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GOE 612 AIRFOIL (goe612-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 612 AIRFOIL (goe612-il)
Reynolds number: 500,000
Max Cl/Cd: 105.51 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe612-il-500000.txt
Download as CSV file: xf-goe612-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 612 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.5071   0.04666   0.04355  -0.1194   0.9798   0.0376
 -11.750  -0.5244   0.03704   0.03344  -0.1360   0.9708   0.0376
 -11.500  -0.5249   0.03360   0.02966  -0.1382   0.9625   0.0378
 -11.250  -0.5145   0.03100   0.02676  -0.1394   0.9560   0.0380
 -11.000  -0.5084   0.02934   0.02484  -0.1379   0.9470   0.0382
 -10.750  -0.4958   0.02784   0.02308  -0.1370   0.9402   0.0384
 -10.500  -0.4905   0.02560   0.02065  -0.1348   0.9311   0.0387
 -10.250  -0.4739   0.02415   0.01909  -0.1337   0.9250   0.0390
 -10.000  -0.4578   0.02317   0.01804  -0.1321   0.9175   0.0394
  -9.750  -0.4393   0.02226   0.01704  -0.1309   0.9104   0.0398
  -9.500  -0.4195   0.02151   0.01619  -0.1297   0.9038   0.0403
  -9.250  -0.4000   0.02078   0.01538  -0.1285   0.8955   0.0408
  -9.000  -0.3781   0.02001   0.01449  -0.1275   0.8891   0.0414
  -8.750  -0.3583   0.01925   0.01363  -0.1262   0.8799   0.0418
  -8.500  -0.3356   0.01848   0.01270  -0.1254   0.8730   0.0423
  -8.250  -0.3141   0.01781   0.01193  -0.1242   0.8634   0.0427
  -8.000  -0.2901   0.01721   0.01118  -0.1235   0.8557   0.0432
  -7.750  -0.2671   0.01672   0.01059  -0.1225   0.8455   0.0436
  -7.500  -0.2448   0.01572   0.00949  -0.1216   0.8370   0.0443
  -7.250  -0.2220   0.01510   0.00885  -0.1208   0.8268   0.0450
  -7.000  -0.1975   0.01465   0.00835  -0.1201   0.8184   0.0457
  -6.750  -0.1731   0.01427   0.00791  -0.1194   0.8090   0.0466
  -6.500  -0.1480   0.01392   0.00748  -0.1187   0.8009   0.0477
  -6.250  -0.1231   0.01358   0.00706  -0.1180   0.7920   0.0486
  -6.000  -0.0976   0.01329   0.00666  -0.1174   0.7845   0.0494
  -5.750  -0.0744   0.01274   0.00608  -0.1166   0.7764   0.0506
  -5.500  -0.0493   0.01240   0.00569  -0.1160   0.7698   0.0520
  -5.250  -0.0240   0.01213   0.00540  -0.1154   0.7632   0.0536
  -5.000   0.0019   0.01190   0.00510  -0.1148   0.7564   0.0552
  -4.750   0.0275   0.01161   0.00474  -0.1143   0.7506   0.0574
  -4.500   0.0528   0.01134   0.00448  -0.1137   0.7443   0.0604
  -4.250   0.0790   0.01116   0.00424  -0.1132   0.7379   0.0637
  -4.000   0.1048   0.01091   0.00398  -0.1127   0.7316   0.0693
  -3.750   0.1304   0.01067   0.00379  -0.1121   0.7250   0.0781
  -3.500   0.1566   0.01048   0.00363  -0.1116   0.7192   0.0946
  -3.250   0.1834   0.01034   0.00352  -0.1113   0.7138   0.1130
  -3.000   0.2095   0.01019   0.00341  -0.1108   0.7080   0.1277
  -2.750   0.2361   0.01007   0.00330  -0.1105   0.7025   0.1416
  -2.500   0.2633   0.00999   0.00322  -0.1102   0.6974   0.1566
  -2.250   0.2892   0.00984   0.00315  -0.1097   0.6919   0.1756
  -2.000   0.3153   0.00969   0.00309  -0.1092   0.6862   0.2028
  -1.750   0.3420   0.00961   0.00304  -0.1089   0.6805   0.2345
  -1.500   0.3681   0.00951   0.00303  -0.1084   0.6750   0.2647
  -1.250   0.3943   0.00942   0.00303  -0.1080   0.6696   0.2923
  -1.000   0.4213   0.00939   0.00302  -0.1076   0.6647   0.3184
  -0.750   0.4481   0.00937   0.00304  -0.1073   0.6598   0.3416
  -0.500   0.4743   0.00932   0.00306  -0.1068   0.6545   0.3636
  -0.250   0.5009   0.00930   0.00307  -0.1064   0.6495   0.3826
   0.000   0.5281   0.00932   0.00307  -0.1061   0.6447   0.3996
   0.250   0.5542   0.00928   0.00309  -0.1056   0.6394   0.4162
   0.500   0.5801   0.00925   0.00310  -0.1050   0.6334   0.4335
   0.750   0.6065   0.00926   0.00310  -0.1046   0.6278   0.4521
   1.000   0.6320   0.00922   0.00313  -0.1040   0.6222   0.4726
   1.250   0.6571   0.00916   0.00316  -0.1033   0.6159   0.4978
   1.500   0.6819   0.00911   0.00317  -0.1026   0.6096   0.5342
   1.750   0.7043   0.00892   0.00322  -0.1014   0.6025   0.5951
   2.000   0.7963   0.00824   0.00342  -0.1148   0.5923   0.9804
   2.250   0.8404   0.00834   0.00350  -0.1183   0.5824   1.0000
   2.500   0.8624   0.00845   0.00352  -0.1170   0.5733   1.0000
   2.750   0.8845   0.00853   0.00358  -0.1157   0.5623   1.0000
   3.000   0.9060   0.00865   0.00364  -0.1143   0.5506   1.0000
   3.250   0.9262   0.00879   0.00370  -0.1126   0.5363   1.0000
   3.500   0.9454   0.00896   0.00379  -0.1108   0.5186   1.0000
   3.750   0.9631   0.00918   0.00390  -0.1087   0.4964   1.0000
   4.000   0.9769   0.00950   0.00406  -0.1059   0.4674   1.0000
   4.250   0.9876   0.00994   0.00429  -0.1025   0.4337   1.0000
   4.750   1.0095   0.01083   0.00486  -0.0960   0.3822   1.0000
   5.000   1.0202   0.01120   0.00512  -0.0927   0.3669   1.0000
   5.250   1.0322   0.01155   0.00539  -0.0897   0.3551   1.0000
   5.500   1.0471   0.01186   0.00565  -0.0872   0.3454   1.0000
   5.750   1.0608   0.01223   0.00595  -0.0847   0.3369   1.0000
   6.000   1.0782   0.01252   0.00622  -0.0828   0.3295   1.0000
   6.250   1.0939   0.01288   0.00654  -0.0807   0.3223   1.0000
   6.500   1.1106   0.01324   0.00687  -0.0788   0.3163   1.0000
   6.750   1.1292   0.01354   0.00717  -0.0772   0.3106   1.0000
   7.000   1.1455   0.01394   0.00753  -0.0754   0.3049   1.0000
   7.250   1.1624   0.01433   0.00791  -0.0737   0.2997   1.0000
   7.500   1.1818   0.01464   0.00824  -0.0724   0.2947   1.0000
   7.750   1.1990   0.01504   0.00862  -0.0708   0.2895   1.0000
   8.000   1.2139   0.01557   0.00910  -0.0689   0.2843   1.0000
   8.250   1.2340   0.01587   0.00946  -0.0678   0.2798   1.0000
   8.500   1.2520   0.01627   0.00987  -0.0665   0.2745   1.0000
   8.750   1.2671   0.01682   0.01038  -0.0648   0.2692   1.0000
   9.000   1.2852   0.01725   0.01084  -0.0635   0.2643   1.0000
   9.250   1.3030   0.01769   0.01131  -0.0623   0.2588   1.0000
   9.500   1.3180   0.01830   0.01189  -0.0607   0.2535   1.0000
   9.750   1.3346   0.01884   0.01245  -0.0594   0.2485   1.0000
  10.000   1.3517   0.01936   0.01300  -0.0583   0.2429   1.0000
  10.250   1.3657   0.02007   0.01369  -0.0567   0.2372   1.0000
  10.500   1.3815   0.02070   0.01435  -0.0555   0.2317   1.0000
  10.750   1.3970   0.02136   0.01503  -0.0543   0.2255   1.0000
  11.000   1.4078   0.02231   0.01595  -0.0526   0.2193   1.0000
  11.250   1.4245   0.02295   0.01664  -0.0516   0.2130   1.0000
  11.500   1.4351   0.02398   0.01763  -0.0501   0.2056   1.0000
  11.750   1.4490   0.02483   0.01850  -0.0490   0.1985   1.0000
  12.000   1.4588   0.02596   0.01961  -0.0476   0.1915   1.0000
  12.250   1.4709   0.02698   0.02065  -0.0464   0.1850   1.0000
  12.500   1.4808   0.02817   0.02184  -0.0452   0.1786   1.0000
  12.750   1.4902   0.02944   0.02310  -0.0439   0.1731   1.0000
  13.000   1.5017   0.03057   0.02428  -0.0429   0.1684   1.0000
  13.250   1.5095   0.03201   0.02571  -0.0417   0.1636   1.0000
  13.500   1.5179   0.03343   0.02715  -0.0406   0.1597   1.0000
  13.750   1.5293   0.03464   0.02842  -0.0397   0.1557   1.0000
  14.000   1.5374   0.03613   0.02993  -0.0387   0.1518   1.0000
  14.250   1.5421   0.03795   0.03174  -0.0376   0.1481   1.0000
  14.500   1.5528   0.03927   0.03313  -0.0369   0.1450   1.0000
  14.750   1.5622   0.04074   0.03466  -0.0361   0.1424   1.0000
  15.000   1.5695   0.04239   0.03635  -0.0353   0.1393   1.0000
  15.250   1.5735   0.04437   0.03835  -0.0345   0.1362   1.0000
  15.500   1.5787   0.04626   0.04027  -0.0337   0.1336   1.0000
  15.750   1.5888   0.04775   0.04185  -0.0332   0.1314   1.0000
  16.000   1.5958   0.04954   0.04371  -0.0327   0.1285   1.0000
  16.250   1.6007   0.05155   0.04576  -0.0322   0.1258   1.0000
  16.500   1.6018   0.05398   0.04821  -0.0316   0.1231   1.0000
  16.750   1.6065   0.05606   0.05036  -0.0312   0.1209   1.0000
  17.000   1.6140   0.05793   0.05233  -0.0310   0.1180   1.0000
  17.250   1.6179   0.06017   0.05463  -0.0307   0.1152   1.0000
  17.500   1.6181   0.06285   0.05735  -0.0305   0.1125   1.0000
  17.750   1.6159   0.06583   0.06037  -0.0303   0.1094   1.0000
  18.000   1.6223   0.06790   0.06255  -0.0302   0.1062   1.0000
  18.250   1.6206   0.07097   0.06566  -0.0303   0.1021   1.0000
  18.500   1.6138   0.07467   0.06939  -0.0305   0.0985   1.0000
  18.750   1.6162   0.07730   0.07212  -0.0307   0.0936   1.0000
  19.000   1.6067   0.08146   0.07631  -0.0311   0.0887   1.0000
  19.250   1.6013   0.08516   0.08008  -0.0316   0.0817   1.0000
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