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GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il)
Reynolds number: 50,000
Max Cl/Cd: 31.83 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe187-il-50000.txt
Download as CSV file: xf-goe187-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 187 (SCHTTE-LANZ 2U10) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3871   0.11713   0.11050  -0.0105   1.0000   0.1046
  -8.750  -0.3904   0.11586   0.10933  -0.0136   1.0000   0.1072
  -8.500  -0.3975   0.11509   0.10869  -0.0173   1.0000   0.1080
  -8.250  -0.3728   0.10765   0.10123  -0.0136   1.0000   0.1171
  -8.000  -0.3767   0.10610   0.09979  -0.0162   1.0000   0.1211
  -7.750  -0.3829   0.10525   0.09907  -0.0219   1.0000   0.1224
  -7.500  -0.3649   0.09909   0.09293  -0.0167   1.0000   0.1328
  -7.250  -0.3686   0.09799   0.09194  -0.0235   1.0000   0.1366
  -7.000  -0.3552   0.09285   0.08682  -0.0193   1.0000   0.1461
  -6.750  -0.3568   0.09196   0.08599  -0.0280   1.0000   0.1513
  -6.500  -0.3453   0.08701   0.08114  -0.0230   1.0000   0.1630
  -6.250  -0.3388   0.08357   0.07779  -0.0230   1.0000   0.1716
  -5.500  -0.3247   0.07523   0.06968  -0.0258   1.0000   0.2110
  -5.000  -0.3180   0.07068   0.06526  -0.0252   1.0000   0.2526
  -4.750   0.0164   0.04419   0.03803  -0.0194   1.0000   1.0000
  -4.500   0.0289   0.04207   0.03598  -0.0207   1.0000   1.0000
  -4.250   0.0412   0.04003   0.03402  -0.0220   1.0000   1.0000
  -4.000   0.0534   0.03808   0.03214  -0.0233   1.0000   1.0000
  -3.750   0.0652   0.03623   0.03038  -0.0246   1.0000   1.0000
  -3.500   0.0249   0.03736   0.03173  -0.0137   1.0000   0.9746
  -3.250  -0.0215   0.03849   0.03313  -0.0025   1.0000   0.9441
  -3.000  -0.0647   0.03910   0.03403   0.0070   1.0000   0.9171
  -2.750  -0.1080   0.03968   0.03486   0.0164   1.0000   0.9021
  -2.500  -0.1490   0.04003   0.03541   0.0249   1.0000   0.8906
  -2.250  -0.1921   0.04028   0.03585   0.0339   1.0000   0.8872
  -2.000  -0.2340   0.04012   0.03586   0.0422   1.0000   0.8773
  -1.750  -0.2885   0.04006   0.03601   0.0530   1.0000   0.8727
  -1.500  -0.0491   0.03657   0.02922  -0.0448   1.0000   0.2624
  -1.250   0.0203   0.03472   0.02622  -0.0514   0.9910   0.1840
  -1.000   0.0868   0.03321   0.02387  -0.0571   0.9774   0.1490
  -0.750   0.1466   0.03168   0.02182  -0.0623   0.9632   0.1399
  -0.500   0.2034   0.03052   0.02022  -0.0668   0.9479   0.1338
  -0.250   0.2608   0.02942   0.01878  -0.0711   0.9327   0.1314
   0.000   0.3167   0.02839   0.01761  -0.0755   0.9170   0.1436
   0.250   0.3746   0.02746   0.01655  -0.0803   0.9012   0.1615
   0.500   0.4302   0.02455   0.01582  -0.0843   0.8864   1.0000
   0.750   0.4689   0.02487   0.01549  -0.0852   0.8653   1.0000
   1.000   0.5118   0.02499   0.01513  -0.0869   0.8463   1.0000
   1.250   0.5504   0.02512   0.01495  -0.0880   0.8278   1.0000
   1.500   0.5790   0.02553   0.01517  -0.0876   0.8068   1.0000
   1.750   0.6112   0.02575   0.01521  -0.0875   0.7890   1.0000
   2.000   0.6418   0.02601   0.01532  -0.0871   0.7725   1.0000
   2.250   0.6650   0.02671   0.01592  -0.0862   0.7536   1.0000
   2.500   0.6901   0.02732   0.01645  -0.0855   0.7371   1.0000
   2.750   0.7151   0.02798   0.01708  -0.0848   0.7220   1.0000
   3.000   0.7395   0.02872   0.01776  -0.0841   0.7077   1.0000
   3.250   0.7634   0.02954   0.01855  -0.0835   0.6943   1.0000
   3.500   0.7873   0.03040   0.01941  -0.0829   0.6820   1.0000
   3.750   0.8135   0.03106   0.02005  -0.0823   0.6713   1.0000
   4.000   0.8357   0.03211   0.02119  -0.0818   0.6594   1.0000
   4.250   0.8549   0.03352   0.02267  -0.0814   0.6473   1.0000
   4.500   0.8745   0.03492   0.02416  -0.0810   0.6361   1.0000
   4.750   0.8962   0.03596   0.02526  -0.0803   0.6247   1.0000
   5.000   0.9206   0.03654   0.02590  -0.0792   0.6126   1.0000
   5.250   0.9462   0.03686   0.02634  -0.0779   0.6001   1.0000
   5.500   0.9700   0.03741   0.02699  -0.0767   0.5874   1.0000
   5.750   0.9893   0.03852   0.02824  -0.0756   0.5742   1.0000
   6.000   1.0110   0.03920   0.02905  -0.0743   0.5604   1.0000
   6.250   1.0355   0.03941   0.02944  -0.0727   0.5459   1.0000
   6.500   1.0635   0.03894   0.02907  -0.0708   0.5301   1.0000
   6.750   1.0806   0.03963   0.02995  -0.0689   0.5109   1.0000
   7.000   1.1111   0.03848   0.02887  -0.0666   0.4915   1.0000
   7.250   1.1377   0.03796   0.02850  -0.0645   0.4716   1.0000
   7.500   1.1613   0.03797   0.02864  -0.0626   0.4507   1.0000
   7.750   1.1865   0.03795   0.02873  -0.0608   0.4289   1.0000
   8.000   1.2120   0.03808   0.02892  -0.0590   0.4051   1.0000
   8.250   1.2299   0.03912   0.03012  -0.0570   0.3793   1.0000
   8.500   1.2481   0.04033   0.03151  -0.0551   0.3542   1.0000
   8.750   1.2719   0.04114   0.03233  -0.0535   0.3319   1.0000
   9.000   1.2831   0.04322   0.03471  -0.0516   0.3126   1.0000
   9.250   1.2985   0.04504   0.03677  -0.0500   0.2972   1.0000
   9.500   1.3117   0.04722   0.03922  -0.0484   0.2849   1.0000
   9.750   1.3382   0.04520   0.03716  -0.0464   0.2612   1.0000
  10.000   1.3486   0.04528   0.03746  -0.0440   0.2417   1.0000
  10.250   1.3565   0.04411   0.03626  -0.0409   0.2164   1.0000
  10.500   1.3535   0.04412   0.03618  -0.0373   0.1912   1.0000
  10.750   1.3467   0.04586   0.03778  -0.0337   0.1664   1.0000
  11.000   1.3327   0.04872   0.04041  -0.0297   0.1411   1.0000
  11.250   1.3162   0.05220   0.04398  -0.0263   0.1232   1.0000
  11.500   1.3054   0.05566   0.04740  -0.0240   0.1087   1.0000
  11.750   1.2994   0.05921   0.05096  -0.0224   0.0977   1.0000
  12.000   1.3013   0.06280   0.05454  -0.0209   0.0884   1.0000
  12.250   1.2981   0.06697   0.05901  -0.0198   0.0834   1.0000
  12.500   1.3089   0.07110   0.06313  -0.0184   0.0778   1.0000
  12.750   1.2933   0.07602   0.06842  -0.0183   0.0771   1.0000
  13.000   1.2754   0.08145   0.07418  -0.0191   0.0767   1.0000
  13.250   1.2557   0.08742   0.08043  -0.0206   0.0767   1.0000
  13.500   1.2344   0.09396   0.08721  -0.0230   0.0769   1.0000
  13.750   1.2123   0.10107   0.09451  -0.0261   0.0775   1.0000
  14.000   1.1902   0.10870   0.10229  -0.0298   0.0781   1.0000
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