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GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il)
Reynolds number: 200,000
Max Cl/Cd: 71.05 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe188-il-200000.txt
Download as CSV file: xf-goe188-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3837   0.09198   0.08869  -0.0167   1.0000   0.0194
  -7.500  -0.3808   0.08875   0.08551  -0.0183   1.0000   0.0197
  -7.250  -0.3779   0.08547   0.08227  -0.0205   1.0000   0.0200
  -7.000  -0.3714   0.08186   0.07869  -0.0236   1.0000   0.0203
  -6.750  -0.3636   0.07818   0.07504  -0.0268   1.0000   0.0207
  -6.500  -0.3547   0.07452   0.07139  -0.0297   1.0000   0.0211
  -6.250  -0.3453   0.07092   0.06780  -0.0322   1.0000   0.0216
  -6.000  -0.3357   0.06747   0.06435  -0.0342   1.0000   0.0221
  -5.750  -0.3269   0.06430   0.06117  -0.0354   1.0000   0.0227
  -5.500  -0.3328   0.06259   0.05949  -0.0332   1.0000   0.0230
  -5.250  -0.2799   0.05827   0.05484  -0.0426   0.9927   0.0247
  -5.000  -0.2345   0.05496   0.05115  -0.0487   0.9852   0.0252
  -4.750  -0.2105   0.04717   0.04334  -0.0535   0.9768   0.0265
  -4.500  -0.1777   0.04311   0.03922  -0.0578   0.9704   0.0284
  -4.250  -0.1414   0.03964   0.03553  -0.0614   0.9591   0.0313
  -4.000  -0.0946   0.03809   0.03326  -0.0639   0.9457   0.0371
  -3.750  -0.0687   0.03297   0.02825  -0.0668   0.9308   0.0409
  -3.500  -0.0369   0.03084   0.02583  -0.0677   0.9136   0.0466
  -3.250  -0.0078   0.02848   0.02302  -0.0678   0.8971   0.0526
  -3.000   0.0169   0.02656   0.02096  -0.0678   0.8821   0.0588
  -2.750   0.0428   0.02476   0.01884  -0.0675   0.8684   0.0690
  -2.500   0.0679   0.02326   0.01710  -0.0672   0.8556   0.0837
  -2.250   0.0923   0.02196   0.01557  -0.0670   0.8437   0.1107
  -1.250   0.2103   0.01711   0.00949  -0.0632   0.8009   0.0754
  -1.000   0.2397   0.01595   0.00812  -0.0621   0.7906   0.0595
  -0.750   0.2685   0.01531   0.00728  -0.0611   0.7804   0.0486
  -0.500   0.2955   0.01429   0.00620  -0.0603   0.7707   0.0449
  -0.250   0.3223   0.01362   0.00547  -0.0596   0.7607   0.0430
   0.000   0.3493   0.01308   0.00491  -0.0592   0.7497   0.0432
   0.250   0.3765   0.01276   0.00451  -0.0589   0.7391   0.0481
   0.500   0.4039   0.01249   0.00408  -0.0585   0.7287   0.0520
   0.750   0.4315   0.01226   0.00375  -0.0580   0.7176   0.0678
   1.000   0.4606   0.00979   0.00363  -0.0579   0.7054   1.0000
   1.250   0.4873   0.00987   0.00352  -0.0575   0.6927   1.0000
   1.500   0.5139   0.00995   0.00345  -0.0571   0.6795   1.0000
   1.750   0.5404   0.01004   0.00341  -0.0567   0.6652   1.0000
   2.000   0.5669   0.01014   0.00338  -0.0563   0.6498   1.0000
   2.250   0.5934   0.01026   0.00338  -0.0560   0.6337   1.0000
   2.500   0.6199   0.01039   0.00341  -0.0556   0.6161   1.0000
   2.750   0.6463   0.01052   0.00346  -0.0553   0.5961   1.0000
   3.000   0.6725   0.01068   0.00348  -0.0549   0.5759   1.0000
   3.250   0.6987   0.01083   0.00355  -0.0546   0.5526   1.0000
   3.500   0.7248   0.01102   0.00364  -0.0542   0.5307   1.0000
   3.750   0.7509   0.01123   0.00375  -0.0540   0.5095   1.0000
   4.000   0.7770   0.01150   0.00390  -0.0537   0.4924   1.0000
   4.250   0.8031   0.01179   0.00410  -0.0535   0.4769   1.0000
   4.500   0.8293   0.01210   0.00437  -0.0533   0.4629   1.0000
   4.750   0.8555   0.01243   0.00465  -0.0531   0.4503   1.0000
   5.000   0.8819   0.01275   0.00496  -0.0530   0.4388   1.0000
   5.250   0.9082   0.01309   0.00530  -0.0529   0.4283   1.0000
   5.500   0.9344   0.01348   0.00569  -0.0528   0.4188   1.0000
   5.750   0.9606   0.01384   0.00607  -0.0526   0.4090   1.0000
   6.000   0.9865   0.01418   0.00646  -0.0525   0.3981   1.0000
   6.250   1.0118   0.01450   0.00681  -0.0522   0.3851   1.0000
   6.500   1.0368   0.01480   0.00718  -0.0519   0.3712   1.0000
   6.750   1.0618   0.01511   0.00754  -0.0516   0.3582   1.0000
   7.000   1.0866   0.01543   0.00792  -0.0512   0.3458   1.0000
   7.250   1.1112   0.01573   0.00830  -0.0509   0.3323   1.0000
   7.500   1.1356   0.01604   0.00872  -0.0505   0.3191   1.0000
   7.750   1.1597   0.01636   0.00914  -0.0500   0.3056   1.0000
   8.000   1.1836   0.01668   0.00959  -0.0496   0.2911   1.0000
   8.250   1.2072   0.01699   0.01004  -0.0491   0.2742   1.0000
   8.500   1.2296   0.01733   0.01048  -0.0484   0.2498   1.0000
   8.750   1.2492   0.01792   0.01098  -0.0475   0.2055   1.0000
   9.000   1.2630   0.01924   0.01198  -0.0460   0.1498   1.0000
   9.250   1.2740   0.02091   0.01330  -0.0443   0.0976   1.0000
   9.500   1.2857   0.02242   0.01473  -0.0425   0.0783   1.0000
   9.750   1.2963   0.02393   0.01626  -0.0405   0.0636   1.0000
  10.000   1.2994   0.02596   0.01827  -0.0378   0.0482   1.0000
  10.250   1.2976   0.02815   0.02052  -0.0343   0.0368   1.0000
  10.500   1.3004   0.02971   0.02222  -0.0312   0.0311   1.0000
  10.750   1.2930   0.03220   0.02474  -0.0280   0.0281   1.0000
  11.000   1.2973   0.03403   0.02674  -0.0262   0.0254   1.0000
  11.250   1.3002   0.03610   0.02894  -0.0247   0.0232   1.0000
  11.500   1.3006   0.03855   0.03149  -0.0235   0.0219   1.0000
  11.750   1.2979   0.04148   0.03449  -0.0223   0.0208   1.0000
  12.000   1.2943   0.04485   0.03793  -0.0203   0.0199   1.0000
  12.250   1.2985   0.04738   0.04066  -0.0191   0.0193   1.0000
  12.500   1.3018   0.05014   0.04362  -0.0179   0.0188   1.0000
  12.750   1.3037   0.05310   0.04679  -0.0170   0.0183   1.0000
  13.000   1.3036   0.05623   0.05012  -0.0165   0.0176   1.0000
  13.250   1.3018   0.05949   0.05357  -0.0164   0.0168   1.0000
  13.500   1.2979   0.06307   0.05733  -0.0166   0.0162   1.0000
  13.750   1.2925   0.06693   0.06140  -0.0171   0.0158   1.0000
  14.000   1.2850   0.07131   0.06600  -0.0176   0.0156   1.0000
  14.250   1.2753   0.07607   0.07097  -0.0185   0.0155   1.0000
  14.500   1.2632   0.08134   0.07647  -0.0199   0.0154   1.0000
  14.750   1.2490   0.08710   0.08247  -0.0219   0.0155   1.0000
  15.000   1.2329   0.09352   0.08911  -0.0245   0.0155   1.0000
  15.250   1.2157   0.10048   0.09630  -0.0278   0.0156   1.0000
  15.500   1.1972   0.10809   0.10413  -0.0317   0.0158   1.0000
  15.750   1.1749   0.11702   0.11329  -0.0369   0.0161   1.0000
  16.000   1.1519   0.12664   0.12309  -0.0428   0.0164   1.0000
  16.250   1.1280   0.13710   0.13373  -0.0494   0.0168   1.0000
  16.500   1.1031   0.14869   0.14547  -0.0568   0.0173   1.0000
  16.750   1.0757   0.16208   0.15897  -0.0652   0.0183   1.0000
  17.000   1.0540   0.17448   0.17138  -0.0722   0.0194   1.0000
  17.250   1.0428   0.18399   0.18089  -0.0771   0.0200   1.0000
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