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GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il)
Reynolds number: 500,000
Max Cl/Cd: 98.79 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe187-il-500000-n5.txt
Download as CSV file: xf-goe187-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3421   0.11764   0.11541  -0.0134   1.0000   0.0052
  -9.500  -0.3355   0.11451   0.11230  -0.0150   1.0000   0.0052
  -9.250  -0.3292   0.11141   0.10921  -0.0166   1.0000   0.0052
  -9.000  -0.2158   0.09222   0.09025  -0.0279   1.0000   0.0055
  -8.750  -0.2122   0.08898   0.08703  -0.0281   0.9997   0.0056
  -8.500  -0.2037   0.08512   0.08317  -0.0303   0.9883   0.0058
  -8.250  -0.1950   0.08118   0.07923  -0.0327   0.9712   0.0059
  -8.000  -0.1852   0.07710   0.07513  -0.0353   0.9456   0.0060
  -7.750  -0.1796   0.07357   0.07153  -0.0366   0.9121   0.0061
  -7.500  -0.1776   0.07055   0.06841  -0.0369   0.8795   0.0061
  -7.250  -0.1753   0.06751   0.06526  -0.0374   0.8507   0.0062
  -7.000  -0.1726   0.06444   0.06211  -0.0382   0.8247   0.0063
  -6.750  -0.1700   0.06132   0.05890  -0.0394   0.8010   0.0064
  -6.500  -0.1645   0.05791   0.05541  -0.0416   0.7817   0.0065
  -6.250  -0.1551   0.05420   0.05163  -0.0447   0.7639   0.0066
  -6.000  -0.1433   0.05034   0.04769  -0.0483   0.7495   0.0068
  -5.750  -0.1290   0.04641   0.04368  -0.0520   0.7362   0.0069
  -5.500  -0.1122   0.04240   0.03958  -0.0559   0.7245   0.0071
  -5.250  -0.0921   0.03837   0.03546  -0.0599   0.7154   0.0075
  -5.000  -0.0676   0.03450   0.03148  -0.0642   0.7074   0.0078
  -4.750  -0.0404   0.03075   0.02758  -0.0682   0.6995   0.0080
  -4.500  -0.0156   0.02726   0.02396  -0.0708   0.6916   0.0081
  -4.250   0.0093   0.02396   0.02049  -0.0728   0.6838   0.0081
  -4.000   0.0343   0.02083   0.01720  -0.0744   0.6769   0.0082
  -3.750   0.0600   0.01789   0.01407  -0.0757   0.6700   0.0082
  -3.500   0.0860   0.01522   0.01121  -0.0766   0.6635   0.0082
  -3.000   0.1346   0.00965   0.00521  -0.0786   0.6494   0.0090
  -2.000   0.2544   0.01873   0.01293  -0.0828   0.6312   0.0076
  -1.750   0.2837   0.01691   0.01081  -0.0827   0.6234   0.0073
  -1.500   0.3132   0.01525   0.00885  -0.0824   0.6148   0.0072
  -1.250   0.3426   0.01372   0.00703  -0.0821   0.6058   0.0073
  -1.000   0.3714   0.01239   0.00542  -0.0817   0.5955   0.0078
  -0.750   0.3994   0.01176   0.00465  -0.0816   0.5837   0.0093
  -0.500   0.4273   0.01115   0.00391  -0.0815   0.5712   0.0100
  -0.250   0.4552   0.01064   0.00329  -0.0813   0.5578   0.0110
   0.000   0.4828   0.01034   0.00287  -0.0812   0.5402   0.0126
   0.250   0.5102   0.01002   0.00239  -0.0811   0.5148   0.0155
   0.500   0.5374   0.00998   0.00217  -0.0810   0.4837   0.0191
   0.750   0.5645   0.01006   0.00207  -0.0809   0.4567   0.0240
   1.000   0.5916   0.01011   0.00196  -0.0809   0.4348   0.0301
   1.250   0.6190   0.01019   0.00192  -0.0809   0.4180   0.0368
   1.500   0.6456   0.00817   0.00206  -0.0814   0.4050   1.0000
   1.750   0.6730   0.00832   0.00208  -0.0813   0.3943   1.0000
   2.000   0.7004   0.00848   0.00213  -0.0813   0.3836   1.0000
   2.250   0.7276   0.00866   0.00220  -0.0813   0.3725   1.0000
   2.750   0.7821   0.00898   0.00236  -0.0812   0.3544   1.0000
   3.000   0.8093   0.00915   0.00246  -0.0812   0.3473   1.0000
   3.250   0.8367   0.00928   0.00258  -0.0812   0.3411   1.0000
   3.500   0.8637   0.00946   0.00270  -0.0812   0.3342   1.0000
   3.750   0.8909   0.00960   0.00282  -0.0812   0.3280   1.0000
   4.000   0.9179   0.00977   0.00297  -0.0812   0.3213   1.0000
   4.250   0.9448   0.00994   0.00313  -0.0812   0.3149   1.0000
   4.500   0.9717   0.01011   0.00328  -0.0811   0.3078   1.0000
   4.750   0.9984   0.01029   0.00347  -0.0811   0.3013   1.0000
   5.000   1.0251   0.01048   0.00366  -0.0810   0.2927   1.0000
   5.250   1.0515   0.01069   0.00385  -0.0810   0.2825   1.0000
   5.500   1.0778   0.01091   0.00408  -0.0809   0.2726   1.0000
   5.750   1.1036   0.01118   0.00432  -0.0807   0.2568   1.0000
   6.000   1.1285   0.01155   0.00460  -0.0805   0.2315   1.0000
   6.250   1.1509   0.01222   0.00504  -0.0800   0.1864   1.0000
   6.500   1.1739   0.01281   0.00555  -0.0795   0.1625   1.0000
   6.750   1.1952   0.01359   0.00615  -0.0788   0.1253   1.0000
   7.000   1.2147   0.01455   0.00685  -0.0779   0.0884   1.0000
   7.250   1.2380   0.01502   0.00733  -0.0774   0.0797   1.0000
   7.500   1.2603   0.01559   0.00788  -0.0768   0.0676   1.0000
   7.750   1.2734   0.01715   0.00913  -0.0749   0.0110   1.0000
   8.000   1.2940   0.01784   0.00991  -0.0740   0.0070   1.0000
   8.250   1.3135   0.01860   0.01078  -0.0728   0.0055   1.0000
   8.500   1.3336   0.01926   0.01155  -0.0718   0.0047   1.0000
   8.750   1.3518   0.02004   0.01242  -0.0706   0.0039   1.0000
   9.000   1.3687   0.02090   0.01341  -0.0692   0.0035   1.0000
   9.250   1.3843   0.02182   0.01444  -0.0676   0.0032   1.0000
   9.500   1.3977   0.02284   0.01561  -0.0658   0.0029   1.0000
   9.750   1.4084   0.02394   0.01682  -0.0635   0.0027   1.0000
  10.000   1.4133   0.02517   0.01816  -0.0604   0.0025   1.0000
  10.250   1.4125   0.02683   0.01995  -0.0569   0.0024   1.0000
  10.500   1.4121   0.02863   0.02189  -0.0539   0.0024   1.0000
  10.750   1.4148   0.03039   0.02379  -0.0518   0.0023   1.0000
  11.000   1.4173   0.03231   0.02584  -0.0500   0.0021   1.0000
  11.250   1.4192   0.03444   0.02811  -0.0487   0.0019   1.0000
  11.500   1.4201   0.03684   0.03064  -0.0476   0.0018   1.0000
  11.750   1.4205   0.03946   0.03339  -0.0469   0.0017   1.0000
  12.000   1.4178   0.04255   0.03661  -0.0464   0.0017   1.0000
  12.250   1.4149   0.04581   0.04000  -0.0462   0.0016   1.0000
  12.500   1.4107   0.04932   0.04363  -0.0461   0.0016   1.0000
  12.750   1.4051   0.05308   0.04752  -0.0462   0.0015   1.0000
  13.000   1.3984   0.05707   0.05163  -0.0465   0.0015   1.0000
  13.250   1.3903   0.06129   0.05598  -0.0469   0.0015   1.0000
  13.500   1.3800   0.06587   0.06068  -0.0474   0.0014   1.0000
  13.750   1.3697   0.07055   0.06548  -0.0479   0.0014   1.0000
  14.000   1.3628   0.07499   0.07007  -0.0486   0.0014   1.0000
  14.250   1.3558   0.07958   0.07481  -0.0496   0.0014   1.0000
  14.500   1.3482   0.08432   0.07970  -0.0506   0.0013   1.0000
  14.750   1.3401   0.08926   0.08479  -0.0517   0.0013   1.0000
  15.000   1.3317   0.09437   0.09006  -0.0531   0.0013   1.0000
  15.250   1.3228   0.09967   0.09552  -0.0546   0.0013   1.0000
  15.500   1.3132   0.10517   0.10122  -0.0563   0.0012   1.0000
  15.750   1.3031   0.11093   0.10714  -0.0583   0.0012   1.0000
  16.000   1.2929   0.11689   0.11326  -0.0606   0.0012   1.0000
  16.250   1.2826   0.12300   0.11952  -0.0631   0.0012   1.0000
  16.500   1.2717   0.12939   0.12606  -0.0660   0.0012   1.0000
  16.750   1.2606   0.13605   0.13287  -0.0692   0.0012   1.0000
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