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GOE 101 AIRFOIL (goe101-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 101 AIRFOIL (goe101-il)
Reynolds number: 100,000
Max Cl/Cd: 59.52 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe101-il-100000-n5.txt
Download as CSV file: xf-goe101-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 101 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3716   0.10638   0.10156  -0.0213   1.0000   0.0314
  -8.250  -0.3689   0.10361   0.09885  -0.0228   1.0000   0.0315
  -8.000  -0.3666   0.10080   0.09611  -0.0241   1.0000   0.0315
  -7.750  -0.3619   0.09776   0.09313  -0.0261   1.0000   0.0316
  -7.500  -0.3553   0.09447   0.08988  -0.0287   1.0000   0.0316
  -7.250  -0.3477   0.09101   0.08645  -0.0313   1.0000   0.0317
  -7.000  -0.3392   0.08749   0.08297  -0.0337   1.0000   0.0317
  -6.750  -0.3320   0.08338   0.07892  -0.0350   1.0000   0.0318
  -6.500  -0.3305   0.07885   0.07446  -0.0321   1.0000   0.0325
  -6.250  -0.3246   0.07553   0.07115  -0.0314   1.0000   0.0332
  -6.000  -0.3181   0.07256   0.06822  -0.0311   1.0000   0.0344
  -5.750  -0.3099   0.06968   0.06537  -0.0319   1.0000   0.0364
  -5.500  -0.2988   0.06665   0.06234  -0.0342   1.0000   0.0395
  -5.250  -0.2692   0.06373   0.05915  -0.0428   1.0000   0.0428
  -4.750  -0.2360   0.05453   0.04996  -0.0464   0.9925   0.0450
  -4.500  -0.2033   0.05045   0.04578  -0.0508   0.9836   0.0480
  -4.250  -0.1463   0.04507   0.03968  -0.0595   0.9738   0.0428
  -4.000  -0.1131   0.04021   0.03466  -0.0632   0.9644   0.0420
  -3.750  -0.0784   0.03575   0.02994  -0.0667   0.9546   0.0398
  -3.500  -0.0405   0.03184   0.02557  -0.0697   0.9438   0.0394
  -3.000   0.0340   0.02615   0.01862  -0.0732   0.9189   0.0433
  -2.750   0.0655   0.02381   0.01613  -0.0748   0.9047   0.0470
  -2.500   0.0990   0.02218   0.01410  -0.0757   0.8893   0.0498
  -2.250   0.1322   0.02056   0.01206  -0.0763   0.8730   0.0503
  -2.000   0.1644   0.01931   0.01045  -0.0766   0.8558   0.0516
  -1.750   0.1948   0.01864   0.00941  -0.0765   0.8361   0.0555
  -1.500   0.2242   0.01772   0.00826  -0.0763   0.8160   0.0556
  -1.250   0.2529   0.01692   0.00728  -0.0760   0.7960   0.0556
  -1.000   0.2804   0.01627   0.00650  -0.0755   0.7753   0.0557
  -0.750   0.3074   0.01574   0.00583  -0.0750   0.7559   0.0560
  -0.500   0.3338   0.01528   0.00528  -0.0744   0.7368   0.0567
  -0.250   0.3602   0.01492   0.00480  -0.0738   0.7179   0.0581
   0.000   0.3870   0.01471   0.00444  -0.0734   0.7001   0.0605
   0.250   0.4136   0.01460   0.00417  -0.0729   0.6835   0.0642
   0.750   0.4678   0.01438   0.00380  -0.0721   0.6534   0.0944
   1.000   0.5007   0.01228   0.00375  -0.0732   0.6394   1.0000
   1.250   0.5270   0.01248   0.00373  -0.0727   0.6263   1.0000
   1.500   0.5534   0.01268   0.00377  -0.0723   0.6144   1.0000
   1.750   0.5798   0.01289   0.00384  -0.0719   0.6039   1.0000
   2.000   0.6062   0.01311   0.00394  -0.0716   0.5934   1.0000
   2.250   0.6325   0.01334   0.00409  -0.0712   0.5833   1.0000
   2.500   0.6589   0.01358   0.00426  -0.0709   0.5747   1.0000
   2.750   0.6853   0.01382   0.00447  -0.0706   0.5659   1.0000
   3.000   0.7116   0.01408   0.00469  -0.0703   0.5572   1.0000
   3.250   0.7377   0.01433   0.00490  -0.0699   0.5483   1.0000
   3.500   0.7636   0.01458   0.00519  -0.0695   0.5376   1.0000
   3.750   0.7891   0.01483   0.00543  -0.0690   0.5258   1.0000
   4.000   0.8142   0.01506   0.00565  -0.0684   0.5121   1.0000
   4.250   0.8393   0.01530   0.00593  -0.0678   0.4987   1.0000
   4.500   0.8647   0.01556   0.00622  -0.0673   0.4874   1.0000
   4.750   0.8901   0.01583   0.00657  -0.0668   0.4767   1.0000
   5.000   0.9156   0.01612   0.00697  -0.0664   0.4669   1.0000
   5.250   0.9409   0.01641   0.00739  -0.0659   0.4573   1.0000
   5.500   0.9658   0.01670   0.00779  -0.0654   0.4456   1.0000
   5.750   0.9906   0.01698   0.00824  -0.0648   0.4325   1.0000
   6.000   1.0150   0.01727   0.00869  -0.0641   0.4183   1.0000
   6.250   1.0370   0.01748   0.00900  -0.0630   0.3869   1.0000
   6.500   1.0582   0.01778   0.00933  -0.0619   0.3403   1.0000
   6.750   1.0753   0.01856   0.00972  -0.0604   0.2562   1.0000
   7.000   1.0895   0.02002   0.01072  -0.0588   0.1845   1.0000
   7.250   1.1007   0.02198   0.01210  -0.0572   0.0923   1.0000
   7.500   1.1110   0.02404   0.01373  -0.0552   0.0376   1.0000
   7.750   1.1246   0.02563   0.01539  -0.0533   0.0287   1.0000
   8.000   1.1386   0.02708   0.01702  -0.0516   0.0246   1.0000
   8.250   1.1494   0.02878   0.01891  -0.0496   0.0226   1.0000
   8.500   1.1581   0.03057   0.02089  -0.0473   0.0215   1.0000
   8.750   1.1682   0.03213   0.02267  -0.0452   0.0205   1.0000
   9.000   1.1769   0.03377   0.02451  -0.0431   0.0191   1.0000
   9.250   1.1839   0.03550   0.02640  -0.0408   0.0179   1.0000
   9.500   1.1895   0.03741   0.02847  -0.0383   0.0172   1.0000
   9.750   1.1966   0.03949   0.03070  -0.0362   0.0167   1.0000
  10.000   1.2056   0.04169   0.03307  -0.0344   0.0162   1.0000
  10.250   1.2153   0.04412   0.03577  -0.0328   0.0158   1.0000
  10.500   1.2242   0.04676   0.03863  -0.0312   0.0155   1.0000
  10.750   1.2299   0.04954   0.04165  -0.0298   0.0150   1.0000
  11.000   1.2310   0.05243   0.04477  -0.0285   0.0144   1.0000
  11.250   1.2290   0.05561   0.04817  -0.0274   0.0139   1.0000
  11.500   1.2247   0.05916   0.05195  -0.0267   0.0135   1.0000
  11.750   1.2182   0.06306   0.05609  -0.0265   0.0133   1.0000
  12.000   1.2079   0.06757   0.06084  -0.0268   0.0130   1.0000
  12.250   1.1968   0.07227   0.06579  -0.0277   0.0128   1.0000
  12.500   1.1847   0.07725   0.07102  -0.0292   0.0128   1.0000
  12.750   1.1716   0.08259   0.07659  -0.0313   0.0128   1.0000
  13.000   1.1573   0.08843   0.08266  -0.0341   0.0128   1.0000
  13.250   1.1435   0.09447   0.08891  -0.0373   0.0129   1.0000
  13.500   1.1279   0.10123   0.09586  -0.0412   0.0129   1.0000
  13.750   1.1124   0.10839   0.10321  -0.0457   0.0130   1.0000
  14.000   1.0965   0.11627   0.11128  -0.0508   0.0132   1.0000
  14.250   1.0784   0.12565   0.12084  -0.0570   0.0136   1.0000
  14.500   1.0540   0.13859   0.13398  -0.0654   0.0144   1.0000
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