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GOE 670 AIRFOIL (goe670-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 670 AIRFOIL (goe670-il)
Reynolds number: 50,000
Max Cl/Cd: 35.66 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe670-il-50000.txt
Download as CSV file: xf-goe670-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 670 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3926   0.11006   0.10291  -0.0275   1.0000   0.2060
  -8.500  -0.3740   0.10500   0.09785  -0.0258   1.0000   0.2140
  -8.250  -0.3894   0.10419   0.09717  -0.0251   1.0000   0.2208
  -8.000  -0.3867   0.10078   0.09382  -0.0239   1.0000   0.2259
  -7.750  -0.3895   0.09869   0.09179  -0.0222   1.0000   0.2348
  -7.500  -0.4247   0.09922   0.09254  -0.0200   1.0000   0.2376
  -7.250  -0.3997   0.09412   0.08740  -0.0183   1.0000   0.2486
  -7.000  -0.4347   0.09428   0.08776  -0.0163   1.0000   0.2530
  -6.750  -0.4185   0.09015   0.08363  -0.0134   1.0000   0.2631
  -6.500  -0.4565   0.09030   0.08394  -0.0139   1.0000   0.2693
  -6.250  -0.4443   0.08655   0.08022  -0.0102   1.0000   0.2834
  -6.000  -0.4412   0.08364   0.07737  -0.0074   1.0000   0.2968
  -5.750  -0.4443   0.08118   0.07496  -0.0049   1.0000   0.3115
  -5.500  -0.4489   0.07885   0.07270  -0.0027   1.0000   0.3276
  -5.250  -0.4614   0.07718   0.07107  -0.0016   1.0000   0.3462
  -5.000  -0.4559   0.07394   0.06791   0.0024   1.0000   0.3650
  -4.750  -0.4533   0.07151   0.06553   0.0063   1.0000   0.3886
  -4.500   0.0291   0.04716   0.03978  -0.0342   1.0000   1.0000
  -4.250   0.0337   0.04568   0.03837  -0.0335   1.0000   1.0000
  -4.000  -0.1692   0.05555   0.04898   0.0102   1.0000   0.8526
  -3.750  -0.0980   0.05052   0.04378  -0.0006   1.0000   0.9215
  -3.500  -0.1686   0.05198   0.04554   0.0135   1.0000   0.8667
  -3.250  -0.2491   0.05319   0.04706   0.0268   1.0000   0.8057
  -3.000  -0.3227   0.05356   0.04771   0.0381   1.0000   0.7642
  -2.750  -0.2970   0.04203   0.03344  -0.0254   1.0000   0.2052
  -2.500  -0.2701   0.03932   0.03003  -0.0262   1.0000   0.1910
  -2.250  -0.2485   0.03747   0.02782  -0.0258   1.0000   0.1911
  -2.000  -0.2269   0.03575   0.02577  -0.0253   1.0000   0.1909
  -1.750  -0.2050   0.03417   0.02385  -0.0247   1.0000   0.1905
  -1.500  -0.1833   0.03279   0.02218  -0.0241   1.0000   0.1922
  -1.250  -0.1638   0.03181   0.02117  -0.0233   1.0000   0.1994
  -1.000  -0.1418   0.03101   0.01999  -0.0226   1.0000   0.2075
  -0.750  -0.1201   0.03016   0.01908  -0.0221   1.0000   0.2150
  -0.500  -0.0995   0.02957   0.01838  -0.0213   1.0000   0.2288
  -0.250  -0.0778   0.02911   0.01781  -0.0206   1.0000   0.2446
   0.000  -0.0525   0.02880   0.01739  -0.0206   1.0000   0.2670
   0.250  -0.0273   0.02847   0.01710  -0.0207   1.0000   0.2939
   0.500  -0.0032   0.02818   0.01695  -0.0206   1.0000   0.3332
   0.750   0.0213   0.02764   0.01692  -0.0206   1.0000   0.4019
   1.000   0.0624   0.02616   0.01668  -0.0230   1.0000   1.0000
   1.250   0.0805   0.02682   0.01699  -0.0223   1.0000   1.0000
   1.500   0.0980   0.02752   0.01746  -0.0217   1.0000   1.0000
   1.750   0.1152   0.02826   0.01802  -0.0211   1.0000   1.0000
   2.000   0.1487   0.02952   0.01911  -0.0238   0.9931   1.0000
   2.250   0.2023   0.03119   0.02063  -0.0302   0.9738   1.0000
   2.500   0.2610   0.03263   0.02197  -0.0369   0.9477   1.0000
   2.750   0.3196   0.03365   0.02294  -0.0429   0.9197   1.0000
   3.000   0.3776   0.03437   0.02365  -0.0483   0.8944   1.0000
   3.250   0.4196   0.03483   0.02413  -0.0509   0.8717   1.0000
   3.500   0.4755   0.03512   0.02448  -0.0552   0.8513   1.0000
   3.750   0.5081   0.03532   0.02476  -0.0558   0.8275   1.0000
   4.000   0.5666   0.03492   0.02450  -0.0596   0.8064   1.0000
   4.250   0.6031   0.03465   0.02437  -0.0599   0.7806   1.0000
   4.500   0.6550   0.03364   0.02353  -0.0617   0.7559   1.0000
   4.750   0.7254   0.03145   0.02162  -0.0651   0.7321   1.0000
   5.000   0.7850   0.02935   0.01973  -0.0666   0.7026   1.0000
   5.250   0.8402   0.02750   0.01804  -0.0674   0.6661   1.0000
   5.500   0.8975   0.02610   0.01660  -0.0689   0.6243   1.0000
   5.750   0.9264   0.02641   0.01683  -0.0676   0.5841   1.0000
   6.000   0.9540   0.02690   0.01729  -0.0665   0.5516   1.0000
   6.250   0.9777   0.02760   0.01798  -0.0651   0.5250   1.0000
   6.500   1.0060   0.02821   0.01854  -0.0644   0.5031   1.0000
   6.750   1.0263   0.02911   0.01951  -0.0628   0.4824   1.0000
   7.000   1.0495   0.02984   0.02029  -0.0615   0.4620   1.0000
   7.250   1.0759   0.03053   0.02091  -0.0606   0.4417   1.0000
   7.500   1.0943   0.03164   0.02215  -0.0588   0.4232   1.0000
   7.750   1.1145   0.03285   0.02348  -0.0573   0.4058   1.0000
   8.000   1.1360   0.03379   0.02447  -0.0558   0.3846   1.0000
   8.250   1.1503   0.03453   0.02522  -0.0531   0.3584   1.0000
   8.500   1.1620   0.03480   0.02536  -0.0498   0.3269   1.0000
   8.750   1.1708   0.03525   0.02573  -0.0463   0.2965   1.0000
   9.000   1.1774   0.03597   0.02636  -0.0426   0.2640   1.0000
   9.250   1.1755   0.03715   0.02744  -0.0377   0.2248   1.0000
   9.500   1.1702   0.03864   0.02858  -0.0324   0.1842   1.0000
   9.750   1.1705   0.04028   0.03005  -0.0282   0.1568   1.0000
  10.000   1.1743   0.04223   0.03213  -0.0247   0.1386   1.0000
  10.250   1.1847   0.04427   0.03418  -0.0223   0.1254   1.0000
  10.500   1.2049   0.04680   0.03663  -0.0213   0.1157   1.0000
  10.750   1.2130   0.04968   0.03990  -0.0189   0.1093   1.0000
  11.000   1.2288   0.05245   0.04267  -0.0178   0.1030   1.0000
  11.250   1.2246   0.05577   0.04648  -0.0144   0.1004   1.0000
  11.500   1.2188   0.05926   0.05034  -0.0112   0.0989   1.0000
  11.750   1.2076   0.06293   0.05435  -0.0080   0.0981   1.0000
  12.000   1.1902   0.06687   0.05860  -0.0051   0.0979   1.0000
  12.250   1.1666   0.07126   0.06329  -0.0028   0.0982   1.0000
  12.500   1.1374   0.07636   0.06866  -0.0015   0.0989   1.0000
  12.750   1.1053   0.08233   0.07484  -0.0019   0.1001   1.0000
  13.000   1.0719   0.08938   0.08203  -0.0039   0.1014   1.0000
  13.250   1.0406   0.09740   0.09015  -0.0073   0.1027   1.0000
  13.500   1.0152   0.10584   0.09864  -0.0112   0.1038   1.0000
  13.750   0.8954   0.14069   0.13323  -0.0355   0.1279   1.0000
  14.000   0.8886   0.14826   0.14079  -0.0389   0.1310   1.0000
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