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GOE 395 AIRFOIL (goe395-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 395 AIRFOIL (goe395-il)
Reynolds number: 200,000
Max Cl/Cd: 102.82 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe395-il-200000.txt
Download as CSV file: xf-goe395-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 395 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.1741   0.09469   0.09124  -0.0537   0.9230   0.0386
  -7.750  -0.1644   0.09229   0.08882  -0.0556   0.9148   0.0407
  -7.500  -0.1551   0.09157   0.08808  -0.0615   0.9062   0.0423
  -7.250  -0.1351   0.09004   0.08651  -0.0718   0.8992   0.0427
  -7.000  -0.1273   0.08490   0.08137  -0.0700   0.8962   0.0432
  -6.750  -0.1170   0.08114   0.07760  -0.0673   0.8932   0.0441
  -6.500  -0.1021   0.07839   0.07484  -0.0685   0.8894   0.0454
  -6.250  -0.0849   0.07578   0.07221  -0.0712   0.8858   0.0474
  -6.000  -0.0412   0.07416   0.07047  -0.0877   0.8815   0.0524
  -5.750  -0.0162   0.06973   0.06601  -0.0942   0.8781   0.0531
  -5.500  -0.0093   0.06630   0.06260  -0.0906   0.8754   0.0539
  -5.250   0.0068   0.06368   0.05998  -0.0906   0.8728   0.0553
  -5.000   0.0298   0.06116   0.05742  -0.0936   0.8703   0.0577
  -4.750   0.1056   0.05789   0.05389  -0.1161   0.8677   0.0641
  -4.500   0.1118   0.05415   0.05017  -0.1130   0.8660   0.0650
  -4.250   0.1282   0.05179   0.04783  -0.1124   0.8639   0.0663
  -4.000   0.1529   0.04958   0.04560  -0.1145   0.8612   0.0686
  -3.750   0.2317   0.04609   0.04171  -0.1333   0.8587   0.0769
  -3.500   0.2451   0.04287   0.03857  -0.1322   0.8568   0.0780
  -3.250   0.2661   0.04091   0.03660  -0.1323   0.8546   0.0795
  -3.000   0.2933   0.03898   0.03460  -0.1338   0.8519   0.0821
  -2.500   0.3736   0.03354   0.02878  -0.1440   0.8437   0.0929
  -2.250   0.3997   0.03198   0.02717  -0.1447   0.8400   0.0953
  -2.000   0.4327   0.03019   0.02521  -0.1466   0.8367   0.1004
  -1.750   0.4882   0.02347   0.01757  -0.1536   0.8336   0.0745
  -1.500   0.5213   0.02139   0.01510  -0.1552   0.8296   0.0751
  -1.250   0.5529   0.01971   0.01299  -0.1560   0.8261   0.0759
  -1.000   0.5830   0.01821   0.01114  -0.1564   0.8229   0.0782
  -0.750   0.6108   0.01773   0.01059  -0.1562   0.8198   0.0824
  -0.500   0.6391   0.01741   0.01008  -0.1563   0.8150   0.0900
  -0.250   0.6664   0.01705   0.00973  -0.1561   0.8106   0.1008
   0.000   0.6942   0.01662   0.00921  -0.1558   0.8069   0.1131
   0.250   0.7215   0.01644   0.00898  -0.1555   0.8028   0.1244
   0.500   0.7483   0.01641   0.00894  -0.1553   0.7975   0.1361
   0.750   0.7753   0.01631   0.00884  -0.1549   0.7931   0.1470
   1.000   0.8027   0.01602   0.00854  -0.1544   0.7894   0.1530
   1.250   0.8291   0.01596   0.00855  -0.1541   0.7831   0.1582
   1.500   0.8563   0.01578   0.00836  -0.1536   0.7781   0.1648
   1.750   0.8834   0.01558   0.00822  -0.1531   0.7736   0.1722
   2.000   0.9096   0.01553   0.00825  -0.1527   0.7665   0.1795
   2.250   0.9369   0.01530   0.00808  -0.1521   0.7613   0.1905
   2.500   0.9632   0.01522   0.00814  -0.1516   0.7544   0.2075
   2.750   0.9900   0.01487   0.00804  -0.1510   0.7475   0.2656
   3.000   1.0129   0.01371   0.00799  -0.1495   0.7399   1.0000
   3.250   1.0397   0.01358   0.00777  -0.1486   0.7313   1.0000
   3.500   1.0656   0.01355   0.00774  -0.1478   0.7213   1.0000
   3.750   1.0931   0.01340   0.00752  -0.1471   0.7140   1.0000
   4.000   1.1187   0.01335   0.00751  -0.1463   0.7024   1.0000
   4.250   1.1448   0.01323   0.00741  -0.1455   0.6907   1.0000
   4.500   1.1710   0.01307   0.00728  -0.1447   0.6784   1.0000
   4.750   1.1969   0.01290   0.00714  -0.1439   0.6636   1.0000
   5.000   1.2225   0.01274   0.00704  -0.1431   0.6452   1.0000
   5.250   1.2477   0.01257   0.00692  -0.1422   0.6194   1.0000
   5.500   1.2724   0.01245   0.00671  -0.1411   0.5845   1.0000
   5.750   1.2955   0.01260   0.00663  -0.1398   0.5479   1.0000
   6.000   1.3172   0.01309   0.00687  -0.1385   0.5148   1.0000
   6.250   1.3393   0.01367   0.00733  -0.1374   0.4892   1.0000
   6.500   1.3610   0.01426   0.00782  -0.1363   0.4647   1.0000
   6.750   1.3822   0.01482   0.00834  -0.1352   0.4374   1.0000
   7.000   1.4018   0.01547   0.00888  -0.1338   0.4050   1.0000
   7.250   1.4202   0.01616   0.00947  -0.1324   0.3677   1.0000
   7.500   1.4368   0.01698   0.01015  -0.1307   0.3273   1.0000
   7.750   1.4507   0.01800   0.01096  -0.1287   0.2742   1.0000
   8.000   1.4587   0.01951   0.01202  -0.1261   0.2038   1.0000
   8.250   1.4662   0.02108   0.01325  -0.1234   0.1593   1.0000
   8.500   1.4763   0.02237   0.01442  -0.1211   0.1350   1.0000
   8.750   1.4848   0.02364   0.01561  -0.1185   0.1155   1.0000
   9.000   1.4928   0.02489   0.01682  -0.1158   0.0901   1.0000
   9.250   1.4927   0.02685   0.01851  -0.1124   0.0587   1.0000
   9.500   1.4924   0.02893   0.02053  -0.1091   0.0458   1.0000
   9.750   1.4922   0.03108   0.02269  -0.1061   0.0405   1.0000
  10.000   1.4982   0.03278   0.02451  -0.1038   0.0369   1.0000
  10.250   1.5019   0.03473   0.02652  -0.1016   0.0344   1.0000
  10.500   1.4990   0.03738   0.02921  -0.0989   0.0325   1.0000
  10.750   1.5057   0.03919   0.03115  -0.0970   0.0310   1.0000
  11.000   1.5120   0.04107   0.03316  -0.0952   0.0293   1.0000
  11.250   1.5173   0.04305   0.03522  -0.0935   0.0278   1.0000
  11.500   1.5215   0.04520   0.03743  -0.0916   0.0268   1.0000
  11.750   1.5252   0.04754   0.03982  -0.0895   0.0259   1.0000
  12.000   1.5327   0.05010   0.04241  -0.0868   0.0251   1.0000
  12.250   1.5419   0.05216   0.04466  -0.0851   0.0247   1.0000
  12.500   1.5507   0.05442   0.04712  -0.0832   0.0242   1.0000
  12.750   1.5578   0.05690   0.04983  -0.0815   0.0238   1.0000
  13.000   1.5616   0.05959   0.05274  -0.0798   0.0232   1.0000
  13.250   1.5628   0.06246   0.05583  -0.0783   0.0226   1.0000
  13.500   1.5622   0.06549   0.05906  -0.0770   0.0220   1.0000
  13.750   1.5599   0.06881   0.06259  -0.0757   0.0216   1.0000
  14.000   1.5546   0.07266   0.06670  -0.0745   0.0215   1.0000
  14.250   1.5458   0.07692   0.07122  -0.0736   0.0214   1.0000
  14.500   1.5334   0.08167   0.07625  -0.0731   0.0214   1.0000
  14.750   1.5175   0.08698   0.08184  -0.0730   0.0215   1.0000
  15.000   1.4987   0.09287   0.08803  -0.0737   0.0216   1.0000
  15.250   1.4783   0.09939   0.09482  -0.0752   0.0217   1.0000
  15.500   1.4562   0.10665   0.10236  -0.0777   0.0219   1.0000
  15.750   1.4331   0.11466   0.11064  -0.0814   0.0222   1.0000
  16.000   1.4098   0.12342   0.11964  -0.0862   0.0224   1.0000
  16.250   1.3859   0.13305   0.12950  -0.0920   0.0227   1.0000
  16.500   1.3613   0.14372   0.14038  -0.0992   0.0230   1.0000
  16.750   1.3356   0.15566   0.15250  -0.1076   0.0234   1.0000
  17.000   1.3078   0.16963   0.16659  -0.1176   0.0240   1.0000
  17.250   1.2835   0.18390   0.18092  -0.1271   0.0247   1.0000
  17.500   0.9307   0.19265   0.18984  -0.1031   0.0423   1.0000
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