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GOE 610-B MOD. AIRFOIL (goe610bm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 610-B MOD. AIRFOIL (goe610bm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 130.29 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe610bm-il-1000000.txt
Download as CSV file: xf-goe610bm-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 610-B MOD. 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3261   0.10325   0.10173  -0.0209   1.0000   0.0096
  -8.250  -0.3195   0.09983   0.09832  -0.0229   1.0000   0.0097
  -8.000  -0.3132   0.09638   0.09489  -0.0250   1.0000   0.0097
  -7.750  -0.3053   0.09181   0.09033  -0.0271   0.9876   0.0100
  -7.500  -0.2916   0.08885   0.08736  -0.0297   0.9712   0.0103
  -7.250  -0.2841   0.08627   0.08475  -0.0309   0.9525   0.0105
  -7.000  -0.2758   0.08356   0.08201  -0.0326   0.9370   0.0109
  -6.750  -0.2640   0.08047   0.07887  -0.0355   0.9238   0.0114
  -6.500  -0.2496   0.07702   0.07537  -0.0391   0.9115   0.0122
  -6.250  -0.2242   0.07217   0.07046  -0.0482   0.8989   0.0131
  -6.000  -0.2014   0.06795   0.06618  -0.0540   0.8876   0.0132
  -5.750  -0.1775   0.06349   0.06167  -0.0597   0.8771   0.0132
  -5.500  -0.1516   0.05879   0.05688  -0.0656   0.8665   0.0133
  -5.250  -0.1231   0.05108   0.04906  -0.0747   0.8556   0.0136
  -5.000  -0.1014   0.04926   0.04717  -0.0762   0.8437   0.0140
  -4.750  -0.0748   0.04688   0.04471  -0.0792   0.8316   0.0148
  -4.500  -0.0302   0.04206   0.03969  -0.0864   0.8198   0.0176
  -4.000   0.0376   0.03082   0.02798  -0.0968   0.7965   0.0159
  -3.750   0.0920   0.01591   0.01173  -0.1051   0.7893   0.0185
  -3.500   0.1195   0.01624   0.01206  -0.1053   0.7775   0.0191
  -3.250   0.1465   0.01672   0.01254  -0.1053   0.7660   0.0201
  -2.750   0.2073   0.01453   0.00983  -0.1063   0.7460   0.0232
  -2.000   0.2951   0.01267   0.00755  -0.1078   0.7177   0.0294
  -1.750   0.3255   0.01158   0.00623  -0.1082   0.7085   0.0293
  -1.500   0.3552   0.01084   0.00532  -0.1085   0.6985   0.0297
  -1.250   0.3845   0.01052   0.00490  -0.1087   0.6873   0.0311
  -1.000   0.4137   0.01014   0.00442  -0.1089   0.6746   0.0317
  -0.750   0.4428   0.00983   0.00402  -0.1091   0.6597   0.0321
  -0.500   0.4718   0.00953   0.00361  -0.1093   0.6411   0.0323
  -0.250   0.5007   0.00925   0.00321  -0.1095   0.6150   0.0324
   0.250   0.5581   0.00889   0.00258  -0.1099   0.5609   0.0333
   0.500   0.5873   0.00864   0.00220  -0.1103   0.5438   0.0344
   0.750   0.6162   0.00855   0.00203  -0.1105   0.5307   0.0363
   1.000   0.6450   0.00854   0.00196  -0.1107   0.5204   0.0377
   1.250   0.6736   0.00856   0.00193  -0.1109   0.5115   0.0390
   1.500   0.7023   0.00856   0.00191  -0.1111   0.5033   0.0402
   1.750   0.7309   0.00860   0.00191  -0.1112   0.4946   0.0419
   2.000   0.7593   0.00865   0.00191  -0.1114   0.4848   0.0462
   2.250   0.7894   0.00764   0.00220  -0.1127   0.4762   0.6474
   2.750   0.8403   0.00703   0.00225  -0.1116   0.4620   1.0000
   3.000   0.8685   0.00717   0.00233  -0.1117   0.4543   1.0000
   3.250   0.8969   0.00726   0.00239  -0.1119   0.4465   1.0000
   3.500   0.9251   0.00739   0.00249  -0.1120   0.4397   1.0000
   3.750   0.9533   0.00750   0.00257  -0.1121   0.4298   1.0000
   4.000   0.9813   0.00764   0.00266  -0.1122   0.4164   1.0000
   4.250   1.0091   0.00781   0.00276  -0.1123   0.4010   1.0000
   4.500   1.0369   0.00797   0.00289  -0.1124   0.3876   1.0000
   4.750   1.0645   0.00817   0.00302  -0.1125   0.3712   1.0000
   5.000   1.0914   0.00847   0.00319  -0.1125   0.3425   1.0000
   5.250   1.1171   0.00897   0.00345  -0.1125   0.2960   1.0000
   5.500   1.1375   0.01041   0.00421  -0.1119   0.1737   1.0000
   5.750   1.1602   0.01139   0.00481  -0.1114   0.1094   1.0000
   6.000   1.1795   0.01290   0.00574  -0.1105   0.0197   1.0000
   6.250   1.2054   0.01324   0.00612  -0.1103   0.0150   1.0000
   6.500   1.2310   0.01362   0.00657  -0.1100   0.0136   1.0000
   6.750   1.2559   0.01408   0.00708  -0.1096   0.0123   1.0000
   7.000   1.2793   0.01474   0.00784  -0.1089   0.0109   1.0000
   7.250   1.3034   0.01522   0.00837  -0.1085   0.0103   1.0000
   7.500   1.3272   0.01573   0.00894  -0.1079   0.0097   1.0000
   7.750   1.3502   0.01632   0.00959  -0.1073   0.0091   1.0000
   8.000   1.3724   0.01697   0.01029  -0.1065   0.0086   1.0000
   8.250   1.3936   0.01768   0.01106  -0.1056   0.0082   1.0000
   8.500   1.4130   0.01853   0.01198  -0.1044   0.0078   1.0000
   8.750   1.4269   0.01990   0.01343  -0.1024   0.0073   1.0000
   9.000   1.4333   0.02183   0.01550  -0.0993   0.0070   1.0000
   9.250   1.4551   0.02220   0.01592  -0.0985   0.0067   1.0000
   9.500   1.4720   0.02297   0.01675  -0.0970   0.0064   1.0000
   9.750   1.4836   0.02406   0.01791  -0.0946   0.0062   1.0000
  10.000   1.4926   0.02523   0.01916  -0.0919   0.0060   1.0000
  10.250   1.4969   0.02648   0.02049  -0.0885   0.0059   1.0000
  10.500   1.5010   0.02788   0.02197  -0.0853   0.0058   1.0000
  10.750   1.5060   0.02936   0.02354  -0.0826   0.0056   1.0000
  11.000   1.5109   0.03099   0.02525  -0.0802   0.0055   1.0000
  11.250   1.5163   0.03266   0.02699  -0.0780   0.0054   1.0000
  11.500   1.5216   0.03441   0.02882  -0.0761   0.0053   1.0000
  11.750   1.5266   0.03624   0.03073  -0.0743   0.0051   1.0000
  12.000   1.5308   0.03823   0.03280  -0.0727   0.0050   1.0000
  12.250   1.5339   0.04039   0.03504  -0.0712   0.0049   1.0000
  12.500   1.5355   0.04285   0.03757  -0.0695   0.0048   1.0000
  12.750   1.5357   0.04589   0.04070  -0.0671   0.0046   1.0000
  13.000   1.5415   0.05035   0.04534  -0.0639   0.0045   1.0000
  13.250   1.5422   0.05358   0.04874  -0.0622   0.0045   1.0000
  13.500   1.5397   0.05681   0.05212  -0.0607   0.0045   1.0000
  13.750   1.5346   0.06036   0.05583  -0.0595   0.0045   1.0000
  14.000   1.5254   0.06458   0.06024  -0.0584   0.0045   1.0000
  14.250   1.5151   0.06874   0.06457  -0.0578   0.0045   1.0000
  14.500   1.5027   0.07326   0.06926  -0.0576   0.0045   1.0000
  14.750   1.4907   0.07768   0.07383  -0.0579   0.0045   1.0000
  15.000   1.4767   0.08259   0.07891  -0.0586   0.0045   1.0000
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