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GOE 505 AIRFOIL (goe505-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 505 AIRFOIL (goe505-il)
Reynolds number: 500,000
Max Cl/Cd: 73.5 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe505-il-500000.txt
Download as CSV file: xf-goe505-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.0029   0.07545   0.07296  -0.1319   0.9524   0.0441
  -9.500  -0.1658   0.03711   0.03392  -0.1598   0.9189   0.0367
  -9.250  -0.1671   0.03371   0.03039  -0.1581   0.9125   0.0358
  -9.000  -0.1848   0.03011   0.02645  -0.1537   0.9038   0.0354
  -8.750  -0.1872   0.02732   0.02330  -0.1505   0.8979   0.0353
  -8.500  -0.1799   0.02515   0.02079  -0.1482   0.8938   0.0353
  -8.250  -0.1745   0.02379   0.01919  -0.1448   0.8881   0.0356
  -8.000  -0.1597   0.02259   0.01774  -0.1429   0.8842   0.0359
  -7.750  -0.1405   0.02145   0.01635  -0.1417   0.8810   0.0362
  -7.500  -0.1238   0.02053   0.01523  -0.1398   0.8768   0.0363
  -7.250  -0.1069   0.01978   0.01430  -0.1378   0.8721   0.0365
  -7.000  -0.0866   0.01836   0.01266  -0.1367   0.8678   0.0367
  -6.750  -0.0620   0.01700   0.01110  -0.1363   0.8643   0.0370
  -6.500  -0.0452   0.01609   0.01011  -0.1342   0.8596   0.0374
  -6.250  -0.0230   0.01536   0.00932  -0.1332   0.8549   0.0381
  -6.000   0.0037   0.01478   0.00865  -0.1330   0.8509   0.0388
  -5.750   0.0287   0.01428   0.00808  -0.1324   0.8468   0.0393
  -5.500   0.0495   0.01386   0.00761  -0.1309   0.8418   0.0398
  -5.250   0.0750   0.01341   0.00708  -0.1303   0.8369   0.0404
  -5.000   0.1031   0.01299   0.00656  -0.1302   0.8319   0.0410
  -4.750   0.1226   0.01265   0.00620  -0.1283   0.8253   0.0416
  -4.500   0.1483   0.01232   0.00579  -0.1278   0.8204   0.0422
  -4.250   0.1769   0.01203   0.00542  -0.1278   0.8168   0.0429
  -4.000   0.1974   0.01173   0.00511  -0.1262   0.8125   0.0439
  -3.750   0.2202   0.01141   0.00479  -0.1251   0.8081   0.0457
  -3.500   0.2465   0.01117   0.00452  -0.1247   0.8038   0.0476
  -3.250   0.2754   0.01098   0.00427  -0.1248   0.7998   0.0497
  -3.000   0.2954   0.01079   0.00410  -0.1230   0.7945   0.0525
  -2.750   0.3196   0.01055   0.00390  -0.1221   0.7890   0.0609
  -2.500   0.3468   0.01026   0.00370  -0.1219   0.7845   0.0926
  -2.250   0.3671   0.01008   0.00364  -0.1202   0.7789   0.1169
  -2.000   0.3900   0.00995   0.00356  -0.1191   0.7730   0.1374
  -1.750   0.4175   0.00984   0.00347  -0.1189   0.7678   0.1578
  -1.500   0.4366   0.00978   0.00346  -0.1169   0.7608   0.1725
  -1.250   0.4604   0.00972   0.00338  -0.1159   0.7539   0.1857
  -1.000   0.4814   0.00965   0.00334  -0.1143   0.7461   0.1973
  -0.750   0.5032   0.00958   0.00326  -0.1129   0.7374   0.2074
  -0.500   0.5222   0.00954   0.00321  -0.1109   0.7267   0.2171
  -0.250   0.5413   0.00946   0.00315  -0.1089   0.7152   0.2269
   0.250   0.5751   0.00940   0.00302  -0.1040   0.6841   0.2452
   0.500   0.5889   0.00943   0.00296  -0.1008   0.6628   0.2549
   0.750   0.5973   0.00949   0.00294  -0.0966   0.6382   0.2642
   1.000   0.6032   0.00963   0.00295  -0.0918   0.6112   0.2728
   1.250   0.6094   0.00982   0.00303  -0.0872   0.5830   0.2829
   1.500   0.6153   0.01009   0.00318  -0.0826   0.5541   0.2938
   1.750   0.6209   0.01040   0.00337  -0.0780   0.5246   0.3061
   2.000   0.6260   0.01075   0.00360  -0.0734   0.4942   0.3228
   2.250   0.6341   0.01104   0.00383  -0.0696   0.4680   0.3459
   2.500   0.6425   0.01133   0.00408  -0.0658   0.4454   0.3772
   2.750   0.6525   0.01150   0.00429  -0.0624   0.4270   0.4246
   3.000   0.8177   0.01148   0.00539  -0.0931   0.3905   0.9901
   3.250   0.8687   0.01195   0.00572  -0.0984   0.3786   0.9980
   3.500   0.8996   0.01224   0.00593  -0.0995   0.3699   1.0000
   3.750   0.9093   0.01247   0.00610  -0.0961   0.3641   1.0000
   4.000   0.9222   0.01266   0.00626  -0.0932   0.3585   1.0000
   4.250   0.9338   0.01291   0.00646  -0.0902   0.3530   1.0000
   4.500   0.9467   0.01319   0.00668  -0.0875   0.3488   1.0000
   4.750   0.9628   0.01337   0.00686  -0.0853   0.3439   1.0000
   5.000   0.9780   0.01361   0.00707  -0.0831   0.3401   1.0000
   5.250   0.9927   0.01390   0.00732  -0.0808   0.3361   1.0000
   5.500   1.0082   0.01421   0.00759  -0.0786   0.3325   1.0000
   5.750   1.0262   0.01442   0.00782  -0.0770   0.3295   1.0000
   6.000   1.0438   0.01466   0.00807  -0.0752   0.3263   1.0000
   6.250   1.0609   0.01495   0.00833  -0.0735   0.3230   1.0000
   6.500   1.0773   0.01528   0.00864  -0.0717   0.3196   1.0000
   6.750   1.0943   0.01563   0.00896  -0.0700   0.3161   1.0000
   7.000   1.1128   0.01586   0.00923  -0.0685   0.3125   1.0000
   7.250   1.1304   0.01615   0.00953  -0.0670   0.3079   1.0000
   7.500   1.1457   0.01656   0.00989  -0.0651   0.3027   1.0000
   7.750   1.1633   0.01690   0.01024  -0.0637   0.2988   1.0000
   8.000   1.1820   0.01717   0.01056  -0.0624   0.2944   1.0000
   8.250   1.1990   0.01755   0.01093  -0.0609   0.2899   1.0000
   8.500   1.2138   0.01805   0.01139  -0.0592   0.2848   1.0000
   8.750   1.2333   0.01832   0.01173  -0.0581   0.2806   1.0000
   9.000   1.2503   0.01872   0.01214  -0.0568   0.2746   1.0000
   9.250   1.2651   0.01926   0.01264  -0.0551   0.2687   1.0000
   9.500   1.2836   0.01961   0.01304  -0.0541   0.2613   1.0000
   9.750   1.2974   0.02022   0.01361  -0.0524   0.2539   1.0000
  10.000   1.3148   0.02068   0.01408  -0.0513   0.2436   1.0000
  10.250   1.3287   0.02133   0.01470  -0.0498   0.2308   1.0000
  10.500   1.3389   0.02221   0.01547  -0.0479   0.2117   1.0000
  10.750   1.3455   0.02335   0.01645  -0.0456   0.1882   1.0000
  11.000   1.3469   0.02487   0.01777  -0.0428   0.1627   1.0000
  11.250   1.3494   0.02637   0.01913  -0.0403   0.1423   1.0000
  11.500   1.3365   0.02898   0.02140  -0.0364   0.0905   1.0000
  11.750   1.3098   0.03278   0.02492  -0.0316   0.0326   1.0000
  12.000   1.3099   0.03474   0.02688  -0.0295   0.0223   1.0000
  12.250   1.3158   0.03632   0.02852  -0.0279   0.0204   1.0000
  12.500   1.3217   0.03793   0.03021  -0.0265   0.0192   1.0000
  12.750   1.3277   0.03957   0.03194  -0.0252   0.0186   1.0000
  13.000   1.3336   0.04127   0.03373  -0.0240   0.0182   1.0000
  13.250   1.3365   0.04331   0.03587  -0.0228   0.0175   1.0000
  13.500   1.3380   0.04556   0.03822  -0.0216   0.0170   1.0000
  13.750   1.3353   0.04829   0.04106  -0.0205   0.0165   1.0000
  14.000   1.3295   0.05150   0.04439  -0.0195   0.0161   1.0000
  14.250   1.3226   0.05498   0.04799  -0.0187   0.0159   1.0000
  14.500   1.3197   0.05813   0.05125  -0.0183   0.0157   1.0000
  14.750   1.3156   0.06153   0.05476  -0.0180   0.0154   1.0000
  15.000   1.3094   0.06530   0.05864  -0.0180   0.0152   1.0000
  15.250   1.3002   0.06958   0.06305  -0.0181   0.0152   1.0000
  15.500   1.2915   0.07393   0.06753  -0.0185   0.0151   1.0000
  15.750   1.2796   0.07880   0.07253  -0.0191   0.0150   1.0000
  16.000   1.2676   0.08381   0.07766  -0.0199   0.0148   1.0000
  16.250   1.2547   0.08907   0.08304  -0.0209   0.0148   1.0000
  16.500   1.2409   0.09452   0.08861  -0.0221   0.0146   1.0000
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