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GOE 257 AIRFOIL (goe257-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 257 AIRFOIL (goe257-il)
Reynolds number: 100,000
Max Cl/Cd: 56.76 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe257-il-100000.txt
Download as CSV file: xf-goe257-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 257 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4215   0.11825   0.11338  -0.0138   1.0000   0.0545
  -9.000  -0.4255   0.11662   0.11186  -0.0183   1.0000   0.0549
  -8.750  -0.4290   0.11450   0.10981  -0.0228   1.0000   0.0551
  -8.500  -0.4022   0.10553   0.10077  -0.0155   1.0000   0.0578
  -8.250  -0.3951   0.10211   0.09737  -0.0159   1.0000   0.0598
  -8.000  -0.3910   0.09897   0.09427  -0.0171   1.0000   0.0620
  -7.750  -0.3895   0.09601   0.09137  -0.0188   1.0000   0.0643
  -7.500  -0.3011   0.08120   0.07694  -0.0272   1.0000   0.0720
  -7.250  -0.3001   0.07809   0.07389  -0.0268   1.0000   0.0752
  -7.000  -0.3049   0.07521   0.07107  -0.0274   1.0000   0.0779
  -6.750  -0.3108   0.07237   0.06831  -0.0305   1.0000   0.0805
  -6.500  -0.3167   0.07008   0.06598  -0.0375   1.0000   0.0821
  -6.250  -0.3176   0.06542   0.06141  -0.0363   1.0000   0.0834
  -6.000  -0.3170   0.06238   0.05848  -0.0309   1.0000   0.0859
  -5.750  -0.3229   0.06051   0.05670  -0.0285   1.0000   0.0879
  -5.500  -0.3362   0.05970   0.05596  -0.0260   1.0000   0.0894
  -5.250  -0.2902   0.06092   0.05624  -0.0455   1.0000   0.0989
  -5.000  -0.2851   0.05847   0.05389  -0.0431   1.0000   0.1026
  -4.750  -0.2686   0.05642   0.05153  -0.0466   1.0000   0.1123
  -4.500  -0.2752   0.05446   0.04977  -0.0428   1.0000   0.1141
  -4.250  -0.2437   0.05114   0.04630  -0.0474   0.9953   0.1287
  -4.000  -0.2010   0.04725   0.04228  -0.0530   0.9876   0.1465
  -3.750  -0.1547   0.04368   0.03847  -0.0596   0.9805   0.1733
  -3.500  -0.1140   0.04050   0.03519  -0.0642   0.9726   0.2038
  -3.250  -0.0769   0.03770   0.03236  -0.0677   0.9649   0.2493
  -2.250   0.1361   0.02615   0.01850  -0.0875   0.9338   0.1508
  -2.000   0.1837   0.02401   0.01573  -0.0896   0.9261   0.1194
  -1.750   0.2208   0.02267   0.01397  -0.0903   0.9138   0.1063
  -1.500   0.2556   0.02163   0.01254  -0.0907   0.9015   0.0987
  -1.250   0.2874   0.02092   0.01164  -0.0907   0.8889   0.0961
  -1.000   0.3171   0.02000   0.01065  -0.0904   0.8764   0.0952
  -0.750   0.3455   0.01933   0.00991  -0.0899   0.8640   0.0956
  -0.500   0.3726   0.01862   0.00923  -0.0892   0.8521   0.0992
  -0.250   0.3986   0.01811   0.00875  -0.0884   0.8391   0.1023
   0.000   0.4249   0.01778   0.00838  -0.0876   0.8260   0.1050
   0.250   0.4514   0.01756   0.00806  -0.0869   0.8131   0.1095
   0.500   0.4784   0.01735   0.00778  -0.0862   0.8003   0.1190
   0.750   0.5042   0.01590   0.00773  -0.0861   0.7884   0.5785
   1.000   0.5309   0.01512   0.00744  -0.0844   0.7766   1.0000
   1.250   0.5575   0.01535   0.00740  -0.0837   0.7647   1.0000
   1.500   0.5839   0.01561   0.00747  -0.0831   0.7513   1.0000
   1.750   0.6101   0.01590   0.00759  -0.0824   0.7371   1.0000
   2.000   0.6364   0.01620   0.00776  -0.0819   0.7231   1.0000
   2.250   0.6626   0.01651   0.00795  -0.0814   0.7090   1.0000
   2.500   0.6890   0.01683   0.00820  -0.0809   0.6953   1.0000
   2.750   0.7154   0.01715   0.00845  -0.0805   0.6819   1.0000
   3.000   0.7417   0.01744   0.00868  -0.0801   0.6685   1.0000
   3.250   0.7682   0.01772   0.00892  -0.0796   0.6558   1.0000
   3.500   0.7950   0.01801   0.00919  -0.0793   0.6448   1.0000
   3.750   0.8219   0.01828   0.00943  -0.0790   0.6339   1.0000
   4.000   0.8485   0.01859   0.00980  -0.0788   0.6219   1.0000
   4.250   0.8752   0.01888   0.01016  -0.0786   0.6105   1.0000
   4.500   0.9019   0.01911   0.01042  -0.0783   0.5994   1.0000
   4.750   0.9288   0.01928   0.01057  -0.0778   0.5885   1.0000
   5.000   0.9551   0.01947   0.01084  -0.0774   0.5753   1.0000
   5.250   0.9813   0.01959   0.01105  -0.0769   0.5611   1.0000
   5.500   1.0074   0.01966   0.01116  -0.0763   0.5461   1.0000
   5.750   1.0332   0.01973   0.01128  -0.0757   0.5295   1.0000
   6.000   1.0585   0.01983   0.01149  -0.0751   0.5105   1.0000
   6.250   1.0838   0.01993   0.01165  -0.0743   0.4910   1.0000
   6.500   1.1081   0.02003   0.01176  -0.0734   0.4669   1.0000
   6.750   1.1314   0.02018   0.01188  -0.0724   0.4395   1.0000
   7.000   1.1537   0.02043   0.01213  -0.0713   0.4099   1.0000
   7.250   1.1761   0.02078   0.01256  -0.0704   0.3819   1.0000
   7.500   1.1977   0.02110   0.01299  -0.0694   0.3492   1.0000
   7.750   1.2171   0.02154   0.01339  -0.0681   0.3016   1.0000
   8.000   1.2245   0.02343   0.01459  -0.0655   0.1963   1.0000
   8.250   1.2192   0.02729   0.01728  -0.0617   0.0749   1.0000
   8.500   1.2255   0.02952   0.01961  -0.0588   0.0646   1.0000
   8.750   1.2259   0.03198   0.02211  -0.0553   0.0595   1.0000
   9.000   1.2345   0.03361   0.02395  -0.0527   0.0553   1.0000
   9.250   1.2400   0.03547   0.02586  -0.0499   0.0515   1.0000
   9.500   1.2454   0.03760   0.02796  -0.0471   0.0490   1.0000
   9.750   1.2700   0.04045   0.03066  -0.0465   0.0468   1.0000
  10.000   1.2958   0.04253   0.03289  -0.0458   0.0457   1.0000
  10.250   1.3219   0.04499   0.03555  -0.0454   0.0446   1.0000
  10.500   1.3408   0.04741   0.03826  -0.0442   0.0429   1.0000
  10.750   1.3570   0.04999   0.04108  -0.0429   0.0413   1.0000
  11.000   1.3709   0.05310   0.04450  -0.0415   0.0409   1.0000
  11.250   1.3777   0.05647   0.04826  -0.0393   0.0412   1.0000
  11.500   1.3773   0.05993   0.05211  -0.0365   0.0417   1.0000
  11.750   1.3698   0.06333   0.05587  -0.0333   0.0423   1.0000
  12.000   1.3584   0.06690   0.05977  -0.0302   0.0429   1.0000
  12.250   1.3451   0.07081   0.06397  -0.0278   0.0435   1.0000
  12.500   1.3298   0.07506   0.06850  -0.0262   0.0441   1.0000
  12.750   1.3129   0.07971   0.07340  -0.0254   0.0447   1.0000
  13.000   1.2949   0.08480   0.07873  -0.0254   0.0452   1.0000
  13.250   1.2763   0.09040   0.08453  -0.0261   0.0458   1.0000
  13.500   1.1086   0.08807   0.08251  -0.0137   0.0446   1.0000
  13.750   1.0793   0.09345   0.08808  -0.0148   0.0450   1.0000
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