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GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il)
Reynolds number: 100,000
Max Cl/Cd: 53.66 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe187-il-100000.txt
Download as CSV file: xf-goe187-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3840   0.11643   0.11166  -0.0147   1.0000   0.0381
  -8.750  -0.3818   0.11434   0.10964  -0.0178   1.0000   0.0383
  -8.500  -0.3798   0.11208   0.10745  -0.0208   1.0000   0.0384
  -8.250  -0.3748   0.10944   0.10486  -0.0249   1.0000   0.0385
  -8.000  -0.3665   0.10645   0.10189  -0.0294   1.0000   0.0386
  -7.750  -0.3558   0.09733   0.09281  -0.0190   1.0000   0.0406
  -7.500  -0.3498   0.09395   0.08948  -0.0192   1.0000   0.0417
  -7.250  -0.3439   0.09077   0.08635  -0.0205   1.0000   0.0428
  -7.000  -0.3370   0.08759   0.08322  -0.0224   1.0000   0.0439
  -6.750  -0.3295   0.08440   0.08005  -0.0247   1.0000   0.0452
  -6.500  -0.3212   0.08124   0.07693  -0.0272   1.0000   0.0466
  -6.250  -0.3121   0.07815   0.07388  -0.0299   1.0000   0.0481
  -6.000  -0.3006   0.07537   0.07111  -0.0337   1.0000   0.0499
  -5.750  -0.2829   0.07373   0.06934  -0.0396   1.0000   0.0512
  -5.500  -0.2713   0.07245   0.06786  -0.0417   1.0000   0.0516
  -5.250  -0.2747   0.06713   0.06278  -0.0389   1.0000   0.0525
  -5.000  -0.2789   0.06422   0.06000  -0.0356   1.0000   0.0537
  -4.750  -0.2805   0.06214   0.05799  -0.0333   1.0000   0.0552
  -4.500  -0.2783   0.06016   0.05601  -0.0322   1.0000   0.0571
  -4.250  -0.2563   0.05728   0.05301  -0.0353   0.9976   0.0614
  -4.000  -0.2025   0.05215   0.04758  -0.0446   0.9891   0.0685
  -3.750  -0.1511   0.04796   0.04306  -0.0524   0.9805   0.0817
  -3.500  -0.1066   0.04391   0.03883  -0.0582   0.9723   0.0968
  -3.250  -0.0667   0.04046   0.03525  -0.0627   0.9631   0.1154
  -3.000  -0.0203   0.03717   0.03171  -0.0685   0.9568   0.1541
  -2.750   0.0131   0.03444   0.02900  -0.0711   0.9467   0.2049
  -2.500   0.0453   0.03208   0.02674  -0.0731   0.9384   0.2949
  -2.250   0.0720   0.02914   0.02412  -0.0725   0.9302   0.3845
  -2.000   0.0931   0.02676   0.02202  -0.0696   0.9193   0.4716
  -1.750   0.1856   0.02437   0.01792  -0.0829   0.9102   0.2770
  -1.500   0.2478   0.02317   0.01519  -0.0835   0.9011   0.1210
  -1.250   0.2844   0.02203   0.01355  -0.0828   0.8884   0.0931
  -1.000   0.3165   0.02044   0.01175  -0.0823   0.8753   0.0826
  -0.750   0.3467   0.01966   0.01076  -0.0813   0.8614   0.0805
  -0.500   0.3743   0.01852   0.00962  -0.0804   0.8471   0.0827
  -0.250   0.4005   0.01771   0.00878  -0.0790   0.8324   0.0830
   0.000   0.4259   0.01707   0.00809  -0.0776   0.8172   0.0870
   0.250   0.4516   0.01660   0.00747  -0.0763   0.8017   0.0990
   0.500   0.4783   0.01625   0.00698  -0.0751   0.7856   0.1165
   0.750   0.5120   0.01396   0.00665  -0.0755   0.7684   1.0000
   1.000   0.5373   0.01412   0.00643  -0.0742   0.7500   1.0000
   1.250   0.5626   0.01427   0.00630  -0.0731   0.7319   1.0000
   1.500   0.5878   0.01447   0.00627  -0.0720   0.7129   1.0000
   1.750   0.6130   0.01471   0.00632  -0.0712   0.6928   1.0000
   2.000   0.6387   0.01495   0.00637  -0.0704   0.6746   1.0000
   2.250   0.6644   0.01523   0.00646  -0.0696   0.6566   1.0000
   2.500   0.6900   0.01552   0.00664  -0.0691   0.6380   1.0000
   2.750   0.7160   0.01581   0.00684  -0.0685   0.6214   1.0000
   3.000   0.7421   0.01614   0.00706  -0.0681   0.6065   1.0000
   3.250   0.7683   0.01648   0.00732  -0.0678   0.5928   1.0000
   3.500   0.7946   0.01682   0.00761  -0.0674   0.5799   1.0000
   3.750   0.8208   0.01716   0.00793  -0.0671   0.5676   1.0000
   4.000   0.8469   0.01746   0.00818  -0.0667   0.5552   1.0000
   4.250   0.8727   0.01771   0.00837  -0.0662   0.5419   1.0000
   4.500   0.8983   0.01793   0.00855  -0.0656   0.5278   1.0000
   4.750   0.9238   0.01817   0.00875  -0.0651   0.5141   1.0000
   5.000   0.9495   0.01844   0.00903  -0.0646   0.5017   1.0000
   5.250   0.9751   0.01878   0.00940  -0.0642   0.4898   1.0000
   5.500   1.0003   0.01914   0.00982  -0.0638   0.4778   1.0000
   5.750   1.0255   0.01952   0.01025  -0.0634   0.4659   1.0000
   6.000   1.0507   0.01992   0.01075  -0.0630   0.4545   1.0000
   6.250   1.0758   0.02032   0.01119  -0.0625   0.4429   1.0000
   6.500   1.1008   0.02072   0.01163  -0.0620   0.4306   1.0000
   6.750   1.1256   0.02115   0.01212  -0.0615   0.4182   1.0000
   7.000   1.1495   0.02158   0.01273  -0.0609   0.4048   1.0000
   7.250   1.1732   0.02201   0.01326  -0.0602   0.3902   1.0000
   7.500   1.1956   0.02240   0.01382  -0.0593   0.3732   1.0000
   7.750   1.2168   0.02275   0.01435  -0.0582   0.3530   1.0000
   8.000   1.2372   0.02307   0.01481  -0.0569   0.3300   1.0000
   8.250   1.2550   0.02339   0.01525  -0.0553   0.3004   1.0000
   8.500   1.2708   0.02375   0.01565  -0.0535   0.2657   1.0000
   8.750   1.2858   0.02436   0.01624  -0.0518   0.2309   1.0000
   9.000   1.3006   0.02531   0.01712  -0.0503   0.2052   1.0000
   9.250   1.3150   0.02641   0.01822  -0.0487   0.1866   1.0000
   9.500   1.3270   0.02761   0.01944  -0.0470   0.1672   1.0000
   9.750   1.3379   0.02881   0.02074  -0.0453   0.1442   1.0000
  10.000   1.3476   0.03016   0.02217  -0.0435   0.1117   1.0000
  10.250   1.3436   0.03261   0.02442  -0.0403   0.0815   1.0000
  10.500   1.3360   0.03503   0.02684  -0.0365   0.0618   1.0000
  10.750   1.3326   0.03732   0.02914  -0.0338   0.0505   1.0000
  11.000   1.3271   0.03999   0.03179  -0.0317   0.0452   1.0000
  11.250   1.3220   0.04288   0.03481  -0.0301   0.0425   1.0000
  11.500   1.3173   0.04596   0.03804  -0.0290   0.0402   1.0000
  11.750   1.3124   0.04924   0.04144  -0.0283   0.0386   1.0000
  12.000   1.3070   0.05269   0.04498  -0.0277   0.0372   1.0000
  12.250   1.3027   0.05605   0.04836  -0.0266   0.0360   1.0000
  12.500   1.3049   0.05885   0.05131  -0.0251   0.0351   1.0000
  12.750   1.3082   0.06170   0.05437  -0.0239   0.0340   1.0000
  13.000   1.3089   0.06494   0.05782  -0.0232   0.0327   1.0000
  13.250   1.3080   0.06844   0.06152  -0.0228   0.0315   1.0000
  13.500   1.3058   0.07218   0.06546  -0.0226   0.0306   1.0000
  13.750   1.3025   0.07623   0.06973  -0.0225   0.0302   1.0000
  14.000   1.2963   0.08082   0.07458  -0.0229   0.0301   1.0000
  14.250   1.2863   0.08599   0.08001  -0.0240   0.0301   1.0000
  14.500   1.2728   0.09178   0.08606  -0.0258   0.0302   1.0000
  14.750   1.2566   0.09820   0.09274  -0.0284   0.0304   1.0000
  15.000   1.2383   0.10530   0.10008  -0.0318   0.0306   1.0000
  15.250   1.2166   0.11349   0.10851  -0.0365   0.0310   1.0000
  15.500   1.1930   0.12265   0.11789  -0.0421   0.0315   1.0000
  15.750   1.1674   0.13295   0.12838  -0.0488   0.0321   1.0000
  16.000   1.1394   0.14481   0.14038  -0.0566   0.0330   1.0000
  16.250   1.1143   0.15687   0.15251  -0.0641   0.0345   1.0000
  16.500   1.0977   0.16716   0.16276  -0.0699   0.0354   1.0000
  16.750   1.0507   0.19479   0.19018  -0.0849   0.0434   1.0000
  17.000   1.0535   0.20025   0.19563  -0.0871   0.0442   1.0000
  17.250   1.0585   0.20495   0.20033  -0.0886   0.0449   1.0000
  17.500   0.7739   0.18336   0.17898  -0.0582   0.0536   1.0000
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