Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 547 AIRFOIL (goe547-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 547 AIRFOIL (goe547-il)
Reynolds number: 1,000,000
Max Cl/Cd: 143.42 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe547-il-1000000.txt
Download as CSV file: xf-goe547-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 547 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.2888   0.13173   0.13016  -0.0393   0.9993   0.0164
 -12.750  -0.3969   0.13463   0.13289  -0.0350   1.0000   0.0150
 -12.500  -0.8574   0.03148   0.02894  -0.1009   0.9919   0.0146
 -12.250  -0.8329   0.02997   0.02736  -0.1032   0.9891   0.0150
 -12.000  -0.7980   0.03057   0.02804  -0.1043   0.9880   0.0153
 -11.750  -0.7657   0.03044   0.02792  -0.1059   0.9867   0.0156
 -11.500  -0.7347   0.02990   0.02733  -0.1079   0.9855   0.0160
 -11.250  -0.7059   0.02855   0.02585  -0.1105   0.9843   0.0165
 -11.000  -0.6865   0.02698   0.02410  -0.1111   0.9792   0.0171
 -10.750  -0.6589   0.02584   0.02281  -0.1127   0.9764   0.0176
 -10.500  -0.6273   0.02514   0.02198  -0.1146   0.9746   0.0180
 -10.250  -0.6040   0.02214   0.01869  -0.1171   0.9726   0.0188
 -10.000  -0.5787   0.02180   0.01834  -0.1171   0.9678   0.0192
  -9.750  -0.5500   0.02147   0.01798  -0.1179   0.9645   0.0196
  -9.500  -0.5199   0.02089   0.01733  -0.1191   0.9623   0.0202
  -9.250  -0.4883   0.02022   0.01658  -0.1206   0.9604   0.0208
  -9.000  -0.4547   0.01952   0.01577  -0.1226   0.9591   0.0217
  -8.750  -0.4304   0.01900   0.01513  -0.1223   0.9524   0.0223
  -8.500  -0.3976   0.01876   0.01478  -0.1237   0.9489   0.0227
  -8.250  -0.3707   0.01592   0.01161  -0.1254   0.9452   0.0238
  -8.000  -0.3443   0.01531   0.01095  -0.1256   0.9382   0.0244
  -7.750  -0.3124   0.01484   0.01041  -0.1269   0.9335   0.0251
  -7.500  -0.2825   0.01449   0.01000  -0.1276   0.9277   0.0259
  -7.250  -0.2546   0.01386   0.00925  -0.1279   0.9209   0.0265
  -7.000  -0.2263   0.01326   0.00854  -0.1283   0.9147   0.0271
  -6.750  -0.2006   0.01277   0.00794  -0.1280   0.9076   0.0276
  -6.250  -0.1472   0.01211   0.00711  -0.1277   0.8954   0.0285
  -6.000  -0.1202   0.01185   0.00676  -0.1276   0.8894   0.0288
  -5.750  -0.0992   0.01054   0.00532  -0.1266   0.8831   0.0297
  -5.500  -0.0752   0.00999   0.00470  -0.1259   0.8767   0.0305
  -5.250  -0.0491   0.00966   0.00431  -0.1257   0.8714   0.0313
  -5.000  -0.0245   0.00933   0.00395  -0.1250   0.8656   0.0318
  -4.750   0.0013   0.00906   0.00361  -0.1246   0.8599   0.0323
  -4.500   0.0272   0.00881   0.00331  -0.1242   0.8545   0.0329
  -4.250   0.0526   0.00857   0.00302  -0.1236   0.8485   0.0335
  -4.000   0.0790   0.00837   0.00275  -0.1233   0.8430   0.0342
  -3.750   0.1049   0.00817   0.00253  -0.1229   0.8375   0.0349
  -3.500   0.1311   0.00802   0.00233  -0.1225   0.8315   0.0357
  -3.250   0.1577   0.00788   0.00214  -0.1222   0.8259   0.0365
  -3.000   0.1833   0.00766   0.00188  -0.1216   0.8197   0.0385
  -2.750   0.2098   0.00753   0.00172  -0.1213   0.8138   0.0407
  -2.500   0.2361   0.00741   0.00160  -0.1209   0.8077   0.0433
  -2.250   0.2622   0.00728   0.00149  -0.1205   0.8010   0.0540
  -2.000   0.2884   0.00714   0.00141  -0.1201   0.7948   0.0765
  -1.750   0.3147   0.00706   0.00133  -0.1197   0.7877   0.0874
  -1.500   0.3406   0.00694   0.00125  -0.1193   0.7810   0.1083
  -1.250   0.3649   0.00661   0.00120  -0.1187   0.7730   0.2000
  -1.000   0.3903   0.00651   0.00117  -0.1181   0.7640   0.2348
  -0.750   0.4150   0.00642   0.00113  -0.1175   0.7527   0.2705
  -0.500   0.4396   0.00627   0.00112  -0.1168   0.7414   0.3249
   0.000   0.4877   0.00602   0.00114  -0.1152   0.7170   0.4517
   0.250   0.5116   0.00597   0.00116  -0.1143   0.7030   0.4999
   0.500   0.5354   0.00591   0.00120  -0.1134   0.6910   0.5555
   0.750   0.5588   0.00585   0.00124  -0.1125   0.6788   0.6134
   1.000   0.5828   0.00579   0.00128  -0.1116   0.6677   0.6606
   1.250   0.6051   0.00565   0.00133  -0.1104   0.6593   0.7322
   1.500   0.6703   0.00530   0.00151  -0.1187   0.6501   0.9758
   1.750   0.7118   0.00541   0.00158  -0.1217   0.6413   0.9939
   2.000   0.7482   0.00553   0.00164  -0.1237   0.6319   1.0000
   2.250   0.7711   0.00562   0.00170  -0.1226   0.6211   1.0000
   2.500   0.7937   0.00572   0.00176  -0.1214   0.6093   1.0000
   2.750   0.8163   0.00584   0.00183  -0.1203   0.5981   1.0000
   3.000   0.8389   0.00595   0.00190  -0.1191   0.5882   1.0000
   3.250   0.8621   0.00605   0.00199  -0.1181   0.5766   1.0000
   3.500   0.8843   0.00618   0.00207  -0.1169   0.5619   1.0000
   3.750   0.9064   0.00632   0.00217  -0.1156   0.5465   1.0000
   4.000   0.9274   0.00650   0.00227  -0.1141   0.5271   1.0000
   4.250   0.9443   0.00682   0.00243  -0.1118   0.4853   1.0000
   4.500   0.9578   0.00732   0.00267  -0.1089   0.4285   1.0000
   4.750   0.9692   0.00798   0.00299  -0.1057   0.3632   1.0000
   5.000   0.9829   0.00856   0.00331  -0.1029   0.3106   1.0000
   5.250   0.9988   0.00904   0.00361  -0.1006   0.2723   1.0000
   5.500   1.0168   0.00942   0.00387  -0.0988   0.2460   1.0000
   5.750   1.0352   0.00978   0.00412  -0.0970   0.2219   1.0000
   6.000   1.0529   0.01016   0.00439  -0.0950   0.1971   1.0000
   6.250   1.0665   0.01071   0.00473  -0.0924   0.1556   1.0000
   6.500   1.0762   0.01135   0.00516  -0.0889   0.1198   1.0000
   6.750   1.0918   0.01174   0.00549  -0.0866   0.1067   1.0000
   7.000   1.1094   0.01205   0.00578  -0.0847   0.0962   1.0000
   7.250   1.1253   0.01246   0.00612  -0.0825   0.0794   1.0000
   7.500   1.1371   0.01309   0.00658  -0.0797   0.0541   1.0000
   7.750   1.1518   0.01360   0.00703  -0.0773   0.0416   1.0000
   8.000   1.1621   0.01435   0.00763  -0.0743   0.0216   1.0000
   8.250   1.1764   0.01492   0.00818  -0.0720   0.0175   1.0000
   8.500   1.1931   0.01536   0.00866  -0.0701   0.0161   1.0000
   8.750   1.2085   0.01588   0.00921  -0.0681   0.0151   1.0000
   9.000   1.2220   0.01652   0.00989  -0.0658   0.0140   1.0000
   9.250   1.2360   0.01716   0.01058  -0.0637   0.0134   1.0000
   9.500   1.2515   0.01770   0.01116  -0.0618   0.0129   1.0000
   9.750   1.2658   0.01832   0.01183  -0.0599   0.0123   1.0000
  10.000   1.2794   0.01900   0.01256  -0.0579   0.0119   1.0000
  10.250   1.2921   0.01974   0.01335  -0.0558   0.0114   1.0000
  10.500   1.3023   0.02067   0.01433  -0.0535   0.0109   1.0000
  10.750   1.3082   0.02189   0.01563  -0.0507   0.0105   1.0000
  11.000   1.3152   0.02309   0.01691  -0.0482   0.0102   1.0000
  11.250   1.3298   0.02379   0.01766  -0.0468   0.0099   1.0000
  11.500   1.3407   0.02476   0.01870  -0.0450   0.0097   1.0000
  11.750   1.3513   0.02578   0.01978  -0.0432   0.0094   1.0000
  12.000   1.3596   0.02700   0.02107  -0.0413   0.0092   1.0000
  12.250   1.3689   0.02816   0.02229  -0.0396   0.0090   1.0000
  12.500   1.3771   0.02946   0.02365  -0.0379   0.0087   1.0000
  12.750   1.3831   0.03095   0.02521  -0.0361   0.0085   1.0000
  13.000   1.3913   0.03229   0.02660  -0.0346   0.0083   1.0000
  13.250   1.3940   0.03413   0.02852  -0.0328   0.0081   1.0000
  13.500   1.3925   0.03639   0.03087  -0.0309   0.0079   1.0000
  13.750   1.3927   0.03859   0.03315  -0.0292   0.0078   1.0000
  14.000   1.3858   0.04155   0.03624  -0.0272   0.0076   1.0000
  14.250   1.3869   0.04382   0.03860  -0.0259   0.0076   1.0000
  14.500   1.3907   0.04590   0.04077  -0.0250   0.0075   1.0000
  14.750   1.3961   0.04788   0.04285  -0.0243   0.0074   1.0000
  15.000   1.3971   0.05037   0.04543  -0.0235   0.0074   1.0000
  15.250   1.4006   0.05267   0.04784  -0.0230   0.0072   1.0000
  15.500   1.3989   0.05557   0.05085  -0.0224   0.0072   1.0000
  15.750   1.3993   0.05837   0.05375  -0.0222   0.0071   1.0000
  16.000   1.3976   0.06149   0.05698  -0.0220   0.0070   1.0000
  16.250   1.3944   0.06486   0.06047  -0.0220   0.0069   1.0000
  16.500   1.3931   0.06811   0.06382  -0.0223   0.0068   1.0000
  16.750   1.3900   0.07170   0.06751  -0.0228   0.0067   1.0000
  17.000   1.3865   0.07545   0.07136  -0.0235   0.0065   1.0000
  17.250   1.3795   0.07980   0.07584  -0.0244   0.0064   1.0000
  17.500   1.3733   0.08414   0.08029  -0.0255   0.0064   1.0000
  17.750   1.3660   0.08880   0.08506  -0.0269   0.0063   1.0000
  18.000   1.3587   0.09363   0.09001  -0.0286   0.0063   1.0000
  18.250   1.3518   0.09860   0.09507  -0.0307   0.0062   1.0000
  18.500   1.3401   0.10438   0.10098  -0.0330   0.0062   1.0000
  18.750   1.3291   0.11028   0.10701  -0.0356   0.0061   1.0000
  19.000   1.3166   0.11656   0.11343  -0.0386   0.0062   1.0000
  19.250   1.3048   0.12295   0.11995  -0.0419   0.0062   1.0000
<< Back to GOE 547 AIRFOIL (goe547-il)

Polar data table (+)

Polar graphs


<< Back to GOE 547 AIRFOIL (goe547-il)