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GOE 610 B AIRFOIL (goe610b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 610 B AIRFOIL (goe610b-il)
Reynolds number: 1,000,000
Max Cl/Cd: 99.41 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe610b-il-1000000-n5.txt
Download as CSV file: xf-goe610b-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 610 B AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2043   0.08111   0.07908  -0.0779   0.8860   0.0063
  -9.250  -0.2464   0.07123   0.06900  -0.0814   0.8424   0.0071
  -9.000  -0.2520   0.06862   0.06634  -0.0816   0.8280   0.0075
  -8.750  -0.2541   0.06540   0.06308  -0.0833   0.8178   0.0076
  -8.500  -0.2498   0.06202   0.05967  -0.0859   0.8106   0.0077
  -8.000  -0.2327   0.05522   0.05280  -0.0916   0.7981   0.0085
  -7.750  -0.2225   0.05102   0.04852  -0.0951   0.7921   0.0089
  -7.250  -0.2163   0.03182   0.02864  -0.1065   0.7814   0.0098
  -7.000  -0.1987   0.02807   0.02469  -0.1071   0.7761   0.0108
  -6.500  -0.1906   0.01119   0.00599  -0.1047   0.7668   0.0134
  -6.250  -0.1645   0.01082   0.00558  -0.1044   0.7609   0.0161
  -6.000  -0.1382   0.01049   0.00522  -0.1040   0.7551   0.0190
  -5.750  -0.1097   0.01082   0.00561  -0.1040   0.7478   0.0227
  -5.500  -0.0816   0.01113   0.00594  -0.1038   0.7404   0.0254
  -5.250  -0.0544   0.01118   0.00594  -0.1035   0.7308   0.0276
  -5.000  -0.0274   0.01119   0.00588  -0.1033   0.7197   0.0287
  -4.750  -0.0007   0.01125   0.00588  -0.1029   0.7049   0.0294
  -4.500   0.0258   0.01140   0.00595  -0.1025   0.6864   0.0299
  -4.250   0.0520   0.01155   0.00600  -0.1021   0.6660   0.0301
  -4.000   0.0782   0.01172   0.00608  -0.1016   0.6462   0.0303
  -3.750   0.1016   0.01085   0.00494  -0.1009   0.6264   0.0312
  -3.500   0.1266   0.01057   0.00450  -0.1003   0.6078   0.0321
  -3.250   0.1526   0.01046   0.00428  -0.0999   0.5939   0.0327
  -3.000   0.1786   0.01014   0.00386  -0.0995   0.5837   0.0329
  -2.750   0.2048   0.01002   0.00366  -0.0991   0.5730   0.0334
  -2.500   0.2306   0.00977   0.00330  -0.0987   0.5617   0.0337
  -2.250   0.2566   0.00951   0.00295  -0.0982   0.5519   0.0340
  -2.000   0.2827   0.00930   0.00268  -0.0978   0.5442   0.0345
  -1.750   0.3090   0.00915   0.00247  -0.0974   0.5365   0.0354
  -1.500   0.3356   0.00903   0.00230  -0.0971   0.5320   0.0366
  -1.250   0.3625   0.00894   0.00220  -0.0969   0.5276   0.0384
  -1.000   0.3895   0.00889   0.00212  -0.0966   0.5236   0.0399
  -0.750   0.4162   0.00888   0.00208  -0.0963   0.5191   0.0409
  -0.500   0.4433   0.00888   0.00206  -0.0961   0.5147   0.0417
  -0.250   0.4702   0.00887   0.00203  -0.0959   0.5083   0.0421
   0.000   0.4966   0.00888   0.00201  -0.0956   0.5014   0.0424
   0.250   0.5236   0.00887   0.00199  -0.0954   0.4954   0.0427
   0.500   0.5502   0.00883   0.00194  -0.0951   0.4905   0.0428
   0.750   0.5765   0.00877   0.00187  -0.0948   0.4853   0.0431
   1.000   0.6026   0.00863   0.00172  -0.0944   0.4788   0.0436
   1.250   0.6285   0.00857   0.00164  -0.0940   0.4710   0.0440
   1.500   0.6548   0.00853   0.00159  -0.0937   0.4626   0.0444
   1.750   0.6807   0.00853   0.00157  -0.0933   0.4517   0.0447
   2.000   0.7058   0.00860   0.00156  -0.0928   0.4294   0.0450
   2.250   0.7228   0.00932   0.00182  -0.0909   0.3284   0.0458
   2.500   0.7464   0.00954   0.00195  -0.0901   0.3037   0.0465
   2.750   0.7711   0.00968   0.00204  -0.0895   0.2887   0.0467
   3.000   0.7960   0.00981   0.00213  -0.0890   0.2767   0.0468
   3.250   0.8212   0.00992   0.00222  -0.0885   0.2671   0.0471
   3.500   0.8465   0.01002   0.00230  -0.0881   0.2592   0.0475
   3.750   0.8714   0.01015   0.00241  -0.0876   0.2501   0.0480
   4.000   0.8965   0.01026   0.00251  -0.0871   0.2408   0.0493
   4.250   0.9210   0.01043   0.00265  -0.0865   0.2293   0.0510
   4.500   0.9447   0.01064   0.00280  -0.0858   0.2131   0.0544
   4.750   0.9683   0.01080   0.00300  -0.0851   0.1994   0.0973
   5.000   0.9857   0.01144   0.00339  -0.0834   0.1384   0.1157
   5.250   1.0458   0.01052   0.00408  -0.0918   0.1196   0.9985
   5.500   1.0716   0.01085   0.00438  -0.0916   0.1112   1.0000
   5.750   1.0942   0.01105   0.00458  -0.0907   0.1077   1.0000
   6.000   1.1166   0.01127   0.00481  -0.0897   0.1043   1.0000
   6.250   1.1382   0.01153   0.00506  -0.0886   0.1000   1.0000
   6.500   1.1598   0.01180   0.00533  -0.0875   0.0956   1.0000
   6.750   1.1825   0.01197   0.00553  -0.0866   0.0925   1.0000
   7.000   1.2026   0.01231   0.00580  -0.0853   0.0781   1.0000
   7.250   1.2153   0.01310   0.00636  -0.0827   0.0425   1.0000
   7.500   1.2285   0.01384   0.00697  -0.0803   0.0195   1.0000
   7.750   1.2469   0.01424   0.00737  -0.0787   0.0147   1.0000
   8.000   1.2657   0.01460   0.00775  -0.0771   0.0127   1.0000
   8.250   1.2832   0.01501   0.00818  -0.0754   0.0112   1.0000
   8.500   1.2990   0.01549   0.00868  -0.0734   0.0096   1.0000
   8.750   1.3145   0.01587   0.00909  -0.0713   0.0089   1.0000
   9.000   1.3286   0.01629   0.00956  -0.0690   0.0082   1.0000
   9.250   1.3418   0.01678   0.01007  -0.0666   0.0076   1.0000
   9.500   1.3543   0.01734   0.01066  -0.0642   0.0069   1.0000
   9.750   1.3681   0.01787   0.01123  -0.0620   0.0065   1.0000
  10.000   1.3815   0.01844   0.01185  -0.0600   0.0063   1.0000
  10.250   1.3948   0.01904   0.01249  -0.0580   0.0058   1.0000
  10.500   1.4073   0.01971   0.01321  -0.0560   0.0055   1.0000
  10.750   1.4190   0.02046   0.01399  -0.0540   0.0052   1.0000
  11.000   1.4293   0.02134   0.01496  -0.0519   0.0050   1.0000
  11.250   1.4389   0.02230   0.01597  -0.0499   0.0047   1.0000
  11.500   1.4488   0.02329   0.01704  -0.0481   0.0046   1.0000
  11.750   1.4611   0.02414   0.01794  -0.0466   0.0042   1.0000
  12.000   1.4697   0.02532   0.01919  -0.0449   0.0042   1.0000
  12.250   1.4794   0.02643   0.02037  -0.0435   0.0040   1.0000
  12.500   1.4872   0.02776   0.02176  -0.0419   0.0038   1.0000
  12.750   1.4946   0.02914   0.02321  -0.0405   0.0037   1.0000
  13.000   1.5019   0.03059   0.02472  -0.0392   0.0036   1.0000
  13.250   1.5077   0.03218   0.02638  -0.0379   0.0034   1.0000
  13.500   1.5110   0.03407   0.02834  -0.0366   0.0033   1.0000
  13.750   1.5111   0.03631   0.03068  -0.0352   0.0032   1.0000
  14.000   1.5129   0.03847   0.03294  -0.0341   0.0032   1.0000
  14.250   1.5177   0.04036   0.03491  -0.0333   0.0031   1.0000
  14.500   1.5171   0.04291   0.03756  -0.0325   0.0031   1.0000
  14.750   1.5184   0.04535   0.04009  -0.0319   0.0030   1.0000
  15.000   1.5160   0.04826   0.04311  -0.0314   0.0030   1.0000
  15.250   1.5179   0.05078   0.04576  -0.0311   0.0029   1.0000
  15.500   1.5163   0.05379   0.04887  -0.0309   0.0029   1.0000
  15.750   1.5121   0.05721   0.05241  -0.0308   0.0028   1.0000
  16.000   1.5101   0.06042   0.05572  -0.0310   0.0027   1.0000
  16.250   1.5028   0.06442   0.05983  -0.0312   0.0027   1.0000
  16.500   1.5009   0.06775   0.06326  -0.0316   0.0027   1.0000
  16.750   1.4936   0.07189   0.06751  -0.0321   0.0026   1.0000
  17.000   1.4892   0.07569   0.07140  -0.0328   0.0026   1.0000
  17.250   1.4859   0.07941   0.07521  -0.0335   0.0025   1.0000
  17.500   1.4817   0.08335   0.07924  -0.0344   0.0024   1.0000
  17.750   1.4698   0.08857   0.08458  -0.0357   0.0024   1.0000
  18.000   1.4593   0.09370   0.08982  -0.0372   0.0024   1.0000
  18.250   1.4522   0.09846   0.09468  -0.0388   0.0023   1.0000
  18.500   1.4422   0.10382   0.10015  -0.0407   0.0023   1.0000
  18.750   1.4308   0.10959   0.10604  -0.0429   0.0023   1.0000
  19.000   1.4160   0.11612   0.11270  -0.0456   0.0023   1.0000
  19.250   1.4026   0.12257   0.11926  -0.0485   0.0023   1.0000
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