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GOE 506 AIRFOIL (goe506-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 506 AIRFOIL (goe506-il)
Reynolds number: 500,000
Max Cl/Cd: 64.19 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe506-il-500000.txt
Download as CSV file: xf-goe506-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 506 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.3529   0.07272   0.07003  -0.1156   0.9742   0.0198
 -13.000  -0.3748   0.06286   0.06002  -0.1255   0.9724   0.0196
 -12.750  -0.3966   0.05386   0.05079  -0.1357   0.9685   0.0196
 -12.500  -0.4104   0.04723   0.04397  -0.1429   0.9635   0.0193
 -12.250  -0.4198   0.04121   0.03762  -0.1510   0.9600   0.0194
 -12.000  -0.4228   0.03667   0.03264  -0.1569   0.9567   0.0198
 -11.750  -0.4277   0.03488   0.03058  -0.1559   0.9484   0.0200
 -11.500  -0.4226   0.03105   0.02650  -0.1567   0.9442   0.0204
 -11.250  -0.4150   0.02982   0.02519  -0.1548   0.9380   0.0207
 -11.000  -0.3962   0.02928   0.02468  -0.1544   0.9334   0.0212
 -10.750  -0.3787   0.02813   0.02341  -0.1541   0.9295   0.0218
 -10.500  -0.3715   0.02697   0.02209  -0.1516   0.9236   0.0221
 -10.250  -0.3623   0.02583   0.02076  -0.1492   0.9177   0.0227
 -10.000  -0.3460   0.02450   0.01921  -0.1481   0.9135   0.0232
  -9.750  -0.3358   0.02368   0.01820  -0.1453   0.9079   0.0237
  -9.500  -0.3244   0.02324   0.01753  -0.1426   0.9018   0.0242
  -9.250  -0.3016   0.02115   0.01535  -0.1426   0.8980   0.0249
  -9.000  -0.2840   0.02060   0.01480  -0.1411   0.8929   0.0258
  -8.750  -0.2668   0.01995   0.01410  -0.1394   0.8875   0.0265
  -8.500  -0.2446   0.01934   0.01341  -0.1386   0.8833   0.0277
  -8.250  -0.2199   0.01867   0.01260  -0.1382   0.8798   0.0284
  -8.000  -0.2058   0.01832   0.01217  -0.1355   0.8741   0.0290
  -7.750  -0.1864   0.01713   0.01093  -0.1343   0.8696   0.0300
  -7.500  -0.1639   0.01634   0.01013  -0.1336   0.8658   0.0311
  -7.250  -0.1449   0.01589   0.00966  -0.1320   0.8610   0.0322
  -7.000  -0.1264   0.01544   0.00916  -0.1303   0.8554   0.0334
  -6.750  -0.1032   0.01497   0.00862  -0.1294   0.8512   0.0344
  -6.500  -0.0784   0.01461   0.00818  -0.1288   0.8475   0.0351
  -6.250  -0.0664   0.01390   0.00745  -0.1258   0.8416   0.0362
  -6.000  -0.0468   0.01335   0.00687  -0.1243   0.8368   0.0378
  -5.750  -0.0221   0.01293   0.00639  -0.1237   0.8330   0.0394
  -5.500  -0.0042   0.01262   0.00605  -0.1217   0.8273   0.0405
  -5.250   0.0182   0.01232   0.00569  -0.1205   0.8221   0.0418
  -5.000   0.0426   0.01190   0.00519  -0.1198   0.8180   0.0438
  -4.750   0.0624   0.01160   0.00487  -0.1182   0.8127   0.0460
  -4.500   0.0849   0.01134   0.00458  -0.1170   0.8078   0.0484
  -4.250   0.1105   0.01111   0.00428  -0.1165   0.8038   0.0516
  -4.000   0.1335   0.01080   0.00401  -0.1155   0.7993   0.0634
  -3.750   0.1471   0.01001   0.00375  -0.1130   0.7938   0.1931
  -3.500   0.1726   0.00987   0.00366  -0.1124   0.7892   0.2214
  -3.250   0.1979   0.00977   0.00357  -0.1118   0.7840   0.2376
  -3.000   0.2199   0.00969   0.00348  -0.1105   0.7768   0.2491
  -2.750   0.2459   0.00960   0.00334  -0.1100   0.7695   0.2590
  -2.500   0.2668   0.00950   0.00326  -0.1085   0.7616   0.2677
  -2.250   0.2929   0.00944   0.00314  -0.1081   0.7549   0.2761
  -2.000   0.3130   0.00935   0.00307  -0.1064   0.7459   0.2852
  -1.750   0.3358   0.00928   0.00298  -0.1053   0.7367   0.2967
  -1.500   0.3572   0.00921   0.00291  -0.1038   0.7264   0.3115
  -1.250   0.3772   0.00913   0.00287  -0.1021   0.7165   0.3286
  -1.000   0.3977   0.00905   0.00282  -0.1006   0.7063   0.3493
  -0.500   0.4313   0.00886   0.00276  -0.0958   0.6785   0.4136
  -0.250   0.4436   0.00876   0.00273  -0.0925   0.6579   0.4516
   0.000   0.4445   0.00873   0.00269  -0.0867   0.6185   0.4901
   0.250   0.4254   0.00909   0.00282  -0.0768   0.5491   0.5235
   0.500   0.4191   0.00943   0.00311  -0.0699   0.5090   0.5815
   0.750   0.4197   0.00954   0.00337  -0.0644   0.4825   0.6665
   1.000   0.4212   0.00952   0.00363  -0.0589   0.4591   0.7776
   1.250   0.5468   0.01011   0.00432  -0.0806   0.4101   0.9408
   1.500   0.5948   0.01062   0.00465  -0.0852   0.3892   0.9706
   1.750   0.6313   0.01101   0.00491  -0.0874   0.3761   0.9869
   2.000   0.6738   0.01136   0.00516  -0.0909   0.3660   0.9963
   2.250   0.7096   0.01168   0.00537  -0.0930   0.3581   1.0000
   2.500   0.7212   0.01182   0.00548  -0.0899   0.3537   1.0000
   2.750   0.7331   0.01200   0.00561  -0.0870   0.3491   1.0000
   3.000   0.7451   0.01223   0.00578  -0.0840   0.3450   1.0000
   3.250   0.7592   0.01244   0.00596  -0.0815   0.3416   1.0000
   3.500   0.7759   0.01261   0.00611  -0.0795   0.3384   1.0000
   3.750   0.7922   0.01281   0.00629  -0.0775   0.3354   1.0000
   4.000   0.8084   0.01304   0.00649  -0.0754   0.3321   1.0000
   4.250   0.8241   0.01332   0.00671  -0.0734   0.3288   1.0000
   4.500   0.8410   0.01359   0.00695  -0.0715   0.3261   1.0000
   4.750   0.8605   0.01377   0.00715  -0.0702   0.3239   1.0000
   5.000   0.8798   0.01398   0.00737  -0.0688   0.3214   1.0000
   5.250   0.8985   0.01422   0.00760  -0.0674   0.3185   1.0000
   5.500   0.9171   0.01449   0.00785  -0.0659   0.3160   1.0000
   5.750   0.9354   0.01479   0.00813  -0.0645   0.3133   1.0000
   6.000   0.9538   0.01513   0.00843  -0.0631   0.3107   1.0000
   6.250   0.9743   0.01535   0.00868  -0.0620   0.3087   1.0000
   6.500   0.9947   0.01558   0.00895  -0.0610   0.3066   1.0000
   6.750   1.0150   0.01584   0.00923  -0.0600   0.3042   1.0000
   7.000   1.0347   0.01612   0.00952  -0.0589   0.3016   1.0000
   7.250   1.0538   0.01644   0.00985  -0.0578   0.2990   1.0000
   7.500   1.0726   0.01680   0.01020  -0.0566   0.2964   1.0000
   7.750   1.0921   0.01714   0.01054  -0.0556   0.2938   1.0000
   8.000   1.1127   0.01739   0.01086  -0.0547   0.2904   1.0000
   8.250   1.1316   0.01772   0.01121  -0.0536   0.2852   1.0000
   8.500   1.1477   0.01819   0.01164  -0.0522   0.2791   1.0000
   8.750   1.1686   0.01846   0.01197  -0.0515   0.2742   1.0000
   9.000   1.1866   0.01886   0.01239  -0.0504   0.2671   1.0000
   9.250   1.2048   0.01928   0.01281  -0.0493   0.2594   1.0000
   9.500   1.2211   0.01980   0.01330  -0.0481   0.2486   1.0000
   9.750   1.2390   0.02026   0.01377  -0.0471   0.2375   1.0000
  10.000   1.2505   0.02108   0.01445  -0.0453   0.2105   1.0000
  10.250   1.2566   0.02225   0.01543  -0.0430   0.1862   1.0000
  10.500   1.2659   0.02327   0.01639  -0.0411   0.1759   1.0000
  10.750   1.2761   0.02426   0.01734  -0.0394   0.1697   1.0000
  11.000   1.2891   0.02509   0.01821  -0.0380   0.1652   1.0000
  11.250   1.3013   0.02599   0.01913  -0.0366   0.1609   1.0000
  11.500   1.3096   0.02716   0.02028  -0.0349   0.1554   1.0000
  11.750   1.3233   0.02800   0.02118  -0.0337   0.1503   1.0000
  12.000   1.3343   0.02905   0.02224  -0.0324   0.1437   1.0000
  12.250   1.3461   0.03006   0.02325  -0.0312   0.1332   1.0000
  12.500   1.3448   0.03204   0.02496  -0.0290   0.0892   1.0000
  12.750   1.3217   0.03581   0.02851  -0.0252   0.0500   1.0000
  13.000   1.3081   0.03905   0.03166  -0.0227   0.0271   1.0000
  13.250   1.3067   0.04142   0.03409  -0.0211   0.0231   1.0000
  13.500   1.3074   0.04369   0.03645  -0.0198   0.0212   1.0000
  13.750   1.3101   0.04585   0.03871  -0.0188   0.0203   1.0000
  14.000   1.3107   0.04826   0.04122  -0.0179   0.0196   1.0000
  14.250   1.3075   0.05116   0.04423  -0.0170   0.0187   1.0000
  14.500   1.3010   0.05455   0.04773  -0.0163   0.0180   1.0000
  14.750   1.2929   0.05829   0.05159  -0.0158   0.0177   1.0000
  15.000   1.2905   0.06150   0.05491  -0.0157   0.0172   1.0000
  15.250   1.2841   0.06534   0.05887  -0.0158   0.0169   1.0000
  15.500   1.2779   0.06929   0.06293  -0.0161   0.0166   1.0000
  15.750   1.2674   0.07392   0.06769  -0.0167   0.0162   1.0000
  16.000   1.2570   0.07860   0.07249  -0.0174   0.0162   1.0000
  16.250   1.2453   0.08354   0.07756  -0.0183   0.0159   1.0000
  16.500   1.2338   0.08851   0.08264  -0.0193   0.0157   1.0000
  16.750   1.2200   0.09386   0.08811  -0.0204   0.0156   1.0000
  17.000   1.2074   0.09909   0.09344  -0.0216   0.0154   1.0000
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