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GOE 100 (SOPWITH) AIRFOIL (goe100-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 100 (SOPWITH) AIRFOIL (goe100-il)
Reynolds number: 100,000
Max Cl/Cd: 54.41 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe100-il-100000.txt
Download as CSV file: xf-goe100-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 100 (SOPWITH) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3112   0.10194   0.09737  -0.0227   1.0000   0.0612
  -8.750  -0.3093   0.09869   0.09416  -0.0230   1.0000   0.0629
  -8.500  -0.4097   0.10696   0.10218  -0.0190   1.0000   0.0579
  -8.250  -0.4016   0.10315   0.09839  -0.0184   1.0000   0.0596
  -8.000  -0.3974   0.10002   0.09530  -0.0187   1.0000   0.0612
  -7.750  -0.3954   0.09712   0.09245  -0.0192   1.0000   0.0629
  -7.500  -0.3961   0.09445   0.08985  -0.0196   1.0000   0.0646
  -7.250  -0.3980   0.09187   0.08736  -0.0206   1.0000   0.0663
  -7.000  -0.3983   0.08946   0.08501  -0.0242   1.0000   0.0682
  -6.750  -0.3955   0.08773   0.08328  -0.0314   1.0000   0.0694
  -6.500  -0.3898   0.08441   0.07996  -0.0346   1.0000   0.0700
  -6.250  -0.3877   0.07924   0.07491  -0.0291   1.0000   0.0714
  -6.000  -0.3828   0.07606   0.07177  -0.0270   1.0000   0.0734
  -5.750  -0.3769   0.07313   0.06885  -0.0267   1.0000   0.0760
  -5.500  -0.3685   0.07017   0.06582  -0.0282   1.0000   0.0798
  -5.250  -0.3511   0.06689   0.06233  -0.0346   1.0000   0.0838
  -5.000  -0.3488   0.06341   0.05898  -0.0306   1.0000   0.0863
  -4.750  -0.3235   0.06149   0.05667  -0.0360   1.0000   0.0967
  -4.500  -0.3233   0.05738   0.05284  -0.0315   1.0000   0.1001
  -4.250  -0.3012   0.05449   0.04969  -0.0344   1.0000   0.1110
  -4.000  -0.2912   0.05142   0.04670  -0.0323   1.0000   0.1154
  -3.750  -0.2699   0.04834   0.04343  -0.0339   1.0000   0.1262
  -3.500  -0.2478   0.04562   0.04050  -0.0349   1.0000   0.1389
  -3.250  -0.2263   0.04300   0.03771  -0.0354   1.0000   0.1523
  -3.000  -0.2041   0.04035   0.03490  -0.0357   1.0000   0.1660
  -2.750  -0.1423   0.02937   0.02237  -0.0399   1.0000   0.0670
  -2.500  -0.1106   0.02681   0.01903  -0.0401   1.0000   0.0696
  -2.250  -0.0776   0.02363   0.01535  -0.0410   1.0000   0.0718
  -2.000  -0.0473   0.02185   0.01329  -0.0412   1.0000   0.0781
  -1.750  -0.0182   0.02071   0.01181  -0.0411   1.0000   0.0969
  -1.500   0.0085   0.02006   0.01112  -0.0410   1.0000   0.1224
  -1.250   0.0329   0.01982   0.01090  -0.0409   1.0000   0.1465
  -1.000   0.0599   0.01920   0.01021  -0.0408   1.0000   0.1589
  -0.750   0.0859   0.01885   0.00977  -0.0407   1.0000   0.1773
  -0.500   0.1130   0.01829   0.00936  -0.0409   1.0000   0.2039
  -0.250   0.1436   0.01745   0.00895  -0.0417   1.0000   0.2865
   0.000   0.1639   0.01552   0.00888  -0.0400   1.0000   1.0000
   0.250   0.1960   0.01592   0.00894  -0.0414   0.9967   1.0000
   0.500   0.2522   0.01627   0.00902  -0.0475   0.9847   1.0000
   0.750   0.3077   0.01645   0.00902  -0.0532   0.9712   1.0000
   1.000   0.3636   0.01643   0.00888  -0.0588   0.9567   1.0000
   1.250   0.4124   0.01623   0.00863  -0.0626   0.9396   1.0000
   1.500   0.4624   0.01589   0.00828  -0.0664   0.9230   1.0000
   1.750   0.5135   0.01539   0.00781  -0.0701   0.9073   1.0000
   2.000   0.5596   0.01483   0.00728  -0.0726   0.8903   1.0000
   2.250   0.5956   0.01438   0.00687  -0.0729   0.8680   1.0000
   2.500   0.6288   0.01393   0.00646  -0.0726   0.8419   1.0000
   2.750   0.6582   0.01357   0.00616  -0.0715   0.8088   1.0000
   3.000   0.6846   0.01331   0.00586  -0.0698   0.7633   1.0000
   3.250   0.7096   0.01319   0.00558  -0.0679   0.6957   1.0000
   3.500   0.7329   0.01347   0.00539  -0.0657   0.6024   1.0000
   3.750   0.7532   0.01426   0.00562  -0.0637   0.5199   1.0000
   4.000   0.7724   0.01511   0.00605  -0.0619   0.4495   1.0000
   4.250   0.7924   0.01584   0.00642  -0.0604   0.3938   1.0000
   4.500   0.8134   0.01648   0.00681  -0.0593   0.3498   1.0000
   4.750   0.8358   0.01705   0.00725  -0.0584   0.3173   1.0000
   5.000   0.8588   0.01759   0.00772  -0.0576   0.2930   1.0000
   5.250   0.8812   0.01802   0.00812  -0.0568   0.2605   1.0000
   5.500   0.9038   0.01850   0.00846  -0.0560   0.2286   1.0000
   5.750   0.9278   0.01896   0.00896  -0.0553   0.2087   1.0000
   6.000   0.9513   0.01946   0.00943  -0.0546   0.1827   1.0000
   6.250   0.9753   0.01995   0.00993  -0.0538   0.1622   1.0000
   6.500   0.9988   0.02055   0.01045  -0.0530   0.1278   1.0000
   6.750   1.0150   0.02233   0.01162  -0.0514   0.0444   1.0000
   7.000   1.0355   0.02356   0.01292  -0.0500   0.0384   1.0000
   7.250   1.0569   0.02461   0.01422  -0.0486   0.0371   1.0000
   7.500   1.0772   0.02577   0.01564  -0.0472   0.0364   1.0000
   7.750   1.0957   0.02704   0.01719  -0.0455   0.0362   1.0000
   8.000   1.1121   0.02844   0.01883  -0.0435   0.0362   1.0000
   8.250   1.1264   0.02997   0.02058  -0.0412   0.0365   1.0000
   8.500   1.1400   0.03166   0.02242  -0.0389   0.0370   1.0000
   8.750   1.1549   0.03361   0.02454  -0.0367   0.0376   1.0000
   9.000   1.1737   0.03593   0.02692  -0.0351   0.0381   1.0000
   9.250   1.1945   0.03838   0.02953  -0.0338   0.0379   1.0000
   9.500   1.2149   0.04118   0.03256  -0.0325   0.0378   1.0000
   9.750   1.2390   0.04544   0.03701  -0.0320   0.0391   1.0000
  10.000   1.2530   0.04641   0.03855  -0.0291   0.0413   1.0000
  10.250   1.2575   0.05019   0.04302  -0.0260   0.0443   1.0000
  10.500   1.2569   0.05456   0.04787  -0.0231   0.0467   1.0000
  10.750   1.2561   0.05984   0.05344  -0.0210   0.0487   1.0000
  11.000   1.2533   0.06261   0.05667  -0.0178   0.0511   1.0000
  11.250   1.2276   0.06604   0.06050  -0.0137   0.0519   1.0000
  11.500   1.2013   0.07008   0.06485  -0.0115   0.0522   1.0000
  11.750   1.1757   0.07480   0.06982  -0.0112   0.0523   1.0000
  12.000   1.1510   0.08025   0.07547  -0.0127   0.0523   1.0000
  12.250   1.1275   0.08645   0.08184  -0.0157   0.0520   1.0000
  12.500   1.1046   0.09367   0.08918  -0.0203   0.0517   1.0000
  12.750   1.0828   0.10174   0.09734  -0.0259   0.0513   1.0000
  13.000   1.0600   0.11087   0.10653  -0.0323   0.0507   1.0000
  13.250   1.0359   0.12116   0.11683  -0.0393   0.0502   1.0000
  13.500   0.9823   0.14317   0.13876  -0.0545   0.0516   1.0000
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