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GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il)
Reynolds number: 500,000
Max Cl/Cd: 100.87 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe187-il-500000.txt
Download as CSV file: xf-goe187-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2789   0.10227   0.10021  -0.0189   1.0000   0.0092
  -9.250  -0.2771   0.09893   0.09688  -0.0203   1.0000   0.0092
  -9.000  -0.2759   0.09550   0.09348  -0.0218   1.0000   0.0093
  -8.750  -0.2733   0.09198   0.08997  -0.0230   1.0000   0.0093
  -8.250  -0.2645   0.08340   0.08143  -0.0224   1.0000   0.0096
  -8.000  -0.2610   0.07998   0.07803  -0.0226   1.0000   0.0098
  -7.750  -0.2586   0.07664   0.07471  -0.0233   1.0000   0.0099
  -7.500  -0.2571   0.07337   0.07147  -0.0239   1.0000   0.0101
  -7.250  -0.2569   0.07024   0.06837  -0.0244   1.0000   0.0104
  -7.000  -0.2604   0.06744   0.06562  -0.0243   1.0000   0.0105
  -6.750  -0.2566   0.06383   0.06204  -0.0268   0.9954   0.0109
  -6.000  -0.2769   0.06664   0.06465  -0.0378   0.9923   0.0111
  -5.750  -0.2423   0.06171   0.05966  -0.0456   0.9817   0.0117
  -5.500  -0.2069   0.05698   0.05483  -0.0527   0.9657   0.0122
  -5.250  -0.1663   0.05255   0.05023  -0.0595   0.9446   0.0128
  -5.000  -0.1325   0.04891   0.04637  -0.0632   0.9188   0.0131
  -4.750  -0.1068   0.04579   0.04301  -0.0645   0.8938   0.0131
  -4.500  -0.0824   0.04281   0.03980  -0.0652   0.8706   0.0132
  -4.250  -0.0576   0.03991   0.03665  -0.0658   0.8487   0.0132
  -4.000  -0.0395   0.03493   0.03145  -0.0669   0.8296   0.0137
  -3.750  -0.0174   0.03250   0.02886  -0.0674   0.8106   0.0142
  -3.500   0.0074   0.03027   0.02642  -0.0677   0.7932   0.0148
  -3.250   0.0340   0.02810   0.02401  -0.0678   0.7776   0.0157
  -3.000   0.0626   0.02609   0.02172  -0.0677   0.7637   0.0172
  -2.750   0.0957   0.02587   0.02110  -0.0665   0.7511   0.0188
  -2.500   0.1214   0.02158   0.01642  -0.0668   0.7408   0.0198
  -2.000   0.1747   0.01894   0.01346  -0.0670   0.7188   0.0242
  -1.750   0.2051   0.01934   0.01359  -0.0662   0.7081   0.0270
  -1.500   0.2338   0.01857   0.01254  -0.0658   0.6979   0.0273
  -1.250   0.2607   0.01517   0.00888  -0.0660   0.6884   0.0298
  -1.000   0.2888   0.01420   0.00780  -0.0659   0.6784   0.0321
  -0.750   0.3174   0.01357   0.00699  -0.0656   0.6686   0.0358
  -0.500   0.3461   0.01244   0.00568  -0.0652   0.6587   0.0342
  -0.250   0.3751   0.01145   0.00450  -0.0646   0.6482   0.0289
   0.000   0.4034   0.01126   0.00422  -0.0643   0.6367   0.0275
   0.250   0.4307   0.01034   0.00325  -0.0640   0.6248   0.0280
   0.500   0.4581   0.00979   0.00266  -0.0639   0.6112   0.0315
   0.750   0.4858   0.00959   0.00239  -0.0638   0.5941   0.0358
   1.000   0.5135   0.00946   0.00214  -0.0636   0.5737   0.0393
   1.250   0.5411   0.00934   0.00189  -0.0635   0.5489   0.0501
   2.000   0.6240   0.00763   0.00192  -0.0641   0.4641   1.0000
   2.250   0.6509   0.00785   0.00199  -0.0640   0.4456   1.0000
   2.500   0.6779   0.00806   0.00208  -0.0639   0.4304   1.0000
   2.750   0.7049   0.00827   0.00219  -0.0638   0.4176   1.0000
   3.000   0.7321   0.00845   0.00230  -0.0638   0.4061   1.0000
   3.250   0.7593   0.00862   0.00241  -0.0637   0.3962   1.0000
   3.500   0.7864   0.00882   0.00255  -0.0637   0.3881   1.0000
   3.750   0.8136   0.00897   0.00269  -0.0636   0.3802   1.0000
   4.000   0.8407   0.00916   0.00284  -0.0636   0.3728   1.0000
   4.250   0.8678   0.00932   0.00298  -0.0635   0.3649   1.0000
   4.500   0.8948   0.00950   0.00314  -0.0635   0.3583   1.0000
   4.750   0.9219   0.00967   0.00333  -0.0635   0.3506   1.0000
   5.000   0.9488   0.00984   0.00350  -0.0634   0.3429   1.0000
   5.250   0.9755   0.01003   0.00368  -0.0634   0.3345   1.0000
   5.500   1.0025   0.01019   0.00386  -0.0633   0.3264   1.0000
   5.750   1.0290   0.01041   0.00409  -0.0632   0.3186   1.0000
   6.000   1.0559   0.01056   0.00429  -0.0632   0.3096   1.0000
   6.250   1.0824   0.01076   0.00451  -0.0631   0.2999   1.0000
   6.500   1.1086   0.01099   0.00473  -0.0630   0.2845   1.0000
   6.750   1.1340   0.01131   0.00499  -0.0628   0.2571   1.0000
   7.000   1.1564   0.01201   0.00541  -0.0623   0.1994   1.0000
   7.250   1.1769   0.01298   0.00610  -0.0616   0.1553   1.0000
   7.500   1.1988   0.01372   0.00669  -0.0610   0.1223   1.0000
   7.750   1.2212   0.01438   0.00724  -0.0604   0.1025   1.0000
   8.000   1.2436   0.01500   0.00783  -0.0599   0.0910   1.0000
   8.250   1.2653   0.01568   0.00847  -0.0592   0.0790   1.0000
   8.500   1.2844   0.01663   0.00916  -0.0583   0.0358   1.0000
   8.750   1.2995   0.01803   0.01048  -0.0566   0.0163   1.0000
   9.000   1.3172   0.01909   0.01171  -0.0551   0.0131   1.0000
   9.250   1.3364   0.01987   0.01263  -0.0541   0.0121   1.0000
   9.500   1.3531   0.02086   0.01375  -0.0526   0.0112   1.0000
   9.750   1.3674   0.02200   0.01502  -0.0509   0.0104   1.0000
  10.000   1.3782   0.02333   0.01647  -0.0488   0.0098   1.0000
  10.250   1.3833   0.02495   0.01823  -0.0459   0.0093   1.0000
  10.500   1.3796   0.02679   0.02021  -0.0418   0.0090   1.0000
  10.750   1.3710   0.02913   0.02270  -0.0379   0.0087   1.0000
  11.250   1.3684   0.03360   0.02744  -0.0335   0.0083   1.0000
  11.500   1.3750   0.03536   0.02934  -0.0326   0.0080   1.0000
  11.750   1.3779   0.03762   0.03172  -0.0317   0.0077   1.0000
  12.000   1.3782   0.04028   0.03451  -0.0309   0.0074   1.0000
  12.250   1.3775   0.04317   0.03752  -0.0303   0.0073   1.0000
  12.500   1.3763   0.04618   0.04067  -0.0298   0.0071   1.0000
  12.750   1.3747   0.04932   0.04393  -0.0294   0.0070   1.0000
  13.000   1.3724   0.05258   0.04732  -0.0291   0.0069   1.0000
  13.250   1.3697   0.05596   0.05083  -0.0290   0.0068   1.0000
  13.500   1.3662   0.05949   0.05450  -0.0289   0.0067   1.0000
  13.750   1.3618   0.06320   0.05835  -0.0290   0.0066   1.0000
  14.000   1.3565   0.06713   0.06241  -0.0293   0.0065   1.0000
  14.250   1.3499   0.07130   0.06673  -0.0298   0.0065   1.0000
  14.500   1.3421   0.07583   0.07142  -0.0306   0.0065   1.0000
  14.750   1.3331   0.08072   0.07647  -0.0318   0.0064   1.0000
  15.000   1.3221   0.08610   0.08204  -0.0334   0.0065   1.0000
  15.250   1.3093   0.09206   0.08819  -0.0355   0.0065   1.0000
  15.500   1.2944   0.09865   0.09499  -0.0381   0.0067   1.0000
  15.750   1.2789   0.10556   0.10209  -0.0412   0.0068   1.0000
  16.000   1.2628   0.11285   0.10956  -0.0447   0.0069   1.0000
  16.250   1.2468   0.12041   0.11729  -0.0486   0.0070   1.0000
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