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GOE 625 AIRFOIL (goe625-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 625 AIRFOIL (goe625-il)
Reynolds number: 100,000
Max Cl/Cd: 42.44 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe625-il-100000-n5.txt
Download as CSV file: xf-goe625-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 625 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.0748   0.10789   0.10224  -0.0965   0.9368   0.0749
 -11.250  -0.0743   0.10299   0.09731  -0.0997   0.9300   0.0758
 -11.000  -0.0962   0.09467   0.08896  -0.1050   0.9225   0.0779
 -10.750  -0.0729   0.09337   0.08763  -0.1060   0.9161   0.0790
 -10.500  -0.0653   0.09094   0.08519  -0.1066   0.9056   0.0803
 -10.250  -0.0628   0.08668   0.08088  -0.1092   0.8986   0.0818
 -10.000  -0.2563   0.05473   0.04858  -0.1316   0.8826   0.0862
  -9.750  -0.2390   0.05426   0.04812  -0.1308   0.8737   0.0871
  -9.500  -0.2358   0.05236   0.04613  -0.1302   0.8642   0.0882
  -9.250  -0.2463   0.04893   0.04248  -0.1298   0.8556   0.0896
  -9.000  -0.2630   0.04489   0.03805  -0.1284   0.8460   0.0916
  -8.750  -0.2772   0.03949   0.03181  -0.1274   0.8401   0.0943
  -8.500  -0.2648   0.03879   0.03110  -0.1255   0.8307   0.0955
  -8.250  -0.2406   0.03815   0.03045  -0.1252   0.8247   0.0969
  -8.000  -0.2182   0.03701   0.02916  -0.1250   0.8194   0.0987
  -7.750  -0.2065   0.03577   0.02772  -0.1232   0.8102   0.1004
  -7.500  -0.1884   0.03383   0.02535  -0.1227   0.8042   0.1029
  -7.250  -0.1691   0.03252   0.02380  -0.1218   0.7975   0.1046
  -7.000  -0.1477   0.03197   0.02323  -0.1209   0.7893   0.1060
  -6.750  -0.1200   0.03112   0.02228  -0.1210   0.7836   0.1077
  -6.500  -0.1007   0.03042   0.02146  -0.1198   0.7745   0.1095
  -6.250  -0.0763   0.02941   0.02021  -0.1193   0.7669   0.1117
  -6.000  -0.0523   0.02835   0.01884  -0.1188   0.7593   0.1138
  -5.750  -0.0294   0.02769   0.01812  -0.1180   0.7499   0.1153
  -5.500  -0.0002   0.02708   0.01746  -0.1181   0.7430   0.1172
  -5.250   0.0209   0.02668   0.01702  -0.1169   0.7322   0.1191
  -5.000   0.0505   0.02596   0.01612  -0.1171   0.7250   0.1217
  -4.750   0.0717   0.02544   0.01548  -0.1159   0.7133   0.1239
  -4.500   0.1004   0.02475   0.01460  -0.1158   0.7046   0.1262
  -4.250   0.1234   0.02441   0.01429  -0.1150   0.6924   0.1283
  -4.000   0.1494   0.02403   0.01385  -0.1145   0.6812   0.1312
  -3.750   0.1764   0.02359   0.01328  -0.1141   0.6698   0.1348
  -3.500   0.2007   0.02322   0.01275  -0.1134   0.6568   0.1384
  -3.250   0.2269   0.02285   0.01238  -0.1130   0.6451   0.1414
  -3.000   0.2528   0.02256   0.01202  -0.1125   0.6330   0.1456
  -2.750   0.2777   0.02233   0.01166  -0.1118   0.6205   0.1512
  -2.500   0.3041   0.02206   0.01136  -0.1115   0.6095   0.1567
  -2.250   0.3290   0.02191   0.01113  -0.1109   0.5977   0.1638
  -2.000   0.3544   0.02173   0.01088  -0.1104   0.5870   0.1711
  -1.750   0.3801   0.02160   0.01067  -0.1100   0.5769   0.1792
  -1.500   0.4051   0.02151   0.01052  -0.1094   0.5673   0.1881
  -1.250   0.4307   0.02144   0.01039  -0.1090   0.5586   0.1977
  -1.000   0.4561   0.02140   0.01030  -0.1086   0.5509   0.2077
  -0.750   0.4813   0.02138   0.01025  -0.1082   0.5435   0.2182
  -0.500   0.5083   0.02135   0.01015  -0.1081   0.5377   0.2290
  -0.250   0.5333   0.02139   0.01019  -0.1077   0.5316   0.2415
   0.000   0.5585   0.02139   0.01025  -0.1074   0.5258   0.2576
   0.250   0.5852   0.02137   0.01026  -0.1073   0.5209   0.2813
   0.500   0.6118   0.02131   0.01032  -0.1072   0.5162   0.3191
   0.750   0.6355   0.02121   0.01052  -0.1068   0.5109   0.3907
   1.000   0.6579   0.02088   0.01072  -0.1059   0.5062   0.5351
   1.250   0.6773   0.02049   0.01101  -0.1034   0.5024   0.7540
   1.500   0.7284   0.02060   0.01123  -0.1072   0.4986   0.9428
   1.750   0.7732   0.02095   0.01150  -0.1109   0.4942   1.0000
   2.000   0.7944   0.02125   0.01170  -0.1099   0.4903   1.0000
   2.250   0.8171   0.02154   0.01186  -0.1092   0.4866   1.0000
   2.500   0.8418   0.02183   0.01200  -0.1088   0.4832   1.0000
   2.750   0.8697   0.02213   0.01212  -0.1089   0.4803   1.0000
   3.000   0.8898   0.02252   0.01248  -0.1078   0.4770   1.0000
   3.250   0.9107   0.02291   0.01285  -0.1069   0.4736   1.0000
   3.500   0.9329   0.02328   0.01317  -0.1061   0.4700   1.0000
   3.750   0.9569   0.02364   0.01345  -0.1057   0.4667   1.0000
   4.000   0.9830   0.02398   0.01368  -0.1056   0.4636   1.0000
   4.250   1.0113   0.02434   0.01389  -0.1059   0.4606   1.0000
   4.500   1.0250   0.02483   0.01445  -0.1038   0.4560   1.0000
   4.750   1.0426   0.02525   0.01487  -0.1023   0.4512   1.0000
   5.000   1.0649   0.02559   0.01513  -0.1016   0.4467   1.0000
   5.250   1.0918   0.02590   0.01531  -0.1017   0.4429   1.0000
   5.500   1.1115   0.02638   0.01578  -0.1007   0.4394   1.0000
   5.750   1.1250   0.02696   0.01643  -0.0986   0.4356   1.0000
   6.000   1.1417   0.02748   0.01698  -0.0972   0.4319   1.0000
   6.250   1.1618   0.02794   0.01742  -0.0962   0.4284   1.0000
   6.500   1.1860   0.02831   0.01773  -0.0960   0.4252   1.0000
   6.750   1.2164   0.02866   0.01797  -0.0967   0.4223   1.0000
   7.000   1.2183   0.02943   0.01888  -0.0929   0.4186   1.0000
   7.250   1.2252   0.03021   0.01975  -0.0901   0.4147   1.0000
   7.500   1.2385   0.03087   0.02045  -0.0883   0.4111   1.0000
   7.750   1.2581   0.03138   0.02095  -0.0875   0.4077   1.0000
   8.000   1.2844   0.03171   0.02121  -0.0876   0.4047   1.0000
   8.250   1.2978   0.03245   0.02198  -0.0859   0.4013   1.0000
   8.500   1.2922   0.03379   0.02351  -0.0819   0.3968   1.0000
   8.750   1.2981   0.03482   0.02461  -0.0796   0.3926   1.0000
   9.000   1.3147   0.03543   0.02522  -0.0786   0.3888   1.0000
   9.250   1.3410   0.03567   0.02540  -0.0786   0.3857   1.0000
   9.500   1.3394   0.03715   0.02701  -0.0757   0.3816   1.0000
   9.750   1.3264   0.03934   0.02939  -0.0720   0.3765   1.0000
  10.000   1.3326   0.04060   0.03071  -0.0702   0.3723   1.0000
  10.250   1.3531   0.04105   0.03114  -0.0698   0.3690   1.0000
  10.500   1.3706   0.04171   0.03180  -0.0691   0.3656   1.0000
  10.750   1.3247   0.04659   0.03701  -0.0639   0.3584   1.0000
  11.000   1.3294   0.04818   0.03864  -0.0625   0.3538   1.0000
  11.250   1.3551   0.04815   0.03857  -0.0624   0.3507   1.0000
  11.500   1.2810   0.05678   0.04755  -0.0579   0.3408   1.0000
  11.750   1.2892   0.05834   0.04913  -0.0572   0.3364   1.0000
  12.000   1.3188   0.05779   0.04854  -0.0571   0.3340   1.0000
  12.500   1.2487   0.07073   0.06178  -0.0547   0.3182   1.0000
  13.000   1.1936   0.08378   0.07503  -0.0545   0.3023   1.0000
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