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GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il)
Reynolds number: 200,000
Max Cl/Cd: 76.06 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe187-il-200000-n5.txt
Download as CSV file: xf-goe187-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2934   0.09803   0.09485  -0.0262   1.0000   0.0130
  -7.500  -0.2918   0.09580   0.09268  -0.0273   1.0000   0.0131
  -7.250  -0.2876   0.09332   0.09026  -0.0289   1.0000   0.0131
  -7.000  -0.2801   0.09054   0.08753  -0.0311   0.9983   0.0132
  -6.750  -0.2528   0.08612   0.08309  -0.0384   0.9886   0.0133
  -6.500  -0.2254   0.08171   0.07865  -0.0453   0.9772   0.0133
  -6.250  -0.1979   0.07738   0.07427  -0.0516   0.9644   0.0134
  -6.000  -0.1694   0.07305   0.06986  -0.0576   0.9514   0.0134
  -5.750  -0.1401   0.06877   0.06550  -0.0631   0.9377   0.0134
  -5.500  -0.1109   0.06462   0.06122  -0.0680   0.9218   0.0135
  -5.250  -0.0899   0.05835   0.05488  -0.0722   0.9043   0.0139
  -5.000  -0.0709   0.05369   0.05011  -0.0745   0.8849   0.0144
  -4.750  -0.0525   0.05027   0.04658  -0.0757   0.8628   0.0150
  -4.500  -0.0320   0.04729   0.04345  -0.0770   0.8414   0.0161
  -4.250  -0.0075   0.04437   0.04033  -0.0787   0.8215   0.0175
  -4.000   0.0195   0.04142   0.03717  -0.0805   0.8046   0.0190
  -3.750   0.0481   0.03854   0.03404  -0.0821   0.7904   0.0205
  -3.500   0.0792   0.03603   0.03123  -0.0833   0.7776   0.0229
  -3.250   0.1150   0.03480   0.02954  -0.0837   0.7656   0.0245
  -3.000   0.1438   0.03274   0.02714  -0.0839   0.7544   0.0247
  -2.750   0.1720   0.03060   0.02468  -0.0842   0.7433   0.0247
  -2.250   0.2239   0.02430   0.01797  -0.0853   0.7231   0.0217
  -2.000   0.2556   0.02174   0.01492  -0.0847   0.7136   0.0155
  -1.750   0.2855   0.02006   0.01286  -0.0843   0.7039   0.0151
  -1.500   0.3129   0.01899   0.01158  -0.0844   0.6945   0.0175
  -1.250   0.3423   0.01761   0.00985  -0.0840   0.6847   0.0170
  -1.000   0.3714   0.01638   0.00833  -0.0835   0.6748   0.0166
  -0.750   0.3998   0.01538   0.00708  -0.0831   0.6647   0.0169
  -0.500   0.4277   0.01464   0.00614  -0.0827   0.6542   0.0187
  -0.250   0.4555   0.01401   0.00538  -0.0824   0.6434   0.0215
   0.000   0.4830   0.01339   0.00466  -0.0820   0.6327   0.0231
   0.250   0.5102   0.01289   0.00409  -0.0818   0.6216   0.0274
   0.500   0.5376   0.01258   0.00367  -0.0817   0.6093   0.0320
   0.750   0.5651   0.01237   0.00333  -0.0816   0.5957   0.0411
   1.000   0.5925   0.01225   0.00307  -0.0814   0.5811   0.0522
   1.250   0.6212   0.01013   0.00301  -0.0818   0.5659   1.0000
   1.500   0.6482   0.01027   0.00294  -0.0816   0.5494   1.0000
   1.750   0.6751   0.01042   0.00293  -0.0814   0.5319   1.0000
   2.000   0.7017   0.01060   0.00294  -0.0812   0.5131   1.0000
   2.250   0.7279   0.01082   0.00297  -0.0809   0.4933   1.0000
   2.500   0.7540   0.01106   0.00305  -0.0807   0.4725   1.0000
   2.750   0.7798   0.01133   0.00315  -0.0804   0.4532   1.0000
   3.000   0.8056   0.01162   0.00329  -0.0801   0.4364   1.0000
   3.250   0.8315   0.01190   0.00346  -0.0799   0.4219   1.0000
   3.500   0.8576   0.01216   0.00364  -0.0797   0.4098   1.0000
   3.750   0.8838   0.01241   0.00383  -0.0795   0.3995   1.0000
   4.000   0.9098   0.01268   0.00407  -0.0793   0.3904   1.0000
   4.250   0.9359   0.01292   0.00429  -0.0792   0.3814   1.0000
   4.500   0.9620   0.01318   0.00454  -0.0790   0.3734   1.0000
   4.750   0.9879   0.01343   0.00482  -0.0788   0.3655   1.0000
   5.000   1.0139   0.01369   0.00509  -0.0786   0.3584   1.0000
   5.250   1.0397   0.01395   0.00538  -0.0784   0.3510   1.0000
   5.500   1.0654   0.01422   0.00569  -0.0782   0.3435   1.0000
   5.750   1.0908   0.01449   0.00603  -0.0780   0.3356   1.0000
   6.000   1.1162   0.01477   0.00637  -0.0777   0.3260   1.0000
   6.250   1.1411   0.01508   0.00673  -0.0774   0.3170   1.0000
   6.500   1.1664   0.01535   0.00713  -0.0772   0.3081   1.0000
   6.750   1.1911   0.01566   0.00753  -0.0768   0.2978   1.0000
   7.000   1.2155   0.01599   0.00795  -0.0764   0.2858   1.0000
   7.250   1.2392   0.01636   0.00839  -0.0759   0.2662   1.0000
   7.500   1.2546   0.01746   0.00903  -0.0746   0.1876   1.0000
   7.750   1.2680   0.01891   0.01016  -0.0730   0.1353   1.0000
   8.000   1.2804   0.02041   0.01130  -0.0713   0.0891   1.0000
   8.250   1.2959   0.02151   0.01232  -0.0698   0.0633   1.0000
   8.500   1.3002   0.02362   0.01409  -0.0668   0.0139   1.0000
   8.750   1.3146   0.02467   0.01534  -0.0650   0.0112   1.0000
   9.000   1.3252   0.02598   0.01685  -0.0628   0.0093   1.0000
   9.250   1.3316   0.02751   0.01862  -0.0600   0.0083   1.0000
   9.500   1.3382   0.02875   0.02005  -0.0572   0.0079   1.0000
   9.750   1.3426   0.03023   0.02173  -0.0544   0.0075   1.0000
  10.000   1.3455   0.03192   0.02366  -0.0519   0.0070   1.0000
  10.250   1.3469   0.03384   0.02575  -0.0497   0.0065   1.0000
  10.500   1.3455   0.03616   0.02821  -0.0479   0.0060   1.0000
  10.750   1.3386   0.03920   0.03142  -0.0464   0.0057   1.0000
  11.000   1.3339   0.04230   0.03467  -0.0454   0.0055   1.0000
  11.250   1.3308   0.04542   0.03795  -0.0447   0.0054   1.0000
  11.500   1.3267   0.04878   0.04146  -0.0443   0.0053   1.0000
  11.750   1.3220   0.05232   0.04514  -0.0441   0.0052   1.0000
  12.000   1.3174   0.05593   0.04888  -0.0439   0.0051   1.0000
  12.250   1.3129   0.05956   0.05264  -0.0438   0.0050   1.0000
  12.500   1.3089   0.06315   0.05635  -0.0436   0.0049   1.0000
  12.750   1.3055   0.06671   0.06004  -0.0435   0.0048   1.0000
  13.000   1.3026   0.07020   0.06365  -0.0432   0.0047   1.0000
  13.250   1.3004   0.07368   0.06727  -0.0431   0.0047   1.0000
  13.500   1.2985   0.07720   0.07092  -0.0429   0.0046   1.0000
  13.750   1.2965   0.08081   0.07467  -0.0428   0.0045   1.0000
  14.000   1.2939   0.08465   0.07866  -0.0431   0.0044   1.0000
  14.250   1.2903   0.08874   0.08290  -0.0438   0.0043   1.0000
  14.500   1.2859   0.09303   0.08733  -0.0448   0.0042   1.0000
  14.750   1.2818   0.09727   0.09168  -0.0459   0.0040   1.0000
  15.000   1.2762   0.10189   0.09643  -0.0473   0.0039   1.0000
  15.250   1.2703   0.10657   0.10122  -0.0486   0.0038   1.0000
  15.500   1.2616   0.11206   0.10687  -0.0506   0.0037   1.0000
  15.750   1.2510   0.11841   0.11344  -0.0540   0.0037   1.0000
  16.000   1.2408   0.12483   0.12008  -0.0574   0.0036   1.0000
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