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

GOE 797 AIRFOIL (goe797-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 797 AIRFOIL (goe797-il)
Reynolds number: 500,000
Max Cl/Cd: 108.23 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe797-il-500000.txt
Download as CSV file: xf-goe797-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 797 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
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.8219   0.04332   0.03972  -0.1132   0.9946   0.0393
 -13.500  -0.8187   0.03948   0.03570  -0.1182   0.9902   0.0396
 -13.250  -0.8113   0.03691   0.03297  -0.1205   0.9852   0.0400
 -13.000  -0.7949   0.03463   0.03051  -0.1228   0.9823   0.0405
 -12.750  -0.7792   0.03258   0.02827  -0.1241   0.9785   0.0409
 -12.500  -0.7626   0.03071   0.02621  -0.1249   0.9737   0.0414
 -12.250  -0.7415   0.02896   0.02425  -0.1260   0.9703   0.0420
 -12.000  -0.7206   0.02752   0.02259  -0.1265   0.9663   0.0424
 -11.750  -0.7033   0.02646   0.02133  -0.1257   0.9596   0.0428
 -11.500  -0.6845   0.02466   0.01940  -0.1256   0.9550   0.0434
 -11.250  -0.6644   0.02378   0.01850  -0.1248   0.9491   0.0440
 -11.000  -0.6429   0.02310   0.01779  -0.1241   0.9427   0.0447
 -10.750  -0.6204   0.02242   0.01703  -0.1235   0.9376   0.0454
 -10.500  -0.6002   0.02171   0.01623  -0.1225   0.9297   0.0460
 -10.250  -0.5784   0.02097   0.01536  -0.1217   0.9233   0.0468
 -10.000  -0.5561   0.02029   0.01454  -0.1209   0.9164   0.0475
  -9.750  -0.5331   0.01970   0.01380  -0.1202   0.9089   0.0481
  -9.500  -0.5112   0.01868   0.01268  -0.1195   0.9023   0.0489
  -9.250  -0.4879   0.01802   0.01200  -0.1189   0.8935   0.0498
  -9.000  -0.4629   0.01754   0.01147  -0.1184   0.8864   0.0508
  -8.750  -0.4379   0.01710   0.01097  -0.1180   0.8768   0.0519
  -8.500  -0.4122   0.01667   0.01041  -0.1176   0.8692   0.0531
  -8.250  -0.3862   0.01629   0.00992  -0.1173   0.8593   0.0540
  -8.000  -0.3617   0.01553   0.00910  -0.1169   0.8511   0.0554
  -7.750  -0.3356   0.01511   0.00866  -0.1166   0.8409   0.0567
  -7.500  -0.3090   0.01478   0.00825  -0.1164   0.8324   0.0582
  -7.250  -0.2820   0.01446   0.00784  -0.1163   0.8228   0.0598
  -7.000  -0.2553   0.01406   0.00734  -0.1161   0.8149   0.0615
  -6.750  -0.2286   0.01367   0.00696  -0.1160   0.8064   0.0636
  -6.250  -0.1731   0.01324   0.00637  -0.1159   0.7914   0.0678
  -6.000  -0.1463   0.01284   0.00594  -0.1158   0.7844   0.0706
  -5.750  -0.1183   0.01264   0.00572  -0.1159   0.7781   0.0734
  -5.500  -0.0899   0.01250   0.00550  -0.1159   0.7718   0.0761
  -5.250  -0.0624   0.01221   0.00522  -0.1159   0.7662   0.0801
  -5.000  -0.0338   0.01210   0.00505  -0.1161   0.7608   0.0840
  -4.750  -0.0058   0.01186   0.00483  -0.1161   0.7552   0.0884
  -4.500   0.0228   0.01177   0.00470  -0.1163   0.7501   0.0933
  -4.250   0.0514   0.01164   0.00455  -0.1164   0.7456   0.0988
  -4.000   0.0802   0.01156   0.00448  -0.1166   0.7406   0.1046
  -3.750   0.1086   0.01142   0.00435  -0.1167   0.7352   0.1108
  -3.500   0.1375   0.01144   0.00430  -0.1168   0.7297   0.1169
  -3.250   0.1660   0.01131   0.00420  -0.1170   0.7246   0.1230
  -3.000   0.1948   0.01127   0.00416  -0.1171   0.7194   0.1290
  -2.750   0.2236   0.01120   0.00405  -0.1173   0.7148   0.1346
  -2.500   0.2524   0.01116   0.00398  -0.1175   0.7101   0.1407
  -2.250   0.2812   0.01111   0.00394  -0.1177   0.7053   0.1460
  -2.000   0.3096   0.01096   0.00381  -0.1178   0.7004   0.1521
  -1.750   0.3383   0.01090   0.00373  -0.1179   0.6956   0.1582
  -1.500   0.3673   0.01091   0.00369  -0.1181   0.6911   0.1635
  -1.250   0.3954   0.01074   0.00359  -0.1182   0.6860   0.1711
  -1.000   0.4240   0.01066   0.00352  -0.1184   0.6810   0.1784
  -0.750   0.4527   0.01060   0.00345  -0.1185   0.6766   0.1875
  -0.500   0.4814   0.01055   0.00342  -0.1187   0.6723   0.1983
  -0.250   0.5097   0.01042   0.00339  -0.1189   0.6678   0.2151
   0.000   0.5380   0.01027   0.00337  -0.1191   0.6633   0.2465
   0.250   0.5661   0.01007   0.00336  -0.1192   0.6592   0.3133
   0.500   0.5934   0.00973   0.00340  -0.1194   0.6551   0.4354
   0.750   0.6182   0.00914   0.00348  -0.1191   0.6506   0.6347
   1.000   0.6396   0.00868   0.00360  -0.1174   0.6461   0.8143
   1.250   0.6615   0.00856   0.00369  -0.1155   0.6417   0.9169
   1.500   0.6967   0.00862   0.00373  -0.1167   0.6370   0.9666
   1.750   0.7406   0.00866   0.00378  -0.1202   0.6312   0.9902
   2.000   0.7880   0.00874   0.00380  -0.1245   0.6252   0.9999
   2.250   0.8125   0.00882   0.00380  -0.1238   0.6198   1.0000
   2.500   0.8367   0.00885   0.00384  -0.1231   0.6138   1.0000
   2.750   0.8611   0.00891   0.00386  -0.1224   0.6077   1.0000
   3.000   0.8859   0.00900   0.00389  -0.1218   0.6016   1.0000
   3.250   0.9109   0.00906   0.00395  -0.1212   0.5944   1.0000
   3.500   0.9359   0.00916   0.00399  -0.1207   0.5873   1.0000
   3.750   0.9613   0.00924   0.00407  -0.1202   0.5793   1.0000
   4.000   0.9859   0.00936   0.00412  -0.1196   0.5701   1.0000
   4.250   1.0106   0.00946   0.00421  -0.1190   0.5587   1.0000
   4.500   1.0345   0.00960   0.00430  -0.1183   0.5459   1.0000
   4.750   1.0577   0.00978   0.00441  -0.1174   0.5314   1.0000
   5.000   1.0801   0.00998   0.00455  -0.1164   0.5146   1.0000
   5.250   1.1015   0.01024   0.00473  -0.1152   0.4957   1.0000
   5.500   1.1214   0.01055   0.00494  -0.1137   0.4745   1.0000
   5.750   1.1393   0.01095   0.00521  -0.1119   0.4526   1.0000
   6.000   1.1567   0.01137   0.00551  -0.1101   0.4330   1.0000
   6.500   1.1923   0.01214   0.00614  -0.1066   0.4035   1.0000
   6.750   1.2085   0.01252   0.00647  -0.1045   0.3926   1.0000
   7.000   1.2230   0.01299   0.00686  -0.1022   0.3822   1.0000
   7.250   1.2417   0.01334   0.00720  -0.1007   0.3735   1.0000
   7.500   1.2583   0.01380   0.00762  -0.0988   0.3664   1.0000
   7.750   1.2780   0.01415   0.00798  -0.0976   0.3602   1.0000
   8.000   1.2963   0.01458   0.00839  -0.0961   0.3538   1.0000
   8.250   1.3127   0.01510   0.00888  -0.0944   0.3480   1.0000
   8.500   1.3337   0.01543   0.00926  -0.0935   0.3433   1.0000
   8.750   1.3522   0.01588   0.00971  -0.0922   0.3381   1.0000
   9.000   1.3685   0.01644   0.01025  -0.0906   0.3327   1.0000
   9.250   1.3878   0.01687   0.01072  -0.0896   0.3281   1.0000
   9.500   1.4067   0.01733   0.01121  -0.0885   0.3229   1.0000
   9.750   1.4229   0.01792   0.01179  -0.0870   0.3175   1.0000
  10.000   1.4395   0.01851   0.01240  -0.0856   0.3123   1.0000
  10.250   1.4582   0.01900   0.01294  -0.0846   0.3065   1.0000
  10.500   1.4730   0.01970   0.01364  -0.0831   0.3004   1.0000
  10.750   1.4893   0.02034   0.01432  -0.0819   0.2944   1.0000
  11.000   1.5055   0.02099   0.01501  -0.0807   0.2870   1.0000
  11.250   1.5183   0.02187   0.01587  -0.0791   0.2793   1.0000
  11.500   1.5337   0.02261   0.01666  -0.0779   0.2698   1.0000
  11.750   1.5463   0.02356   0.01760  -0.0765   0.2593   1.0000
  12.000   1.5562   0.02469   0.01871  -0.0748   0.2467   1.0000
  12.250   1.5648   0.02598   0.01996  -0.0731   0.2315   1.0000
  12.500   1.5704   0.02751   0.02143  -0.0713   0.2137   1.0000
  12.750   1.5725   0.02935   0.02319  -0.0692   0.1966   1.0000
  13.000   1.5742   0.03128   0.02506  -0.0672   0.1839   1.0000
  13.250   1.5757   0.03332   0.02705  -0.0654   0.1742   1.0000
  13.500   1.5816   0.03505   0.02880  -0.0640   0.1670   1.0000
  13.750   1.5834   0.03716   0.03090  -0.0624   0.1607   1.0000
  14.000   1.5922   0.03871   0.03249  -0.0614   0.1557   1.0000
  14.250   1.5959   0.04075   0.03455  -0.0601   0.1504   1.0000
  14.500   1.6003   0.04275   0.03657  -0.0590   0.1456   1.0000
  14.750   1.6086   0.04443   0.03832  -0.0581   0.1412   1.0000
  15.000   1.6120   0.04659   0.04050  -0.0571   0.1367   1.0000
  15.250   1.6158   0.04873   0.04268  -0.0561   0.1323   1.0000
  15.500   1.6232   0.05058   0.04459  -0.0555   0.1277   1.0000
  15.750   1.6255   0.05296   0.04699  -0.0546   0.1232   1.0000
  16.000   1.6290   0.05526   0.04933  -0.0539   0.1193   1.0000
  16.250   1.6348   0.05733   0.05147  -0.0534   0.1153   1.0000
  16.500   1.6360   0.05992   0.05409  -0.0527   0.1112   1.0000
  16.750   1.6371   0.06258   0.05679  -0.0522   0.1076   1.0000
  17.000   1.6412   0.06493   0.05921  -0.0518   0.1034   1.0000
  17.250   1.6396   0.06799   0.06229  -0.0514   0.0993   1.0000
  17.500   1.6399   0.07083   0.06520  -0.0511   0.0955   1.0000
  17.750   1.6396   0.07377   0.06819  -0.0509   0.0911   1.0000
  18.000   1.6345   0.07736   0.07181  -0.0507   0.0871   1.0000
  18.250   1.6337   0.08047   0.07499  -0.0507   0.0828   1.0000
  18.500   1.6268   0.08440   0.07894  -0.0507   0.0786   1.0000
  18.750   1.6237   0.08785   0.08246  -0.0509   0.0742   1.0000
  19.000   1.6142   0.09218   0.08683  -0.0512   0.0699   1.0000
  19.250   1.6078   0.09619   0.09090  -0.0517   0.0652   1.0000
<< Back to GOE 797 AIRFOIL (goe797-il)

Polar data table (+)

Polar graphs


<< Back to GOE 797 AIRFOIL (goe797-il)