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GOE 610-B MOD. AIRFOIL (goe610bm-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 610-B MOD. AIRFOIL (goe610bm-il)
Reynolds number: 200,000
Max Cl/Cd: 82.3 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe610bm-il-200000-n5.txt
Download as CSV file: xf-goe610bm-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2782   0.10181   0.09851  -0.0283   1.0000   0.0205
  -7.750  -0.2742   0.09947   0.09623  -0.0296   1.0000   0.0214
  -7.500  -0.2765   0.09786   0.09469  -0.0295   1.0000   0.0219
  -7.250  -0.2612   0.09449   0.09134  -0.0350   0.9881   0.0222
  -7.000  -0.2404   0.09042   0.08727  -0.0418   0.9776   0.0223
  -6.750  -0.2187   0.08616   0.08300  -0.0482   0.9677   0.0224
  -6.500  -0.1966   0.08177   0.07857  -0.0540   0.9582   0.0224
  -6.000  -0.1524   0.07306   0.06979  -0.0647   0.9376   0.0224
  -5.750  -0.1381   0.06890   0.06560  -0.0663   0.9268   0.0217
  -5.500  -0.1217   0.06481   0.06148  -0.0689   0.9156   0.0196
  -5.250  -0.0962   0.06017   0.05676  -0.0749   0.9044   0.0182
  -5.000  -0.0665   0.05526   0.05175  -0.0815   0.8947   0.0176
  -4.750  -0.0343   0.05047   0.04683  -0.0881   0.8846   0.0175
  -4.500  -0.0010   0.04626   0.04247  -0.0937   0.8751   0.0186
  -4.250   0.0375   0.04136   0.03735  -0.1001   0.8666   0.0206
  -4.000   0.0790   0.03551   0.03115  -0.1065   0.8573   0.0212
  -3.750   0.1237   0.02858   0.02360  -0.1123   0.8495   0.0236
  -3.500   0.1479   0.02810   0.02308  -0.1128   0.8391   0.0258
  -3.250   0.1815   0.02512   0.01971  -0.1149   0.8291   0.0275
  -3.000   0.2148   0.02259   0.01671  -0.1163   0.8192   0.0308
  -2.750   0.2472   0.02065   0.01422  -0.1170   0.8092   0.0331
  -2.500   0.2784   0.01901   0.01208  -0.1178   0.7982   0.0350
  -2.250   0.3074   0.01760   0.01043  -0.1184   0.7873   0.0378
  -2.000   0.3367   0.01659   0.00913  -0.1186   0.7763   0.0387
  -1.500   0.3944   0.01514   0.00719  -0.1187   0.7537   0.0406
  -1.250   0.4228   0.01472   0.00660  -0.1187   0.7420   0.0427
  -1.000   0.4512   0.01428   0.00598  -0.1186   0.7302   0.0438
  -0.750   0.4795   0.01381   0.00539  -0.1186   0.7184   0.0435
  -0.250   0.5361   0.01312   0.00450  -0.1186   0.6930   0.0435
   0.000   0.5645   0.01287   0.00418  -0.1186   0.6790   0.0438
   0.250   0.5928   0.01268   0.00392  -0.1187   0.6643   0.0443
   0.500   0.6211   0.01256   0.00370  -0.1187   0.6487   0.0452
   0.750   0.6491   0.01249   0.00352  -0.1187   0.6317   0.0466
   1.000   0.6772   0.01244   0.00337  -0.1187   0.6141   0.0493
   1.250   0.7051   0.01241   0.00327  -0.1187   0.5974   0.0569
   1.500   0.7332   0.01218   0.00331  -0.1190   0.5823   0.1950
   2.000   0.7812   0.01085   0.00338  -0.1175   0.5576   1.0000
   2.250   0.8087   0.01105   0.00347  -0.1174   0.5471   1.0000
   2.500   0.8363   0.01127   0.00358  -0.1174   0.5376   1.0000
   3.000   0.8912   0.01171   0.00388  -0.1174   0.5212   1.0000
   3.500   0.9460   0.01216   0.00424  -0.1174   0.5063   1.0000
   3.750   0.9730   0.01242   0.00446  -0.1173   0.4975   1.0000
   4.000   0.9999   0.01266   0.00467  -0.1172   0.4862   1.0000
   4.250   1.0267   0.01288   0.00488  -0.1171   0.4748   1.0000
   4.500   1.0535   0.01312   0.00514  -0.1170   0.4656   1.0000
   4.750   1.0803   0.01334   0.00538  -0.1169   0.4566   1.0000
   5.000   1.1071   0.01356   0.00565  -0.1168   0.4479   1.0000
   5.250   1.1332   0.01380   0.00589  -0.1166   0.4339   1.0000
   5.500   1.1579   0.01407   0.00612  -0.1162   0.4048   1.0000
   5.750   1.1819   0.01443   0.00636  -0.1157   0.3690   1.0000
   6.000   1.2049   0.01495   0.00669  -0.1152   0.3239   1.0000
   6.250   1.2222   0.01617   0.00735  -0.1140   0.2293   1.0000
   6.500   1.2366   0.01786   0.00848  -0.1125   0.1427   1.0000
   6.750   1.2543   0.01907   0.00940  -0.1114   0.0960   1.0000
   7.000   1.2657   0.02092   0.01077  -0.1093   0.0221   1.0000
   7.250   1.2845   0.02185   0.01177  -0.1080   0.0175   1.0000
   7.500   1.3038   0.02268   0.01277  -0.1067   0.0148   1.0000
   7.750   1.3219   0.02359   0.01387  -0.1053   0.0136   1.0000
   8.000   1.3394   0.02449   0.01499  -0.1038   0.0130   1.0000
   8.250   1.3551   0.02549   0.01615  -0.1021   0.0119   1.0000
   8.500   1.3686   0.02661   0.01743  -0.1001   0.0109   1.0000
   8.750   1.3791   0.02787   0.01886  -0.0977   0.0103   1.0000
   9.000   1.3852   0.02926   0.02041  -0.0947   0.0099   1.0000
   9.250   1.3870   0.03086   0.02215  -0.0913   0.0096   1.0000
   9.500   1.3868   0.03277   0.02420  -0.0881   0.0094   1.0000
   9.750   1.3848   0.03500   0.02654  -0.0852   0.0092   1.0000
  10.000   1.3812   0.03755   0.02919  -0.0825   0.0090   1.0000
  10.250   1.3770   0.04038   0.03209  -0.0800   0.0088   1.0000
  10.500   1.3783   0.04284   0.03463  -0.0780   0.0086   1.0000
  10.750   1.3860   0.04465   0.03665  -0.0768   0.0082   1.0000
  11.000   1.3917   0.04672   0.03887  -0.0755   0.0077   1.0000
  11.250   1.3957   0.04907   0.04134  -0.0741   0.0074   1.0000
  11.500   1.3996   0.05153   0.04391  -0.0727   0.0072   1.0000
  11.750   1.4038   0.05401   0.04651  -0.0713   0.0070   1.0000
  12.000   1.4084   0.05653   0.04916  -0.0700   0.0069   1.0000
  12.250   1.4128   0.05914   0.05190  -0.0687   0.0068   1.0000
  12.500   1.4164   0.06189   0.05479  -0.0675   0.0067   1.0000
  12.750   1.4187   0.06484   0.05791  -0.0664   0.0066   1.0000
  13.000   1.4195   0.06803   0.06128  -0.0656   0.0065   1.0000
  13.250   1.4182   0.07149   0.06493  -0.0649   0.0065   1.0000
  13.500   1.4151   0.07521   0.06885  -0.0645   0.0064   1.0000
  13.750   1.4100   0.07924   0.07309  -0.0644   0.0064   1.0000
  14.000   1.4031   0.08360   0.07767  -0.0647   0.0064   1.0000
  14.250   1.3944   0.08829   0.08259  -0.0654   0.0064   1.0000
  14.500   1.3845   0.09338   0.08790  -0.0665   0.0064   1.0000
  14.750   1.3735   0.09886   0.09360  -0.0681   0.0064   1.0000
  15.000   1.3615   0.10471   0.09968  -0.0703   0.0064   1.0000
  15.250   1.3487   0.11094   0.10613  -0.0730   0.0065   1.0000
  15.500   1.3357   0.11749   0.11289  -0.0761   0.0065   1.0000
  15.750   1.3225   0.12439   0.12001  -0.0798   0.0065   1.0000
  16.000   1.3092   0.13168   0.12749  -0.0839   0.0065   1.0000
  16.250   1.2957   0.13941   0.13542  -0.0887   0.0066   1.0000
  16.500   1.2823   0.14751   0.14370  -0.0938   0.0066   1.0000
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