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

GOE 522 AIRFOIL (goe522-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 522 AIRFOIL (goe522-il)
Reynolds number: 500,000
Max Cl/Cd: 73.66 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe522-il-500000.txt
Download as CSV file: xf-goe522-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 522 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
  ------ -------- --------- --------- -------- -------- --------
 -18.750  -0.6577   0.11173   0.10816  -0.0792   0.9997   0.0371
 -18.500  -0.6843   0.10222   0.09843  -0.0864   0.9989   0.0369
 -18.250  -0.6993   0.09481   0.09085  -0.0924   0.9978   0.0368
 -18.000  -0.7081   0.08856   0.08445  -0.0978   0.9964   0.0367
 -17.750  -0.7130   0.08297   0.07872  -0.1028   0.9949   0.0367
 -17.500  -0.7138   0.07804   0.07366  -0.1076   0.9934   0.0367
 -17.250  -0.7090   0.07398   0.06949  -0.1118   0.9921   0.0367
 -17.000  -0.7054   0.07023   0.06564  -0.1151   0.9901   0.0367
 -16.750  -0.6995   0.06691   0.06224  -0.1181   0.9877   0.0367
 -16.500  -0.6925   0.06359   0.05882  -0.1213   0.9855   0.0368
 -16.250  -0.6818   0.06065   0.05581  -0.1245   0.9835   0.0368
 -16.000  -0.6688   0.05789   0.05297  -0.1278   0.9818   0.0369
 -15.750  -0.6541   0.05530   0.05030  -0.1310   0.9803   0.0369
 -15.500  -0.6385   0.05271   0.04764  -0.1345   0.9791   0.0371
 -15.250  -0.6218   0.05047   0.04534  -0.1374   0.9774   0.0372
 -15.000  -0.6124   0.04851   0.04333  -0.1383   0.9724   0.0372
 -14.750  -0.5953   0.04631   0.04108  -0.1411   0.9695   0.0373
 -14.500  -0.5755   0.04425   0.03896  -0.1440   0.9674   0.0375
 -14.250  -0.5530   0.04233   0.03700  -0.1470   0.9657   0.0375
 -14.000  -0.5308   0.04022   0.03482  -0.1505   0.9643   0.0377
 -13.750  -0.5060   0.03843   0.03300  -0.1537   0.9629   0.0378
 -13.500  -0.4963   0.03672   0.03123  -0.1543   0.9557   0.0379
 -13.250  -0.4735   0.03533   0.02985  -0.1560   0.9529   0.0382
 -13.000  -0.4483   0.03368   0.02820  -0.1590   0.9504   0.0384
 -12.750  -0.4197   0.03186   0.02637  -0.1630   0.9484   0.0387
 -12.500  -0.3957   0.02998   0.02446  -0.1666   0.9443   0.0390
 -12.250  -0.3812   0.02815   0.02260  -0.1685   0.9364   0.0393
 -12.000  -0.3558   0.02624   0.02063  -0.1725   0.9312   0.0396
 -11.750  -0.3429   0.02461   0.01894  -0.1738   0.9227   0.0398
 -11.500  -0.3287   0.02303   0.01729  -0.1752   0.9140   0.0400
 -11.250  -0.3219   0.02161   0.01579  -0.1750   0.9039   0.0403
 -11.000  -0.3143   0.02043   0.01452  -0.1743   0.8941   0.0405
 -10.750  -0.3126   0.01949   0.01350  -0.1721   0.8844   0.0406
 -10.500  -0.3095   0.01870   0.01262  -0.1694   0.8753   0.0408
 -10.250  -0.3057   0.01808   0.01192  -0.1663   0.8671   0.0411
 -10.000  -0.3052   0.01764   0.01142  -0.1621   0.8580   0.0412
  -9.750  -0.2909   0.01714   0.01083  -0.1604   0.8513   0.0415
  -9.500  -0.2835   0.01676   0.01041  -0.1572   0.8430   0.0418
  -9.250  -0.2681   0.01634   0.00991  -0.1553   0.8357   0.0420
  -9.000  -0.2505   0.01590   0.00940  -0.1539   0.8294   0.0424
  -8.750  -0.2384   0.01545   0.00893  -0.1513   0.8217   0.0429
  -8.500  -0.2197   0.01504   0.00846  -0.1499   0.8149   0.0435
  -8.250  -0.1996   0.01467   0.00802  -0.1487   0.8084   0.0442
  -8.000  -0.1820   0.01434   0.00767  -0.1469   0.8005   0.0450
  -7.750  -0.1597   0.01404   0.00728  -0.1459   0.7934   0.0460
  -7.500  -0.1388   0.01375   0.00696  -0.1447   0.7863   0.0473
  -7.250  -0.1193   0.01342   0.00662  -0.1432   0.7785   0.0499
  -7.000  -0.0998   0.01290   0.00619  -0.1419   0.7713   0.0701
  -6.750  -0.0795   0.01262   0.00597  -0.1405   0.7635   0.0848
  -6.500  -0.0570   0.01241   0.00575  -0.1394   0.7550   0.0934
  -6.250  -0.0336   0.01222   0.00555  -0.1385   0.7468   0.1015
  -6.000  -0.0119   0.01204   0.00539  -0.1373   0.7373   0.1102
  -5.750   0.0124   0.01191   0.00522  -0.1365   0.7285   0.1183
  -5.500   0.0342   0.01178   0.00510  -0.1352   0.7187   0.1258
  -5.250   0.0577   0.01168   0.00495  -0.1342   0.7087   0.1336
  -5.000   0.0788   0.01154   0.00483  -0.1328   0.6975   0.1406
  -4.750   0.1011   0.01149   0.00470  -0.1316   0.6856   0.1476
  -4.500   0.1210   0.01135   0.00455  -0.1299   0.6719   0.1550
  -4.250   0.1413   0.01127   0.00443  -0.1283   0.6576   0.1620
  -4.000   0.1600   0.01118   0.00429  -0.1264   0.6423   0.1709
  -3.750   0.1773   0.01109   0.00416  -0.1243   0.6262   0.1821
  -3.500   0.1946   0.01097   0.00405  -0.1222   0.6101   0.1998
  -3.250   0.2117   0.01085   0.00400  -0.1201   0.5957   0.2290
  -3.000   0.2292   0.01086   0.00399  -0.1180   0.5828   0.2535
  -2.750   0.2468   0.01088   0.00399  -0.1159   0.5713   0.2705
  -2.500   0.2651   0.01091   0.00400  -0.1139   0.5617   0.2827
  -2.250   0.2858   0.01099   0.00401  -0.1123   0.5533   0.2928
  -2.000   0.3056   0.01106   0.00404  -0.1107   0.5457   0.3024
  -1.750   0.3285   0.01111   0.00407  -0.1096   0.5398   0.3113
  -1.500   0.3503   0.01114   0.00410  -0.1083   0.5339   0.3197
  -1.250   0.3715   0.01125   0.00415  -0.1070   0.5276   0.3278
  -1.000   0.3946   0.01135   0.00420  -0.1059   0.5220   0.3346
  -0.750   0.4159   0.01136   0.00425  -0.1046   0.5162   0.3424
  -0.500   0.4377   0.01145   0.00431  -0.1033   0.5106   0.3510
  -0.250   0.4612   0.01160   0.00440  -0.1025   0.5054   0.3596
   0.000   0.4844   0.01164   0.00449  -0.1015   0.5015   0.3691
   0.250   0.5067   0.01172   0.00457  -0.1004   0.4972   0.3782
   0.500   0.5284   0.01177   0.00465  -0.0991   0.4927   0.3876
   0.750   0.5507   0.01188   0.00474  -0.0981   0.4883   0.3966
   1.000   0.5751   0.01204   0.00484  -0.0974   0.4829   0.4053
   1.250   0.5957   0.01206   0.00494  -0.0960   0.4796   0.4161
   1.500   0.6167   0.01213   0.00504  -0.0946   0.4753   0.4273
   1.750   0.6375   0.01220   0.00515  -0.0933   0.4711   0.4405
   2.000   0.6587   0.01232   0.00526  -0.0920   0.4667   0.4542
   2.250   0.6828   0.01247   0.00540  -0.0914   0.4625   0.4705
   2.500   0.7034   0.01251   0.00554  -0.0900   0.4597   0.4884
   2.750   0.7243   0.01258   0.00568  -0.0887   0.4563   0.5065
   3.000   0.7451   0.01267   0.00583  -0.0874   0.4529   0.5261
   3.250   0.7658   0.01279   0.00597  -0.0861   0.4493   0.5462
   3.500   0.7867   0.01293   0.00614  -0.0849   0.4456   0.5663
   3.750   0.8089   0.01306   0.00631  -0.0839   0.4420   0.5874
   4.000   0.8280   0.01314   0.00650  -0.0823   0.4389   0.6081
   4.250   0.8468   0.01324   0.00668  -0.0807   0.4352   0.6301
   4.500   0.8650   0.01335   0.00686  -0.0791   0.4312   0.6547
   4.750   0.8834   0.01348   0.00706  -0.0774   0.4275   0.6837
   5.000   0.9025   0.01361   0.00727  -0.0759   0.4234   0.7214
   5.250   0.9163   0.01362   0.00754  -0.0733   0.4203   0.7828
   5.500   0.9738   0.01359   0.00791  -0.0797   0.4153   0.9239
   5.750   1.0276   0.01395   0.00823  -0.0856   0.4100   1.0000
   6.000   1.0465   0.01427   0.00847  -0.0844   0.4056   1.0000
   6.250   1.0669   0.01452   0.00874  -0.0833   0.4018   1.0000
   6.500   1.0869   0.01479   0.00901  -0.0823   0.3973   1.0000
   6.750   1.1054   0.01512   0.00931  -0.0810   0.3925   1.0000
   7.000   1.1227   0.01552   0.00965  -0.0796   0.3875   1.0000
   7.250   1.1425   0.01585   0.00999  -0.0786   0.3829   1.0000
   7.500   1.1612   0.01621   0.01036  -0.0775   0.3774   1.0000
   7.750   1.1779   0.01668   0.01079  -0.0762   0.3716   1.0000
   8.000   1.1952   0.01715   0.01123  -0.0750   0.3659   1.0000
   8.250   1.2131   0.01760   0.01170  -0.0739   0.3593   1.0000
   8.500   1.2276   0.01822   0.01227  -0.0724   0.3524   1.0000
   8.750   1.2447   0.01876   0.01281  -0.0713   0.3450   1.0000
   9.000   1.2583   0.01949   0.01350  -0.0699   0.3366   1.0000
   9.250   1.2731   0.02019   0.01419  -0.0686   0.3281   1.0000
   9.500   1.2838   0.02112   0.01507  -0.0670   0.3183   1.0000
   9.750   1.2973   0.02196   0.01589  -0.0658   0.3087   1.0000
  10.000   1.3054   0.02313   0.01699  -0.0640   0.2987   1.0000
  10.250   1.3176   0.02411   0.01795  -0.0628   0.2898   1.0000
  10.500   1.3257   0.02536   0.01916  -0.0612   0.2818   1.0000
  10.750   1.3376   0.02643   0.02021  -0.0601   0.2750   1.0000
  11.000   1.3450   0.02780   0.02153  -0.0586   0.2692   1.0000
  11.250   1.3576   0.02887   0.02261  -0.0577   0.2645   1.0000
  11.500   1.3692   0.03002   0.02378  -0.0567   0.2603   1.0000
  11.750   1.3787   0.03133   0.02507  -0.0555   0.2565   1.0000
  12.000   1.3861   0.03280   0.02650  -0.0543   0.2528   1.0000
  12.250   1.3995   0.03389   0.02764  -0.0536   0.2503   1.0000
  12.500   1.4129   0.03498   0.02877  -0.0530   0.2479   1.0000
  12.750   1.4239   0.03626   0.03007  -0.0522   0.2454   1.0000
  13.000   1.4343   0.03759   0.03142  -0.0513   0.2431   1.0000
  13.250   1.4441   0.03897   0.03279  -0.0505   0.2409   1.0000
  13.500   1.4532   0.04040   0.03421  -0.0497   0.2387   1.0000
  13.750   1.4650   0.04161   0.03544  -0.0490   0.2366   1.0000
  14.000   1.4774   0.04286   0.03676  -0.0485   0.2352   1.0000
  14.250   1.4885   0.04422   0.03818  -0.0479   0.2337   1.0000
  14.500   1.4997   0.04557   0.03957  -0.0474   0.2321   1.0000
  14.750   1.5107   0.04693   0.04097  -0.0469   0.2305   1.0000
  15.000   1.5207   0.04841   0.04248  -0.0464   0.2289   1.0000
  15.250   1.5311   0.04982   0.04392  -0.0459   0.2275   1.0000
  15.500   1.5419   0.05117   0.04528  -0.0454   0.2259   1.0000
  15.750   1.5536   0.05238   0.04649  -0.0449   0.2242   1.0000
  16.000   1.5699   0.05307   0.04715  -0.0444   0.2224   1.0000
  16.250   1.5780   0.05481   0.04898  -0.0441   0.2214   1.0000
  16.500   1.5867   0.05648   0.05074  -0.0438   0.2203   1.0000
  16.750   1.5958   0.05810   0.05242  -0.0435   0.2192   1.0000
  17.000   1.6046   0.05974   0.05413  -0.0432   0.2180   1.0000
  17.250   1.6142   0.06130   0.05574  -0.0430   0.2168   1.0000
  17.500   1.6222   0.06302   0.05752  -0.0427   0.2154   1.0000
  17.750   1.6304   0.06471   0.05926  -0.0425   0.2140   1.0000
  18.000   1.6391   0.06635   0.06093  -0.0423   0.2126   1.0000
  18.250   1.6487   0.06783   0.06242  -0.0421   0.2108   1.0000
  18.500   1.6641   0.06858   0.06315  -0.0418   0.2090   1.0000
  18.750   1.6731   0.07013   0.06476  -0.0416   0.2074   1.0000
  19.000   1.6718   0.07302   0.06777  -0.0417   0.2060   1.0000
  19.250   1.6692   0.07607   0.07093  -0.0418   0.2041   1.0000
<< Back to GOE 522 AIRFOIL (goe522-il)

Polar data table (+)

Polar graphs


<< Back to GOE 522 AIRFOIL (goe522-il)