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GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il)
Reynolds number: 100,000
Max Cl/Cd: 58.22 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe187-il-100000-n5.txt
Download as CSV file: xf-goe187-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3076   0.10640   0.10180  -0.0253   1.0000   0.0244
  -8.000  -0.3051   0.10407   0.09954  -0.0268   1.0000   0.0245
  -7.750  -0.3032   0.10176   0.09732  -0.0282   1.0000   0.0245
  -7.500  -0.2984   0.09924   0.09486  -0.0306   1.0000   0.0246
  -7.250  -0.2932   0.09668   0.09237  -0.0328   1.0000   0.0247
  -7.000  -0.2882   0.09415   0.08991  -0.0347   1.0000   0.0247
  -6.750  -0.2836   0.09169   0.08751  -0.0362   1.0000   0.0248
  -6.500  -0.2808   0.08942   0.08528  -0.0368   1.0000   0.0248
  -6.250  -0.2680   0.08414   0.08008  -0.0388   0.9955   0.0252
  -6.000  -0.2568   0.07868   0.07467  -0.0375   0.9896   0.0262
  -5.750  -0.2310   0.07416   0.07010  -0.0424   0.9807   0.0273
  -5.500  -0.2008   0.06972   0.06560  -0.0488   0.9709   0.0285
  -5.250  -0.1680   0.06534   0.06114  -0.0555   0.9608   0.0299
  -5.000  -0.1332   0.06106   0.05675  -0.0622   0.9506   0.0315
  -4.750  -0.0918   0.05699   0.05249  -0.0697   0.9408   0.0338
  -4.500  -0.0418   0.05434   0.04936  -0.0773   0.9290   0.0352
  -4.250  -0.0135   0.04948   0.04441  -0.0805   0.9174   0.0359
  -4.000   0.0099   0.04526   0.04018  -0.0824   0.9040   0.0376
  -3.750   0.0403   0.04208   0.03680  -0.0846   0.8886   0.0400
  -3.500   0.0735   0.03935   0.03375  -0.0866   0.8726   0.0433
  -3.250   0.1085   0.03692   0.03081  -0.0882   0.8576   0.0478
  -3.000   0.1317   0.03399   0.02784  -0.0888   0.8437   0.0529
  -2.750   0.1603   0.03180   0.02533  -0.0896   0.8303   0.0652
  -2.500   0.1902   0.03084   0.02389  -0.0901   0.8172   0.0877
  -2.000   0.2556   0.02543   0.01769  -0.0888   0.7942   0.0310
  -1.750   0.2862   0.02366   0.01547  -0.0883   0.7830   0.0279
  -1.500   0.3166   0.02233   0.01362  -0.0876   0.7715   0.0260
  -1.250   0.3444   0.02101   0.01208  -0.0874   0.7595   0.0280
  -1.000   0.3728   0.01999   0.01079  -0.0869   0.7479   0.0303
  -0.750   0.4011   0.01896   0.00950  -0.0863   0.7366   0.0307
  -0.500   0.4289   0.01807   0.00839  -0.0856   0.7255   0.0318
  -0.250   0.4561   0.01745   0.00760  -0.0849   0.7134   0.0359
   0.000   0.4822   0.01664   0.00677  -0.0844   0.7013   0.0397
   0.250   0.5091   0.01624   0.00618  -0.0839   0.6892   0.0455
   0.500   0.5363   0.01587   0.00561  -0.0835   0.6768   0.0557
   0.750   0.5643   0.01562   0.00520  -0.0832   0.6639   0.0758
   1.000   0.5945   0.01347   0.00498  -0.0836   0.6508   1.0000
   1.250   0.6212   0.01363   0.00483  -0.0832   0.6371   1.0000
   1.500   0.6478   0.01380   0.00478  -0.0828   0.6233   1.0000
   1.750   0.6742   0.01397   0.00476  -0.0824   0.6087   1.0000
   2.000   0.7006   0.01415   0.00479  -0.0821   0.5933   1.0000
   2.250   0.7268   0.01434   0.00484  -0.0817   0.5775   1.0000
   2.500   0.7530   0.01454   0.00493  -0.0814   0.5616   1.0000
   2.750   0.7791   0.01476   0.00504  -0.0811   0.5464   1.0000
   3.000   0.8052   0.01500   0.00518  -0.0807   0.5319   1.0000
   3.250   0.8311   0.01525   0.00536  -0.0804   0.5180   1.0000
   3.500   0.8570   0.01552   0.00554  -0.0801   0.5048   1.0000
   3.750   0.8828   0.01581   0.00575  -0.0798   0.4930   1.0000
   4.000   0.9085   0.01612   0.00604  -0.0795   0.4813   1.0000
   4.250   0.9340   0.01644   0.00632  -0.0791   0.4689   1.0000
   4.500   0.9589   0.01677   0.00660  -0.0787   0.4552   1.0000
   4.750   0.9836   0.01712   0.00690  -0.0782   0.4408   1.0000
   5.000   1.0081   0.01749   0.00727  -0.0778   0.4270   1.0000
   5.250   1.0327   0.01786   0.00764  -0.0773   0.4145   1.0000
   5.500   1.0572   0.01825   0.00804  -0.0769   0.4036   1.0000
   5.750   1.0816   0.01864   0.00851  -0.0765   0.3932   1.0000
   6.000   1.1064   0.01903   0.00901  -0.0761   0.3840   1.0000
   6.250   1.1308   0.01944   0.00949  -0.0757   0.3760   1.0000
   6.500   1.1547   0.01984   0.01002  -0.0752   0.3651   1.0000
   6.750   1.1784   0.02024   0.01061  -0.0747   0.3540   1.0000
   7.000   1.2018   0.02067   0.01118  -0.0741   0.3439   1.0000
   7.250   1.2246   0.02112   0.01175  -0.0735   0.3329   1.0000
   7.500   1.2475   0.02155   0.01242  -0.0728   0.3211   1.0000
   7.750   1.2697   0.02201   0.01315  -0.0721   0.3082   1.0000
   8.000   1.2895   0.02250   0.01379  -0.0710   0.2852   1.0000
   8.250   1.3030   0.02331   0.01439  -0.0692   0.2220   1.0000
   8.500   1.3078   0.02517   0.01564  -0.0667   0.1570   1.0000
   8.750   1.3173   0.02679   0.01705  -0.0647   0.1142   1.0000
   9.000   1.3243   0.02855   0.01861  -0.0624   0.0866   1.0000
   9.250   1.3241   0.03078   0.02052  -0.0594   0.0291   1.0000
   9.500   1.3203   0.03298   0.02265  -0.0558   0.0201   1.0000
   9.750   1.3206   0.03481   0.02466  -0.0527   0.0178   1.0000
  10.000   1.3202   0.03685   0.02691  -0.0500   0.0164   1.0000
  10.250   1.3179   0.03921   0.02949  -0.0477   0.0151   1.0000
  10.500   1.3131   0.04200   0.03259  -0.0458   0.0140   1.0000
  10.750   1.3075   0.04510   0.03592  -0.0445   0.0132   1.0000
  11.000   1.3045   0.04811   0.03917  -0.0437   0.0127   1.0000
  11.250   1.2995   0.05154   0.04283  -0.0432   0.0123   1.0000
  11.500   1.2931   0.05530   0.04682  -0.0431   0.0120   1.0000
  11.750   1.2857   0.05937   0.05110  -0.0434   0.0118   1.0000
  12.000   1.2775   0.06366   0.05559  -0.0438   0.0116   1.0000
  12.250   1.2689   0.06815   0.06028  -0.0445   0.0115   1.0000
  12.500   1.2602   0.07274   0.06505  -0.0453   0.0113   1.0000
  12.750   1.2517   0.07740   0.06988  -0.0462   0.0112   1.0000
  13.000   1.2439   0.08203   0.07468  -0.0471   0.0111   1.0000
  13.250   1.2371   0.08656   0.07936  -0.0480   0.0109   1.0000
  13.500   1.2314   0.09099   0.08395  -0.0488   0.0107   1.0000
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