.0000
  13.500   1.6275   0.03150   0.02541  -0.0534   0.0471   1.0000
  13.750   1.6299   0.03362   0.02757  -0.0525   0.0449   1.0000
  14.000   1.6337   0.03569   0.02970  -0.0519   0.0433   1.0000
  14.250   1.6386   0.03772   0.03179  -0.0514   0.0424   1.0000
  14.500   1.6407   0.04005   0.03418  -0.0510   0.0406   1.0000
  14.750   1.6417   0.04257   0.03675  -0.0506   0.0392   1.0000
  15.000   1.6406   0.04533   0.03956  -0.0503   0.0375   1.0000
  15.250   1.6414   0.04796   0.04226  -0.0502   0.0361   1.0000
  15.500   1.6411   0.05076   0.04512  -0.0501   0.0349   1.0000
  15.750   1.6380   0.05396   0.04838  -0.0501   0.0332   1.0000
  16.000   1.6347   0.05725   0.05172  -0.0503   0.0320   1.0000
  16.250   1.6328   0.06046   0.05501  -0.0505   0.0305   1.0000
  16.500   1.6289   0.06402   0.05863  -0.0510   0.0288   1.0000
  16.750   1.6234   0.06786   0.06253  -0.0516   0.0274   1.0000
  17.000   1.6192   0.07163   0.06637  -0.0523   0.0259   1.0000
  17.250   1.6125   0.07584   0.07064  -0.0532   0.0243   1.0000
  17.500   1.6058   0.08015   0.07502  -0.0542   0.0229   1.0000
  17.750   1.5986   0.08460   0.07954  -0.0554   0.0213   1.0000
  18.000   1.5897   0.08940   0.08441  -0.0568   0.0198   1.0000
  18.250   1.5823   0.09405   0.08914  -0.0582   0.0187   1.0000
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