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GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il)
Reynolds number: 100,000
Max Cl/Cd: 51.41 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe188-il-100000.txt
Download as CSV file: xf-goe188-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 188 (SCHTTE-LANZ 3U10) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3902   0.09902   0.09438  -0.0168   1.0000   0.0477
  -7.750  -0.3898   0.09635   0.09178  -0.0201   1.0000   0.0486
  -7.500  -0.3873   0.09354   0.08903  -0.0258   1.0000   0.0493
  -7.250  -0.3799   0.09060   0.08608  -0.0324   1.0000   0.0497
  -7.000  -0.3711   0.08782   0.08322  -0.0371   1.0000   0.0500
  -6.750  -0.3659   0.08168   0.07721  -0.0360   1.0000   0.0510
  -6.500  -0.3600   0.07758   0.07323  -0.0319   1.0000   0.0532
  -6.250  -0.3518   0.07430   0.06998  -0.0323   1.0000   0.0555
  -6.000  -0.3429   0.07106   0.06675  -0.0339   1.0000   0.0586
  -5.750  -0.3301   0.06829   0.06388  -0.0377   1.0000   0.0627
  -5.500  -0.3185   0.06716   0.06239  -0.0410   1.0000   0.0645
  -5.250  -0.3224   0.06195   0.05758  -0.0369   1.0000   0.0671
  -5.000  -0.3261   0.06015   0.05584  -0.0339   1.0000   0.0700
  -4.750  -0.3269   0.05850   0.05416  -0.0322   1.0000   0.0739
  -4.500  -0.3165   0.05744   0.05267  -0.0337   1.0000   0.0793
  -4.250  -0.3087   0.05338   0.04885  -0.0328   0.9984   0.0832
  -4.000  -0.2670   0.04927   0.04444  -0.0390   0.9916   0.0963
  -3.750  -0.2282   0.04551   0.04052  -0.0439   0.9851   0.1129
  -3.500  -0.1888   0.04209   0.03687  -0.0488   0.9766   0.1397
  -3.250  -0.1488   0.03878   0.03347  -0.0534   0.9687   0.1827
  -2.250  -0.0215   0.02784   0.02316  -0.0566   0.9342   0.4796
  -2.000   0.0996   0.02574   0.01797  -0.0716   0.9283   0.1503
  -1.750   0.1441   0.02341   0.01517  -0.0722   0.9191   0.1037
  -1.500   0.1845   0.02178   0.01315  -0.0727   0.9094   0.0826
  -1.250   0.2242   0.02047   0.01163  -0.0735   0.9006   0.0739
  -1.000   0.2573   0.01935   0.01037  -0.0734   0.8893   0.0691
  -0.750   0.2869   0.01848   0.00948  -0.0728   0.8771   0.0682
  -0.500   0.3144   0.01778   0.00878  -0.0721   0.8647   0.0733
  -0.250   0.3413   0.01730   0.00818  -0.0711   0.8520   0.0760
   0.000   0.3683   0.01692   0.00764  -0.0702   0.8392   0.0813
   0.250   0.3950   0.01660   0.00727  -0.0692   0.8261   0.1019
   0.500   0.4294   0.01417   0.00701  -0.0691   0.8139   1.0000
   0.750   0.4542   0.01434   0.00687  -0.0679   0.7994   1.0000
   1.000   0.4786   0.01452   0.00681  -0.0667   0.7842   1.0000
   1.250   0.5031   0.01469   0.00680  -0.0656   0.7687   1.0000
   1.500   0.5276   0.01484   0.00679  -0.0646   0.7527   1.0000
   1.750   0.5524   0.01498   0.00678  -0.0635   0.7364   1.0000
   2.000   0.5774   0.01510   0.00676  -0.0625   0.7199   1.0000
   2.250   0.6026   0.01521   0.00673  -0.0615   0.7035   1.0000
   2.500   0.6275   0.01537   0.00682  -0.0606   0.6845   1.0000
   2.750   0.6528   0.01553   0.00687  -0.0598   0.6660   1.0000
   3.000   0.6785   0.01569   0.00691  -0.0590   0.6486   1.0000
   3.250   0.7042   0.01590   0.00701  -0.0583   0.6314   1.0000
   3.500   0.7297   0.01617   0.00726  -0.0577   0.6129   1.0000
   3.750   0.7554   0.01643   0.00745  -0.0572   0.5958   1.0000
   4.000   0.7812   0.01666   0.00761  -0.0566   0.5793   1.0000
   4.250   0.8069   0.01687   0.00775  -0.0561   0.5631   1.0000
   4.500   0.8328   0.01711   0.00797  -0.0556   0.5478   1.0000
   4.750   0.8587   0.01741   0.00824  -0.0552   0.5335   1.0000
   5.000   0.8846   0.01775   0.00860  -0.0548   0.5200   1.0000
   5.250   0.9104   0.01812   0.00900  -0.0545   0.5070   1.0000
   5.500   0.9361   0.01853   0.00944  -0.0542   0.4943   1.0000
   5.750   0.9617   0.01896   0.00998  -0.0539   0.4819   1.0000
   6.000   0.9873   0.01945   0.01053  -0.0536   0.4701   1.0000
   6.250   1.0130   0.01998   0.01111  -0.0533   0.4589   1.0000
   6.500   1.0388   0.02052   0.01169  -0.0530   0.4477   1.0000
   6.750   1.0645   0.02107   0.01231  -0.0527   0.4356   1.0000
   7.000   1.0884   0.02156   0.01289  -0.0521   0.4202   1.0000
   7.250   1.1110   0.02197   0.01342  -0.0512   0.4022   1.0000
   7.500   1.1338   0.02233   0.01388  -0.0504   0.3841   1.0000
   7.750   1.1569   0.02272   0.01434  -0.0496   0.3675   1.0000
   8.000   1.1798   0.02314   0.01484  -0.0489   0.3516   1.0000
   8.250   1.2011   0.02354   0.01543  -0.0479   0.3345   1.0000
   8.500   1.2213   0.02388   0.01601  -0.0468   0.3158   1.0000
   8.750   1.2412   0.02419   0.01650  -0.0455   0.2963   1.0000
   9.000   1.2579   0.02447   0.01705  -0.0439   0.2703   1.0000
   9.250   1.2693   0.02487   0.01753  -0.0415   0.2279   1.0000
   9.500   1.2721   0.02643   0.01872  -0.0386   0.1728   1.0000
   9.750   1.2749   0.02848   0.02052  -0.0359   0.1341   1.0000
  10.000   1.2784   0.03043   0.02237  -0.0333   0.1093   1.0000
  10.250   1.2774   0.03268   0.02455  -0.0303   0.0914   1.0000
  10.500   1.2701   0.03518   0.02700  -0.0266   0.0778   1.0000
  10.750   1.2645   0.03811   0.02988  -0.0233   0.0668   1.0000
  11.000   1.2660   0.04114   0.03283  -0.0209   0.0578   1.0000
  11.250   1.2687   0.04358   0.03541  -0.0190   0.0511   1.0000
  11.500   1.2828   0.04675   0.03862  -0.0174   0.0459   1.0000
  11.750   1.2939   0.04966   0.04181  -0.0158   0.0428   1.0000
  12.000   1.3015   0.05267   0.04502  -0.0144   0.0404   1.0000
  12.250   1.3175   0.05778   0.05015  -0.0140   0.0372   1.0000
  12.500   1.3062   0.06050   0.05322  -0.0120   0.0366   1.0000
  12.750   1.2954   0.06393   0.05700  -0.0109   0.0360   1.0000
  13.000   1.2833   0.06791   0.06130  -0.0104   0.0356   1.0000
  13.250   1.2695   0.07240   0.06608  -0.0104   0.0354   1.0000
  13.500   1.2537   0.07733   0.07130  -0.0111   0.0354   1.0000
  13.750   1.2362   0.08269   0.07692  -0.0125   0.0354   1.0000
  14.000   1.2174   0.08849   0.08295  -0.0145   0.0356   1.0000
  14.250   1.1977   0.09474   0.08941  -0.0172   0.0358   1.0000
  14.500   1.1775   0.10145   0.09632  -0.0206   0.0360   1.0000
  14.750   1.1570   0.10863   0.10367  -0.0245   0.0363   1.0000
  15.000   1.1366   0.11633   0.11152  -0.0289   0.0366   1.0000
  15.250   1.1173   0.12450   0.11980  -0.0337   0.0370   1.0000
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