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GOE 358 AIRFOIL (goe358-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 358 AIRFOIL (goe358-il)
Reynolds number: 100,000
Max Cl/Cd: 61.77 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe358-il-100000-n5.txt
Download as CSV file: xf-goe358-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 358 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3404   0.09521   0.09016  -0.0387   1.0000   0.0448
  -8.500  -0.3506   0.09203   0.08707  -0.0383   1.0000   0.0457
  -8.250  -0.3649   0.08895   0.08409  -0.0372   1.0000   0.0464
  -8.000  -0.3833   0.08612   0.08136  -0.0355   1.0000   0.0467
  -7.750  -0.4002   0.08230   0.07765  -0.0353   1.0000   0.0471
  -7.250  -0.4020   0.06876   0.06419  -0.0483   0.9946   0.0495
  -6.750  -0.2882   0.03320   0.02657  -0.1148   0.9833   0.0607
  -6.500  -0.2534   0.03142   0.02476  -0.1180   0.9790   0.0641
  -6.250  -0.2125   0.02947   0.02247  -0.1226   0.9757   0.0684
  -6.000  -0.1733   0.02744   0.01984  -0.1267   0.9706   0.0726
  -5.750  -0.1345   0.02569   0.01785  -0.1301   0.9667   0.0758
  -5.500  -0.0983   0.02465   0.01670  -0.1324   0.9617   0.0792
  -5.250  -0.0607   0.02364   0.01548  -0.1348   0.9563   0.0829
  -5.000  -0.0216   0.02262   0.01421  -0.1374   0.9519   0.0855
  -4.750   0.0136   0.02182   0.01321  -0.1390   0.9451   0.0880
  -4.500   0.0531   0.02099   0.01243  -0.1415   0.9412   0.0920
  -4.250   0.0856   0.02042   0.01181  -0.1425   0.9329   0.0951
  -4.000   0.1252   0.01981   0.01111  -0.1448   0.9284   0.0984
  -3.750   0.1576   0.01935   0.01055  -0.1456   0.9197   0.1017
  -3.500   0.1960   0.01875   0.00996  -0.1477   0.9141   0.1066
  -3.250   0.2286   0.01829   0.00944  -0.1484   0.9033   0.1145
  -3.000   0.2648   0.01767   0.00882  -0.1499   0.8930   0.1280
  -2.750   0.3018   0.01694   0.00815  -0.1515   0.8822   0.1541
  -2.500   0.3334   0.01641   0.00786  -0.1522   0.8686   0.2068
  -2.250   0.3646   0.01630   0.00783  -0.1524   0.8563   0.2600
  -2.000   0.3975   0.01624   0.00767  -0.1529   0.8458   0.2900
  -1.750   0.4281   0.01627   0.00765  -0.1529   0.8337   0.3114
  -1.500   0.4580   0.01636   0.00768  -0.1529   0.8207   0.3317
  -1.250   0.4884   0.01646   0.00771  -0.1528   0.8079   0.3500
  -1.000   0.5186   0.01654   0.00774  -0.1527   0.7950   0.3662
  -0.750   0.5487   0.01659   0.00773  -0.1526   0.7816   0.3800
  -0.500   0.5785   0.01659   0.00762  -0.1526   0.7673   0.3913
  -0.250   0.6074   0.01660   0.00756  -0.1523   0.7525   0.4004
   0.000   0.6361   0.01661   0.00750  -0.1521   0.7377   0.4092
   0.250   0.6646   0.01664   0.00744  -0.1519   0.7230   0.4176
   0.500   0.6928   0.01664   0.00737  -0.1517   0.7078   0.4238
   0.750   0.7205   0.01667   0.00734  -0.1514   0.6921   0.4292
   1.000   0.7483   0.01671   0.00728  -0.1511   0.6756   0.4348
   1.250   0.7754   0.01675   0.00727  -0.1507   0.6586   0.4397
   1.500   0.8022   0.01682   0.00730  -0.1502   0.6411   0.4452
   1.750   0.8291   0.01692   0.00732  -0.1498   0.6234   0.4514
   2.000   0.8558   0.01701   0.00737  -0.1494   0.6060   0.4562
   2.250   0.8824   0.01714   0.00745  -0.1489   0.5888   0.4618
   2.500   0.9090   0.01731   0.00752  -0.1484   0.5722   0.4686
   2.750   0.9350   0.01747   0.00765  -0.1479   0.5563   0.4744
   3.000   0.9612   0.01767   0.00780  -0.1474   0.5412   0.4813
   3.250   0.9871   0.01789   0.00797  -0.1468   0.5268   0.4877
   3.500   1.0128   0.01812   0.00819  -0.1463   0.5131   0.4950
   3.750   1.0385   0.01838   0.00841  -0.1457   0.5004   0.5032
   4.000   1.0639   0.01864   0.00867  -0.1452   0.4882   0.5120
   4.250   1.0894   0.01889   0.00898  -0.1446   0.4769   0.5212
   4.500   1.1149   0.01918   0.00927  -0.1441   0.4674   0.5320
   4.750   1.1403   0.01944   0.00963  -0.1436   0.4585   0.5439
   5.000   1.1658   0.01972   0.01000  -0.1431   0.4511   0.5588
   5.250   1.1910   0.01998   0.01041  -0.1425   0.4426   0.5787
   5.500   1.2159   0.02022   0.01079  -0.1419   0.4354   0.6104
   5.750   1.2366   0.02002   0.01115  -0.1404   0.4275   1.0000
   6.000   1.2621   0.02047   0.01154  -0.1399   0.4205   1.0000
   6.250   1.2867   0.02089   0.01206  -0.1393   0.4119   1.0000
   6.500   1.3110   0.02134   0.01249  -0.1386   0.4036   1.0000
   6.750   1.3339   0.02175   0.01300  -0.1377   0.3926   1.0000
   7.000   1.3564   0.02219   0.01348  -0.1367   0.3814   1.0000
   7.250   1.3787   0.02265   0.01396  -0.1357   0.3714   1.0000
   7.500   1.4000   0.02309   0.01455  -0.1345   0.3594   1.0000
   7.750   1.4206   0.02357   0.01511  -0.1332   0.3469   1.0000
   8.000   1.4405   0.02407   0.01568  -0.1318   0.3341   1.0000
   8.250   1.4598   0.02460   0.01631  -0.1304   0.3218   1.0000
   8.500   1.4773   0.02514   0.01697  -0.1286   0.3054   1.0000
   8.750   1.4927   0.02572   0.01768  -0.1266   0.2808   1.0000
   9.000   1.5046   0.02647   0.01841  -0.1242   0.2412   1.0000
   9.250   1.5068   0.02785   0.01940  -0.1206   0.1897   1.0000
   9.500   1.5063   0.02954   0.02087  -0.1167   0.1644   1.0000
   9.750   1.5073   0.03118   0.02246  -0.1131   0.1454   1.0000
  10.000   1.5096   0.03282   0.02411  -0.1099   0.1266   1.0000
  10.250   1.5120   0.03450   0.02581  -0.1070   0.1074   1.0000
  10.500   1.5112   0.03648   0.02775  -0.1040   0.0931   1.0000
  10.750   1.5084   0.03872   0.02997  -0.1012   0.0832   1.0000
  11.000   1.5039   0.04122   0.03250  -0.0986   0.0758   1.0000
  11.250   1.5003   0.04381   0.03519  -0.0964   0.0696   1.0000
  11.500   1.4931   0.04689   0.03832  -0.0945   0.0647   1.0000
  11.750   1.4885   0.04993   0.04150  -0.0930   0.0602   1.0000
  12.000   1.4825   0.05327   0.04499  -0.0918   0.0563   1.0000
  12.250   1.4727   0.05720   0.04897  -0.0909   0.0535   1.0000
  12.500   1.4692   0.06056   0.05251  -0.0902   0.0501   1.0000
  12.750   1.4643   0.06418   0.05628  -0.0898   0.0470   1.0000
  13.000   1.4576   0.06811   0.06031  -0.0896   0.0448   1.0000
  13.250   1.4490   0.07234   0.06460  -0.0895   0.0430   1.0000
  13.500   1.4461   0.07593   0.06834  -0.0893   0.0410   1.0000
  13.750   1.4433   0.07959   0.07215  -0.0893   0.0389   1.0000
  14.000   1.4398   0.08341   0.07610  -0.0895   0.0371   1.0000
  14.250   1.4359   0.08737   0.08017  -0.0898   0.0356   1.0000
  14.500   1.4316   0.09142   0.08430  -0.0903   0.0344   1.0000
  14.750   1.4277   0.09528   0.08818  -0.0905   0.0332   1.0000
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