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GOE 405 AIRFOIL (goe405-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 405 AIRFOIL (goe405-il)
Reynolds number: 500,000
Max Cl/Cd: 115.44 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe405-il-500000.txt
Download as CSV file: xf-goe405-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 405 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.0715   0.09122   0.08892  -0.0947   0.9709   0.0260
  -9.250  -0.0624   0.08709   0.08479  -0.0992   0.9643   0.0262
  -9.000  -0.0458   0.08246   0.08016  -0.1047   0.9608   0.0263
  -8.750  -0.0307   0.07750   0.07520  -0.1084   0.9586   0.0270
  -8.500  -0.0050   0.07473   0.07241  -0.1122   0.9564   0.0276
  -8.250   0.0118   0.07204   0.06970  -0.1150   0.9483   0.0286
  -8.000   0.0353   0.06812   0.06575  -0.1214   0.9429   0.0300
  -7.750   0.0394   0.06278   0.06037  -0.1302   0.9255   0.0327
  -7.500   0.0480   0.05827   0.05579  -0.1357   0.9118   0.0329
  -7.000  -0.0234   0.02390   0.02011  -0.1504   0.8711   0.0258
  -6.750  -0.0117   0.02052   0.01610  -0.1494   0.8617   0.0266
  -6.500   0.0075   0.01858   0.01393  -0.1489   0.8541   0.0277
  -6.250   0.0308   0.01811   0.01339  -0.1483   0.8455   0.0290
  -6.000   0.0559   0.01742   0.01251  -0.1480   0.8382   0.0305
  -5.750   0.0781   0.01652   0.01137  -0.1470   0.8285   0.0318
  -5.500   0.1029   0.01597   0.01056  -0.1464   0.8194   0.0327
  -5.250   0.1237   0.01411   0.00838  -0.1455   0.8101   0.0344
  -5.000   0.1481   0.01361   0.00781  -0.1449   0.8011   0.0360
  -4.750   0.1742   0.01314   0.00719  -0.1445   0.7940   0.0376
  -4.500   0.1992   0.01264   0.00658  -0.1439   0.7864   0.0389
  -4.250   0.2257   0.01228   0.00606  -0.1436   0.7798   0.0403
  -4.000   0.2514   0.01197   0.00565  -0.1431   0.7728   0.0413
  -3.750   0.2760   0.01113   0.00468  -0.1424   0.7662   0.0432
  -3.500   0.3016   0.01078   0.00427  -0.1420   0.7598   0.0450
  -3.250   0.3276   0.01054   0.00398  -0.1416   0.7532   0.0472
  -3.000   0.3542   0.01034   0.00369  -0.1412   0.7475   0.0493
  -2.750   0.3799   0.01015   0.00344  -0.1407   0.7408   0.0509
  -2.500   0.4060   0.00985   0.00309  -0.1403   0.7350   0.0551
  -2.250   0.4319   0.00968   0.00291  -0.1398   0.7288   0.0609
  -2.000   0.4574   0.00943   0.00274  -0.1393   0.7227   0.0829
  -1.750   0.4837   0.00933   0.00272  -0.1390   0.7169   0.1235
  -1.500   0.5099   0.00932   0.00272  -0.1386   0.7105   0.1398
  -1.250   0.5369   0.00935   0.00270  -0.1384   0.7048   0.1513
  -1.000   0.5631   0.00937   0.00269  -0.1381   0.6985   0.1613
  -0.750   0.5893   0.00937   0.00270  -0.1377   0.6920   0.1716
  -0.500   0.6156   0.00939   0.00270  -0.1374   0.6859   0.1815
  -0.250   0.6416   0.00942   0.00270  -0.1370   0.6790   0.1911
   0.000   0.6677   0.00943   0.00270  -0.1366   0.6727   0.2014
   0.250   0.6929   0.00940   0.00270  -0.1361   0.6652   0.2115
   0.750   0.7437   0.00939   0.00269  -0.1350   0.6506   0.2307
   1.000   0.7690   0.00942   0.00267  -0.1345   0.6432   0.2402
   1.250   0.7936   0.00940   0.00269  -0.1339   0.6343   0.2510
   1.500   0.8180   0.00940   0.00270  -0.1332   0.6259   0.2645
   1.750   0.8420   0.00939   0.00272  -0.1324   0.6161   0.2801
   2.000   0.8655   0.00936   0.00275  -0.1316   0.6056   0.3036
   2.250   0.8825   0.00876   0.00286  -0.1297   0.5950   0.6167
   2.500   0.9422   0.00826   0.00305  -0.1368   0.5810   1.0000
   2.750   0.9636   0.00841   0.00312  -0.1355   0.5688   1.0000
   3.000   0.9852   0.00856   0.00320  -0.1342   0.5560   1.0000
   3.250   1.0066   0.00872   0.00330  -0.1330   0.5432   1.0000
   3.500   1.0277   0.00891   0.00341  -0.1316   0.5304   1.0000
   3.750   1.0485   0.00910   0.00355  -0.1303   0.5179   1.0000
   4.000   1.0688   0.00932   0.00370  -0.1288   0.5054   1.0000
   4.250   1.0888   0.00956   0.00386  -0.1274   0.4936   1.0000
   4.500   1.1097   0.00977   0.00403  -0.1261   0.4826   1.0000
   4.750   1.1304   0.00999   0.00422  -0.1248   0.4729   1.0000
   5.000   1.1500   0.01025   0.00442  -0.1232   0.4636   1.0000
   5.250   1.1706   0.01046   0.00462  -0.1219   0.4541   1.0000
   5.500   1.1899   0.01071   0.00484  -0.1204   0.4461   1.0000
   5.750   1.2088   0.01094   0.00506  -0.1187   0.4379   1.0000
   6.000   1.2268   0.01120   0.00530  -0.1169   0.4289   1.0000
   6.500   1.2611   0.01174   0.00580  -0.1131   0.4088   1.0000
   6.750   1.2785   0.01203   0.00608  -0.1113   0.3995   1.0000
   7.250   1.3124   0.01265   0.00667  -0.1076   0.3783   1.0000
   7.500   1.3294   0.01297   0.00699  -0.1058   0.3680   1.0000
   7.750   1.3449   0.01335   0.00736  -0.1038   0.3556   1.0000
   8.000   1.3597   0.01377   0.00775  -0.1018   0.3416   1.0000
   8.250   1.3735   0.01425   0.00819  -0.0996   0.3239   1.0000
   8.500   1.3854   0.01483   0.00870  -0.0972   0.3043   1.0000
   8.750   1.3944   0.01558   0.00934  -0.0944   0.2804   1.0000
   9.000   1.3952   0.01679   0.01031  -0.0906   0.2426   1.0000
   9.250   1.3932   0.01825   0.01151  -0.0866   0.2008   1.0000
   9.500   1.3801   0.02048   0.01332  -0.0815   0.1365   1.0000
   9.750   1.3535   0.02377   0.01613  -0.0753   0.0556   1.0000
  10.000   1.3490   0.02584   0.01808  -0.0720   0.0287   1.0000
  10.250   1.3550   0.02726   0.01953  -0.0699   0.0234   1.0000
  10.500   1.3609   0.02874   0.02105  -0.0680   0.0212   1.0000
  10.750   1.3659   0.03033   0.02274  -0.0661   0.0200   1.0000
  11.000   1.3730   0.03182   0.02432  -0.0645   0.0190   1.0000
  11.250   1.3779   0.03352   0.02612  -0.0629   0.0181   1.0000
  11.500   1.3814   0.03541   0.02809  -0.0614   0.0173   1.0000
  11.750   1.3819   0.03765   0.03041  -0.0598   0.0165   1.0000
  12.000   1.3784   0.04035   0.03322  -0.0582   0.0160   1.0000
  12.250   1.3691   0.04376   0.03676  -0.0565   0.0155   1.0000
  12.500   1.3701   0.04625   0.03935  -0.0555   0.0153   1.0000
  12.750   1.3709   0.04882   0.04201  -0.0546   0.0149   1.0000
  13.000   1.3689   0.05178   0.04509  -0.0538   0.0146   1.0000
  13.250   1.3650   0.05505   0.04846  -0.0531   0.0145   1.0000
  13.500   1.3625   0.05823   0.05174  -0.0526   0.0142   1.0000
  13.750   1.3583   0.06171   0.05532  -0.0522   0.0139   1.0000
  14.000   1.3555   0.06509   0.05879  -0.0520   0.0136   1.0000
  14.250   1.3512   0.06874   0.06253  -0.0519   0.0134   1.0000
  14.500   1.3486   0.07223   0.06609  -0.0519   0.0129   1.0000
  14.750   1.3440   0.07599   0.06992  -0.0520   0.0126   1.0000
  15.000   1.3376   0.07998   0.07396  -0.0520   0.0122   1.0000
  15.250   1.3335   0.08354   0.07758  -0.0519   0.0120   1.0000
  15.500   1.3327   0.08626   0.08033  -0.0510   0.0117   1.0000
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