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GOE 395 AIRFOIL (goe395-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 395 AIRFOIL (goe395-il)
Reynolds number: 500,000
Max Cl/Cd: 149.87 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe395-il-500000.txt
Download as CSV file: xf-goe395-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2429   0.10139   0.09850  -0.0379   0.8098   0.0214
  -8.250  -0.2350   0.09849   0.09558  -0.0406   0.8067   0.0215
  -8.000  -0.2254   0.09537   0.09244  -0.0432   0.8039   0.0215
  -7.750  -0.2155   0.09087   0.08794  -0.0419   0.8020   0.0220
  -7.500  -0.2036   0.08836   0.08542  -0.0427   0.7997   0.0224
  -7.250  -0.1920   0.08595   0.08301  -0.0442   0.7973   0.0230
  -7.000  -0.1786   0.08334   0.08040  -0.0466   0.7951   0.0238
  -6.750  -0.1626   0.08041   0.07744  -0.0500   0.7931   0.0250
  -6.500  -0.1319   0.07661   0.07359  -0.0624   0.7908   0.0270
  -6.250  -0.1069   0.07280   0.06975  -0.0688   0.7891   0.0271
  -6.000  -0.0966   0.06830   0.06527  -0.0692   0.7876   0.0278
  -5.750  -0.0784   0.06604   0.06300  -0.0703   0.7860   0.0284
  -5.500  -0.0560   0.06357   0.06051  -0.0733   0.7842   0.0294
  -5.250  -0.0295   0.06066   0.05757  -0.0780   0.7824   0.0313
  -5.000   0.0289   0.05572   0.05250  -0.0942   0.7807   0.0342
  -4.750   0.0463   0.05129   0.04806  -0.0964   0.7794   0.0353
  -4.500   0.0693   0.04948   0.04622  -0.0977   0.7781   0.0362
  -4.250   0.0985   0.04724   0.04393  -0.1011   0.7769   0.0379
  -4.000   0.1654   0.04012   0.03658  -0.1179   0.7753   0.0434
  -3.750   0.1879   0.03853   0.03497  -0.1185   0.7733   0.0443
  -3.500   0.2145   0.03702   0.03345  -0.1198   0.7709   0.0455
  -3.250   0.2475   0.03495   0.03131  -0.1231   0.7682   0.0479
  -3.000   0.3241   0.02202   0.01761  -0.1404   0.7662   0.0444
  -2.750   0.3679   0.01410   0.00854  -0.1462   0.7641   0.0418
  -2.500   0.3977   0.01309   0.00723  -0.1467   0.7620   0.0424
  -2.250   0.4272   0.01210   0.00595  -0.1471   0.7598   0.0431
  -2.000   0.4566   0.01119   0.00487  -0.1474   0.7576   0.0445
  -1.750   0.4855   0.01080   0.00443  -0.1475   0.7551   0.0460
  -1.500   0.5141   0.01054   0.00414  -0.1476   0.7522   0.0477
  -1.250   0.5426   0.01033   0.00389  -0.1475   0.7490   0.0502
  -1.000   0.5710   0.01019   0.00368  -0.1474   0.7463   0.0529
  -0.750   0.5994   0.01003   0.00352  -0.1474   0.7436   0.0587
  -0.500   0.6280   0.00990   0.00344  -0.1474   0.7408   0.0676
  -0.250   0.6564   0.00994   0.00349  -0.1473   0.7380   0.0788
   0.000   0.6846   0.00999   0.00356  -0.1472   0.7352   0.0868
   0.250   0.7127   0.00997   0.00352  -0.1471   0.7324   0.0926
   0.500   0.7408   0.00998   0.00353  -0.1471   0.7297   0.0986
   0.750   0.7689   0.00998   0.00355  -0.1470   0.7268   0.1032
   1.000   0.7971   0.00986   0.00347  -0.1470   0.7233   0.1075
   1.250   0.8251   0.00978   0.00343  -0.1469   0.7193   0.1132
   1.500   0.8530   0.00974   0.00337  -0.1467   0.7151   0.1180
   1.750   0.8809   0.00962   0.00329  -0.1466   0.7102   0.1215
   2.000   0.9089   0.00950   0.00323  -0.1465   0.7052   0.1270
   2.250   0.9368   0.00943   0.00316  -0.1463   0.7004   0.1323
   2.500   0.9647   0.00932   0.00314  -0.1462   0.6948   0.1394
   2.750   0.9925   0.00921   0.00309  -0.1461   0.6882   0.1504
   3.000   1.0203   0.00909   0.00306  -0.1459   0.6817   0.1795
   3.250   1.0481   0.00855   0.00330  -0.1461   0.6731   0.5491
   3.500   1.0712   0.00772   0.00323  -0.1449   0.6648   1.0000
   3.750   1.0987   0.00771   0.00320  -0.1447   0.6544   1.0000
   4.000   1.1260   0.00769   0.00318  -0.1444   0.6381   1.0000
   4.250   1.1525   0.00769   0.00312  -0.1440   0.5995   1.0000
   4.500   1.1750   0.00815   0.00320  -0.1429   0.5361   1.0000
   4.750   1.1985   0.00869   0.00351  -0.1422   0.5003   1.0000
   5.000   1.2230   0.00913   0.00382  -0.1416   0.4752   1.0000
   5.250   1.2477   0.00951   0.00413  -0.1411   0.4526   1.0000
   5.500   1.2719   0.00994   0.00445  -0.1405   0.4256   1.0000
   5.750   1.2958   0.01038   0.00478  -0.1400   0.3981   1.0000
   6.000   1.3194   0.01084   0.00512  -0.1393   0.3710   1.0000
   6.250   1.3423   0.01136   0.00552  -0.1386   0.3392   1.0000
   6.500   1.3642   0.01196   0.00595  -0.1378   0.3032   1.0000
   6.750   1.3846   0.01270   0.00646  -0.1368   0.2585   1.0000
   7.000   1.4012   0.01381   0.00719  -0.1353   0.1918   1.0000
   7.250   1.4178   0.01490   0.00798  -0.1338   0.1457   1.0000
   7.500   1.4367   0.01571   0.00867  -0.1326   0.1223   1.0000
   7.750   1.4563   0.01640   0.00928  -0.1314   0.1052   1.0000
   8.000   1.4754   0.01711   0.00990  -0.1302   0.0862   1.0000
   8.250   1.4915   0.01806   0.01066  -0.1286   0.0583   1.0000
   8.500   1.5035   0.01932   0.01172  -0.1264   0.0322   1.0000
   8.750   1.5174   0.02034   0.01270  -0.1243   0.0234   1.0000
   9.000   1.5303   0.02132   0.01369  -0.1221   0.0202   1.0000
   9.250   1.5408   0.02230   0.01476  -0.1195   0.0187   1.0000
   9.500   1.5520   0.02327   0.01581  -0.1172   0.0177   1.0000
   9.750   1.5616   0.02438   0.01700  -0.1148   0.0168   1.0000
  10.000   1.5696   0.02566   0.01836  -0.1124   0.0160   1.0000
  10.250   1.5744   0.02725   0.02006  -0.1099   0.0154   1.0000
  10.500   1.5747   0.02932   0.02223  -0.1071   0.0148   1.0000
  10.750   1.5770   0.03131   0.02434  -0.1047   0.0143   1.0000
  11.000   1.5850   0.03283   0.02595  -0.1029   0.0139   1.0000
  11.250   1.5916   0.03452   0.02774  -0.1012   0.0134   1.0000
  11.500   1.5968   0.03638   0.02970  -0.0994   0.0130   1.0000
  11.750   1.6006   0.03841   0.03182  -0.0976   0.0126   1.0000
  12.000   1.6037   0.04053   0.03404  -0.0959   0.0123   1.0000
  12.250   1.6060   0.04277   0.03638  -0.0942   0.0120   1.0000
  12.500   1.6073   0.04514   0.03883  -0.0925   0.0117   1.0000
  12.750   1.6072   0.04766   0.04144  -0.0908   0.0115   1.0000
  13.000   1.6055   0.05041   0.04428  -0.0890   0.0112   1.0000
  13.250   1.6024   0.05338   0.04735  -0.0869   0.0110   1.0000
  13.500   1.5987   0.05664   0.05075  -0.0843   0.0108   1.0000
  13.750   1.5992   0.05934   0.05359  -0.0830   0.0107   1.0000
  14.000   1.5989   0.06211   0.05652  -0.0819   0.0106   1.0000
  14.250   1.5975   0.06511   0.05968  -0.0810   0.0104   1.0000
  14.500   1.5951   0.06834   0.06307  -0.0802   0.0103   1.0000
  14.750   1.5916   0.07180   0.06671  -0.0796   0.0102   1.0000
  15.000   1.5868   0.07551   0.07060  -0.0792   0.0100   1.0000
  15.250   1.5807   0.07955   0.07481  -0.0791   0.0099   1.0000
  15.500   1.5740   0.08383   0.07925  -0.0794   0.0097   1.0000
  15.750   1.5658   0.08847   0.08407  -0.0800   0.0096   1.0000
  16.000   1.5566   0.09345   0.08921  -0.0809   0.0094   1.0000
  16.250   1.5471   0.09867   0.09460  -0.0822   0.0093   1.0000
  16.500   1.5352   0.10450   0.10062  -0.0840   0.0093   1.0000
  16.750   1.5232   0.11058   0.10688  -0.0863   0.0092   1.0000
  17.000   1.5091   0.11725   0.11374  -0.0891   0.0092   1.0000
  17.250   1.4946   0.12425   0.12092  -0.0924   0.0092   1.0000
  17.500   1.4782   0.13195   0.12882  -0.0964   0.0092   1.0000
  17.750   1.4616   0.14005   0.13711  -0.1011   0.0093   1.0000
  18.000   1.4444   0.14873   0.14597  -0.1064   0.0093   1.0000
  18.250   1.4251   0.15835   0.15578  -0.1126   0.0094   1.0000
  18.500   1.4054   0.16876   0.16637  -0.1197   0.0095   1.0000
  18.750   1.3835   0.18068   0.17848  -0.1280   0.0097   1.0000
  19.000   1.3579   0.19517   0.19314  -0.1382   0.0099   1.0000
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