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GOE 505 AIRFOIL (goe505-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 505 AIRFOIL (goe505-il)
Reynolds number: 1,000,000
Max Cl/Cd: 90.96 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe505-il-1000000.txt
Download as CSV file: xf-goe505-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 505 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750   0.0311   0.10191   0.10014  -0.1134   0.9662   0.0231
 -12.500   0.0392   0.09857   0.09680  -0.1153   0.9632   0.0240
 -12.000  -0.3726   0.03158   0.02894  -0.1694   0.9522   0.0228
 -11.750  -0.3526   0.03081   0.02815  -0.1698   0.9448   0.0231
 -11.500  -0.3542   0.02873   0.02588  -0.1680   0.9321   0.0232
 -11.250  -0.3515   0.02731   0.02429  -0.1657   0.9205   0.0235
 -11.000  -0.3480   0.02577   0.02254  -0.1632   0.9090   0.0237
 -10.750  -0.3440   0.02453   0.02113  -0.1602   0.8976   0.0240
 -10.500  -0.3361   0.02344   0.01985  -0.1576   0.8883   0.0243
 -10.250  -0.3240   0.02252   0.01875  -0.1556   0.8807   0.0247
 -10.000  -0.3123   0.02166   0.01772  -0.1532   0.8742   0.0250
  -9.750  -0.2975   0.02094   0.01684  -0.1513   0.8686   0.0253
  -9.500  -0.2801   0.02030   0.01603  -0.1498   0.8638   0.0255
  -9.250  -0.2627   0.01993   0.01554  -0.1480   0.8595   0.0257
  -9.000  -0.2541   0.01823   0.01359  -0.1452   0.8548   0.0260
  -8.750  -0.2390   0.01689   0.01210  -0.1433   0.8508   0.0263
  -8.500  -0.2199   0.01609   0.01121  -0.1420   0.8469   0.0266
  -8.250  -0.2002   0.01557   0.01066  -0.1406   0.8429   0.0271
  -8.000  -0.1792   0.01508   0.01010  -0.1394   0.8385   0.0275
  -7.750  -0.1568   0.01457   0.00948  -0.1384   0.8343   0.0278
  -7.500  -0.1347   0.01410   0.00894  -0.1374   0.8305   0.0281
  -7.250  -0.1132   0.01364   0.00843  -0.1361   0.8267   0.0284
  -7.000  -0.0910   0.01319   0.00790  -0.1350   0.8227   0.0287
  -6.750  -0.0672   0.01278   0.00741  -0.1342   0.8188   0.0290
  -6.500  -0.0431   0.01241   0.00697  -0.1335   0.8152   0.0294
  -6.250  -0.0206   0.01208   0.00660  -0.1323   0.8115   0.0298
  -6.000   0.0025   0.01176   0.00623  -0.1313   0.8070   0.0301
  -5.750   0.0277   0.01156   0.00594  -0.1306   0.8017   0.0305
  -5.500   0.0510   0.01131   0.00566  -0.1296   0.7968   0.0307
  -5.250   0.0731   0.01086   0.00516  -0.1284   0.7927   0.0310
  -5.000   0.0958   0.01040   0.00465  -0.1273   0.7895   0.0315
  -4.750   0.1202   0.01007   0.00427  -0.1266   0.7862   0.0320
  -4.500   0.1452   0.00982   0.00398  -0.1259   0.7825   0.0325
  -4.250   0.1688   0.00958   0.00373  -0.1250   0.7790   0.0331
  -4.000   0.1930   0.00937   0.00351  -0.1241   0.7748   0.0337
  -3.750   0.2181   0.00919   0.00329  -0.1234   0.7707   0.0344
  -3.500   0.2438   0.00905   0.00310  -0.1229   0.7667   0.0352
  -3.250   0.2677   0.00889   0.00295  -0.1220   0.7624   0.0361
  -3.000   0.2921   0.00875   0.00279  -0.1211   0.7575   0.0367
  -2.750   0.3166   0.00858   0.00257  -0.1203   0.7525   0.0386
  -2.500   0.3403   0.00843   0.00244  -0.1193   0.7472   0.0404
  -2.250   0.3637   0.00831   0.00231  -0.1182   0.7405   0.0428
  -2.000   0.3855   0.00809   0.00217  -0.1169   0.7334   0.0655
  -1.750   0.4064   0.00790   0.00209  -0.1154   0.7242   0.0944
  -1.500   0.4273   0.00779   0.00201  -0.1138   0.7142   0.1129
  -1.250   0.4465   0.00771   0.00196  -0.1119   0.7016   0.1336
  -1.000   0.4645   0.00768   0.00193  -0.1097   0.6854   0.1517
  -0.750   0.4800   0.00771   0.00192  -0.1069   0.6646   0.1671
  -0.500   0.4917   0.00780   0.00194  -0.1033   0.6403   0.1791
  -0.250   0.4998   0.00793   0.00196  -0.0990   0.6143   0.1874
   0.000   0.5084   0.00807   0.00201  -0.0948   0.5887   0.1955
   0.250   0.5171   0.00828   0.00209  -0.0907   0.5615   0.2008
   0.500   0.5277   0.00849   0.00219  -0.0870   0.5337   0.2074
   0.750   0.5381   0.00875   0.00233  -0.0834   0.5051   0.2135
   1.000   0.5490   0.00904   0.00248  -0.0799   0.4770   0.2190
   1.250   0.5601   0.00931   0.00265  -0.0765   0.4488   0.2272
   1.500   0.5738   0.00956   0.00280  -0.0736   0.4267   0.2344
   1.750   0.5879   0.00979   0.00295  -0.0709   0.4056   0.2439
   2.000   0.6043   0.00997   0.00309  -0.0687   0.3914   0.2565
   2.250   0.6203   0.01016   0.00324  -0.0664   0.3782   0.2686
   2.500   0.6361   0.01035   0.00341  -0.0640   0.3658   0.2829
   2.750   0.6551   0.01046   0.00355  -0.0623   0.3581   0.3055
   3.000   0.6720   0.01061   0.00372  -0.0603   0.3505   0.3364
   3.250   0.6904   0.01069   0.00388  -0.0585   0.3450   0.3727
   3.500   0.7067   0.01076   0.00405  -0.0564   0.3385   0.4233
   3.750   0.8640   0.01015   0.00476  -0.0856   0.3263   0.9842
   4.000   0.9014   0.01045   0.00501  -0.0880   0.3216   0.9919
   4.250   0.9398   0.01077   0.00527  -0.0907   0.3163   0.9966
   4.500   0.9855   0.01096   0.00544  -0.0948   0.3132   0.9992
   4.750   1.0142   0.01115   0.00561  -0.0954   0.3098   1.0000
   5.000   1.0281   0.01133   0.00577  -0.0928   0.3071   1.0000
   5.250   1.0420   0.01155   0.00597  -0.0902   0.3039   1.0000
   5.500   1.0553   0.01180   0.00620  -0.0875   0.3006   1.0000
   5.750   1.0737   0.01194   0.00635  -0.0858   0.2984   1.0000
   6.000   1.0916   0.01211   0.00653  -0.0841   0.2950   1.0000
   6.250   1.1082   0.01233   0.00674  -0.0821   0.2911   1.0000
   6.500   1.1235   0.01262   0.00700  -0.0800   0.2871   1.0000
   6.750   1.1413   0.01285   0.00722  -0.0783   0.2829   1.0000
   7.000   1.1603   0.01305   0.00743  -0.0769   0.2803   1.0000
   7.250   1.1778   0.01331   0.00768  -0.0753   0.2752   1.0000
   7.500   1.1939   0.01364   0.00798  -0.0734   0.2709   1.0000
   7.750   1.2127   0.01388   0.00823  -0.0720   0.2666   1.0000
   8.000   1.2311   0.01415   0.00850  -0.0707   0.2610   1.0000
   8.250   1.2466   0.01456   0.00886  -0.0688   0.2541   1.0000
   8.500   1.2651   0.01485   0.00915  -0.0675   0.2470   1.0000
   8.750   1.2806   0.01529   0.00954  -0.0658   0.2371   1.0000
   9.000   1.2949   0.01581   0.00999  -0.0640   0.2246   1.0000
   9.250   1.3066   0.01649   0.01055  -0.0618   0.2041   1.0000
   9.500   1.3106   0.01758   0.01144  -0.0586   0.1752   1.0000
   9.750   1.3152   0.01870   0.01239  -0.0556   0.1519   1.0000
  10.000   1.3128   0.02027   0.01369  -0.0519   0.1153   1.0000
  10.250   1.2888   0.02325   0.01628  -0.0457   0.0455   1.0000
  10.500   1.2884   0.02491   0.01786  -0.0426   0.0182   1.0000
  10.750   1.3004   0.02581   0.01878  -0.0410   0.0165   1.0000
  11.000   1.3120   0.02674   0.01976  -0.0395   0.0154   1.0000
  11.250   1.3240   0.02767   0.02074  -0.0381   0.0147   1.0000
  11.500   1.3342   0.02875   0.02186  -0.0366   0.0142   1.0000
  11.750   1.3429   0.02996   0.02313  -0.0350   0.0135   1.0000
  12.000   1.3497   0.03135   0.02458  -0.0332   0.0129   1.0000
  12.250   1.3598   0.03250   0.02578  -0.0319   0.0125   1.0000
  12.500   1.3683   0.03382   0.02715  -0.0306   0.0122   1.0000
  12.750   1.3751   0.03532   0.02870  -0.0292   0.0119   1.0000
  13.000   1.3821   0.03683   0.03028  -0.0279   0.0117   1.0000
  13.250   1.3873   0.03853   0.03204  -0.0266   0.0114   1.0000
  13.500   1.3914   0.04039   0.03397  -0.0253   0.0112   1.0000
  13.750   1.3937   0.04248   0.03612  -0.0241   0.0108   1.0000
  14.000   1.3915   0.04510   0.03883  -0.0228   0.0105   1.0000
  14.250   1.3819   0.04857   0.04243  -0.0215   0.0102   1.0000
  14.500   1.3768   0.05173   0.04570  -0.0206   0.0102   1.0000
  14.750   1.3804   0.05407   0.04810  -0.0201   0.0100   1.0000
  15.000   1.3816   0.05672   0.05083  -0.0198   0.0099   1.0000
  15.250   1.3735   0.06058   0.05479  -0.0195   0.0099   1.0000
  15.500   1.3698   0.06399   0.05830  -0.0194   0.0097   1.0000
  15.750   1.3653   0.06760   0.06200  -0.0195   0.0096   1.0000
  16.000   1.3554   0.07203   0.06653  -0.0198   0.0095   1.0000
  16.250   1.3500   0.07595   0.07054  -0.0202   0.0093   1.0000
  16.500   1.3368   0.08100   0.07570  -0.0209   0.0092   1.0000
  16.750   1.3242   0.08610   0.08091  -0.0218   0.0090   1.0000
  17.000   1.3137   0.09096   0.08587  -0.0227   0.0089   1.0000
  17.250   1.3004   0.09630   0.09132  -0.0239   0.0088   1.0000
  17.500   1.2851   0.10196   0.09709  -0.0252   0.0089   1.0000
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