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

GOE 504 AIRFOIL (goe504-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 504 AIRFOIL (goe504-il)
Reynolds number: 1,000,000
Max Cl/Cd: 104.1 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe504-il-1000000-n5.txt
Download as CSV file: xf-goe504-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 504 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
  ------ -------- --------- --------- -------- -------- --------
 -18.500  -0.6200   0.11268   0.11040  -0.0710   0.9999   0.0086
 -18.250  -0.6538   0.10213   0.09970  -0.0774   0.9995   0.0088
 -18.000  -0.6806   0.09303   0.09046  -0.0833   0.9990   0.0087
 -17.750  -0.6979   0.08563   0.08297  -0.0885   0.9983   0.0088
 -17.500  -0.7136   0.07868   0.07590  -0.0936   0.9972   0.0088
 -17.250  -0.7335   0.07163   0.06874  -0.0986   0.9939   0.0089
 -17.000  -0.7543   0.06497   0.06197  -0.1033   0.9916   0.0089
 -16.750  -0.7711   0.05880   0.05570  -0.1080   0.9888   0.0090
 -16.500  -0.7856   0.05264   0.04942  -0.1132   0.9857   0.0091
 -16.250  -0.8012   0.04636   0.04301  -0.1185   0.9817   0.0091
 -16.000  -0.8084   0.04088   0.03740  -0.1235   0.9767   0.0092
 -15.750  -0.8049   0.03592   0.03230  -0.1295   0.9732   0.0094
 -15.500  -0.7998   0.03161   0.02784  -0.1350   0.9673   0.0093
 -15.250  -0.7841   0.02839   0.02448  -0.1403   0.9622   0.0096
 -15.000  -0.7625   0.02597   0.02193  -0.1451   0.9575   0.0098
 -14.750  -0.7381   0.02398   0.01986  -0.1494   0.9511   0.0103
 -14.500  -0.7086   0.02243   0.01821  -0.1535   0.9449   0.0106
 -14.250  -0.6865   0.02131   0.01700  -0.1552   0.9339   0.0109
 -14.000  -0.6667   0.02040   0.01599  -0.1559   0.9220   0.0113
 -13.750  -0.6515   0.01961   0.01509  -0.1554   0.9073   0.0116
 -13.500  -0.6396   0.01897   0.01434  -0.1538   0.8909   0.0120
 -13.250  -0.6315   0.01839   0.01361  -0.1513   0.8714   0.0122
 -13.000  -0.6247   0.01788   0.01296  -0.1482   0.8530   0.0124
 -12.750  -0.6171   0.01746   0.01243  -0.1451   0.8362   0.0127
 -12.500  -0.6086   0.01711   0.01199  -0.1420   0.8205   0.0130
 -12.250  -0.5974   0.01686   0.01166  -0.1392   0.8073   0.0134
 -12.000  -0.5829   0.01657   0.01129  -0.1371   0.7952   0.0138
 -11.750  -0.5668   0.01630   0.01094  -0.1352   0.7841   0.0142
 -11.250  -0.5323   0.01572   0.01021  -0.1318   0.7643   0.0151
 -11.000  -0.5143   0.01545   0.00984  -0.1302   0.7555   0.0155
 -10.750  -0.4956   0.01514   0.00947  -0.1287   0.7466   0.0160
 -10.500  -0.4749   0.01494   0.00923  -0.1275   0.7389   0.0164
 -10.250  -0.4528   0.01477   0.00902  -0.1266   0.7313   0.0169
 -10.000  -0.4317   0.01457   0.00876  -0.1254   0.7242   0.0173
  -9.750  -0.4099   0.01434   0.00849  -0.1244   0.7168   0.0178
  -9.500  -0.3881   0.01416   0.00823  -0.1234   0.7100   0.0183
  -9.250  -0.3658   0.01393   0.00795  -0.1225   0.7041   0.0188
  -9.000  -0.3438   0.01371   0.00766  -0.1215   0.6971   0.0191
  -8.750  -0.3221   0.01347   0.00736  -0.1204   0.6910   0.0195
  -8.500  -0.3002   0.01319   0.00704  -0.1195   0.6850   0.0200
  -8.250  -0.2775   0.01300   0.00680  -0.1185   0.6786   0.0204
  -8.000  -0.2540   0.01281   0.00658  -0.1178   0.6730   0.0208
  -7.750  -0.2300   0.01266   0.00639  -0.1171   0.6666   0.0214
  -7.500  -0.2073   0.01248   0.00615  -0.1162   0.6605   0.0219
  -7.250  -0.1833   0.01228   0.00591  -0.1155   0.6548   0.0224
  -7.000  -0.1597   0.01212   0.00569  -0.1147   0.6483   0.0229
  -6.750  -0.1359   0.01196   0.00548  -0.1140   0.6424   0.0233
  -6.500  -0.1112   0.01183   0.00531  -0.1134   0.6366   0.0235
  -6.250  -0.0896   0.01153   0.00494  -0.1123   0.6304   0.0240
  -6.000  -0.0667   0.01127   0.00465  -0.1114   0.6247   0.0246
  -5.750  -0.0429   0.01109   0.00443  -0.1106   0.6180   0.0252
  -5.500  -0.0194   0.01095   0.00423  -0.1098   0.6119   0.0257
  -5.250   0.0052   0.01079   0.00404  -0.1092   0.6058   0.0261
  -5.000   0.0290   0.01066   0.00386  -0.1084   0.5990   0.0266
  -4.750   0.0533   0.01053   0.00369  -0.1077   0.5930   0.0271
  -4.500   0.0779   0.01042   0.00354  -0.1071   0.5866   0.0276
  -4.250   0.1017   0.01033   0.00339  -0.1063   0.5802   0.0280
  -4.000   0.1267   0.01022   0.00325  -0.1057   0.5741   0.0283
  -3.750   0.1507   0.01015   0.00313  -0.1050   0.5673   0.0286
  -3.500   0.1750   0.01004   0.00298  -0.1043   0.5617   0.0292
  -3.250   0.1993   0.00994   0.00285  -0.1036   0.5552   0.0299
  -3.000   0.2229   0.00988   0.00274  -0.1028   0.5490   0.0308
  -2.750   0.2478   0.00981   0.00265  -0.1022   0.5431   0.0318
  -2.500   0.2718   0.00977   0.00257  -0.1014   0.5366   0.0328
  -2.250   0.2960   0.00974   0.00250  -0.1007   0.5311   0.0338
  -2.000   0.3206   0.00970   0.00244  -0.1001   0.5250   0.0354
  -1.750   0.3441   0.00967   0.00239  -0.0992   0.5194   0.0390
  -1.500   0.3659   0.00946   0.00231  -0.0982   0.5142   0.0829
  -1.250   0.3888   0.00934   0.00225  -0.0972   0.5085   0.1080
  -1.000   0.4065   0.00900   0.00217  -0.0954   0.5026   0.1992
  -0.750   0.4299   0.00894   0.00217  -0.0946   0.4981   0.2230
  -0.500   0.4530   0.00890   0.00218  -0.0937   0.4932   0.2433
  -0.250   0.4744   0.00891   0.00220  -0.0924   0.4878   0.2568
   0.000   0.4963   0.00891   0.00221  -0.0913   0.4827   0.2659
   0.250   0.5187   0.00892   0.00222  -0.0902   0.4778   0.2746
   0.500   0.5398   0.00895   0.00225  -0.0889   0.4724   0.2851
   0.750   0.5619   0.00898   0.00228  -0.0878   0.4679   0.2943
   1.000   0.5840   0.00900   0.00232  -0.0867   0.4619   0.3027
   1.250   0.6049   0.00906   0.00237  -0.0855   0.4564   0.3127
   1.500   0.6260   0.00907   0.00244  -0.0842   0.4512   0.3378
   1.750   0.6476   0.00910   0.00252  -0.0831   0.4455   0.3582
   2.000   0.6670   0.00917   0.00262  -0.0815   0.4390   0.3814
   2.250   0.6887   0.00920   0.00271  -0.0805   0.4341   0.4039
   2.500   0.7093   0.00924   0.00281  -0.0792   0.4283   0.4326
   2.750   0.7281   0.00929   0.00293  -0.0776   0.4225   0.4709
   3.000   0.7477   0.00928   0.00305  -0.0761   0.4167   0.5218
   3.250   0.7655   0.00928   0.00319  -0.0743   0.4111   0.5803
   3.500   0.7806   0.00922   0.00335  -0.0719   0.4056   0.6632
   3.750   0.7943   0.00912   0.00350  -0.0692   0.4009   0.7532
   4.000   0.8058   0.00906   0.00369  -0.0659   0.3946   0.8403
   4.250   0.9131   0.00920   0.00405  -0.0837   0.3853   0.9536
   4.500   0.9771   0.00950   0.00430  -0.0921   0.3773   0.9768
   4.750   1.0098   0.00970   0.00448  -0.0935   0.3718   0.9880
   5.000   1.0348   0.00998   0.00472  -0.0934   0.3650   0.9989
   5.250   1.0597   0.01021   0.00492  -0.0933   0.3594   1.0000
   5.500   1.0759   0.01040   0.00510  -0.0913   0.3532   1.0000
   5.750   1.0916   0.01064   0.00531  -0.0892   0.3475   1.0000
   6.000   1.1090   0.01086   0.00552  -0.0875   0.3429   1.0000
   6.250   1.1260   0.01111   0.00575  -0.0858   0.3364   1.0000
   6.500   1.1414   0.01144   0.00604  -0.0838   0.3285   1.0000
   6.750   1.1552   0.01184   0.00639  -0.0817   0.3169   1.0000
   7.000   1.1731   0.01213   0.00667  -0.0803   0.3121   1.0000
   7.250   1.1879   0.01255   0.00705  -0.0784   0.3022   1.0000
   7.500   1.2041   0.01295   0.00742  -0.0768   0.2944   1.0000
   7.750   1.2173   0.01348   0.00789  -0.0748   0.2832   1.0000
   8.000   1.2291   0.01409   0.00844  -0.0727   0.2702   1.0000
   8.250   1.2458   0.01453   0.00887  -0.0713   0.2635   1.0000
   8.500   1.2582   0.01517   0.00947  -0.0695   0.2533   1.0000
   8.750   1.2703   0.01586   0.01011  -0.0676   0.2421   1.0000
   9.000   1.2806   0.01667   0.01086  -0.0656   0.2290   1.0000
   9.250   1.2882   0.01766   0.01177  -0.0634   0.2139   1.0000
   9.500   1.2965   0.01866   0.01270  -0.0613   0.2006   1.0000
   9.750   1.2979   0.02009   0.01403  -0.0586   0.1810   1.0000
  10.000   1.2865   0.02239   0.01613  -0.0548   0.1461   1.0000
  10.250   1.2597   0.02592   0.01939  -0.0499   0.0991   1.0000
  10.500   1.2326   0.02983   0.02310  -0.0458   0.0510   1.0000
  10.750   1.2195   0.03298   0.02616  -0.0431   0.0169   1.0000
  11.000   1.2272   0.03455   0.02776  -0.0422   0.0140   1.0000
  11.250   1.2365   0.03602   0.02926  -0.0414   0.0127   1.0000
  11.500   1.2447   0.03762   0.03090  -0.0406   0.0118   1.0000
  11.750   1.2521   0.03932   0.03265  -0.0399   0.0110   1.0000
  12.000   1.2599   0.04101   0.03437  -0.0392   0.0107   1.0000
  12.250   1.2678   0.04272   0.03613  -0.0386   0.0101   1.0000
  12.500   1.2748   0.04455   0.03800  -0.0380   0.0097   1.0000
  12.750   1.2809   0.04648   0.03998  -0.0374   0.0092   1.0000
  13.000   1.2857   0.04858   0.04212  -0.0369   0.0087   1.0000
  13.250   1.2890   0.05087   0.04447  -0.0363   0.0083   1.0000
  13.500   1.2932   0.05309   0.04674  -0.0359   0.0081   1.0000
  13.750   1.2989   0.05519   0.04889  -0.0355   0.0078   1.0000
  14.000   1.3025   0.05754   0.05130  -0.0352   0.0075   1.0000
  14.250   1.3053   0.06002   0.05383  -0.0349   0.0074   1.0000
  14.500   1.3081   0.06251   0.05638  -0.0347   0.0071   1.0000
  14.750   1.3095   0.06519   0.05913  -0.0345   0.0069   1.0000
  15.000   1.3111   0.06788   0.06187  -0.0343   0.0068   1.0000
  15.250   1.3116   0.07073   0.06477  -0.0343   0.0065   1.0000
  15.500   1.3111   0.07375   0.06786  -0.0342   0.0064   1.0000
  15.750   1.3089   0.07699   0.07117  -0.0343   0.0063   1.0000
  16.000   1.3074   0.08016   0.07441  -0.0343   0.0060   1.0000
  16.250   1.3061   0.08336   0.07768  -0.0345   0.0060   1.0000
  16.500   1.3045   0.08665   0.08103  -0.0347   0.0058   1.0000
  16.750   1.3021   0.09006   0.08452  -0.0350   0.0058   1.0000
  17.000   1.2990   0.09357   0.08811  -0.0354   0.0056   1.0000
  17.250   1.2962   0.09708   0.09169  -0.0358   0.0055   1.0000
  17.500   1.2940   0.10051   0.09518  -0.0363   0.0053   1.0000
  17.750   1.2905   0.10419   0.09893  -0.0369   0.0053   1.0000
  18.000   1.2877   0.10780   0.10261  -0.0375   0.0051   1.0000
  18.250   1.2842   0.11152   0.10639  -0.0383   0.0050   1.0000
  18.500   1.2802   0.11532   0.11026  -0.0391   0.0049   1.0000
  18.750   1.2752   0.11928   0.11429  -0.0400   0.0049   1.0000
  19.000   1.2735   0.12279   0.11786  -0.0409   0.0048   1.0000
<< Back to GOE 504 AIRFOIL (goe504-il)

Polar data table (+)

Polar graphs


<< Back to GOE 504 AIRFOIL (goe504-il)