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GOE 411 AIRFOIL (goe411-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 411 AIRFOIL (goe411-il)
Reynolds number: 200,000
Max Cl/Cd: 35.59 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe411-il-200000-n5.txt
Download as CSV file: xf-goe411-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 411 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
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.6375   0.09774   0.09384  -0.0370   1.0000   0.0086
 -13.000  -0.6531   0.09115   0.08706  -0.0427   1.0000   0.0091
 -12.750  -0.6727   0.08378   0.07970  -0.0449   1.0000   0.0082
 -12.500  -0.6896   0.07794   0.07372  -0.0485   1.0000   0.0084
 -12.250  -0.7086   0.07220   0.06786  -0.0511   1.0000   0.0082
 -12.000  -0.7205   0.06936   0.06480  -0.0530   1.0000   0.0089
 -11.750  -0.7456   0.06254   0.05791  -0.0538   1.0000   0.0076
 -11.500  -0.7576   0.05975   0.05494  -0.0536   1.0000   0.0082
 -11.250  -0.7753   0.05601   0.05103  -0.0525   1.0000   0.0079
 -11.000  -0.7854   0.05462   0.04944  -0.0504   1.0000   0.0086
 -10.750  -0.7993   0.05186   0.04652  -0.0476   1.0000   0.0085
 -10.500  -0.8138   0.04900   0.04349  -0.0441   1.0000   0.0082
 -10.250  -0.8259   0.05010   0.04439  -0.0384   1.0000   0.0090
  -9.750  -0.8475   0.04569   0.03965  -0.0287   1.0000   0.0089
  -9.500  -0.8547   0.04485   0.03860  -0.0236   1.0000   0.0091
  -9.250  -0.8569   0.04238   0.03592  -0.0196   1.0000   0.0090
  -9.000  -0.8565   0.04001   0.03333  -0.0158   1.0000   0.0089
  -8.750  -0.8537   0.03806   0.03117  -0.0121   1.0000   0.0089
  -8.500  -0.8487   0.03614   0.02902  -0.0086   1.0000   0.0089
  -8.250  -0.8412   0.03438   0.02705  -0.0054   1.0000   0.0090
  -8.000  -0.8313   0.03271   0.02519  -0.0025   1.0000   0.0090
  -7.750  -0.8205   0.03137   0.02367   0.0004   1.0000   0.0091
  -7.500  -0.8074   0.02991   0.02201   0.0029   1.0000   0.0092
  -7.250  -0.7895   0.02766   0.01964   0.0044   1.0000   0.0094
  -7.000  -0.7742   0.02564   0.01758   0.0064   1.0000   0.0097
  -6.750  -0.7638   0.02432   0.01623   0.0093   1.0000   0.0100
  -6.500  -0.7485   0.02316   0.01508   0.0109   0.9988   0.0113
  -6.250  -0.7178   0.02197   0.01383   0.0095   0.9947   0.0125
  -6.000  -0.6893   0.02078   0.01258   0.0087   0.9896   0.0130
  -5.750  -0.6606   0.01968   0.01137   0.0079   0.9844   0.0139
  -5.500  -0.6314   0.01879   0.01034   0.0071   0.9791   0.0149
  -5.250  -0.6027   0.01819   0.00958   0.0066   0.9739   0.0163
  -5.000  -0.5746   0.01731   0.00849   0.0062   0.9694   0.0186
  -4.750  -0.5481   0.01673   0.00775   0.0062   0.9638   0.0212
  -4.500  -0.5174   0.01620   0.00710   0.0055   0.9595   0.0274
  -4.250  -0.5015   0.01479   0.00628   0.0070   0.9522   0.1512
  -4.000  -0.4790   0.01355   0.00573   0.0072   0.9475   0.2735
  -3.750  -0.4598   0.01289   0.00541   0.0085   0.9395   0.3497
  -3.500  -0.4346   0.01227   0.00518   0.0087   0.9346   0.4397
  -3.250  -0.4146   0.01189   0.00502   0.0103   0.9264   0.5015
  -3.000  -0.3806   0.01163   0.00476   0.0089   0.9228   0.5233
  -2.750  -0.3565   0.01145   0.00457   0.0097   0.9140   0.5401
  -2.500  -0.3212   0.01123   0.00434   0.0081   0.9097   0.5580
  -2.250  -0.2959   0.01105   0.00416   0.0086   0.9002   0.5747
  -2.000  -0.2597   0.01082   0.00395   0.0068   0.8951   0.5919
  -1.750  -0.2331   0.01063   0.00381   0.0071   0.8848   0.6081
  -1.500  -0.2015   0.01042   0.00364   0.0063   0.8762   0.6287
  -1.250  -0.1688   0.01016   0.00352   0.0054   0.8674   0.6599
  -1.000  -0.1389   0.00995   0.00348   0.0052   0.8560   0.6969
  -0.750  -0.1059   0.00980   0.00345   0.0043   0.8443   0.7328
  -0.500  -0.0710   0.00971   0.00341   0.0029   0.8315   0.7606
  -0.250  -0.0360   0.00965   0.00337   0.0016   0.8169   0.7820
   0.000   0.0000   0.00963   0.00336   0.0000   0.8004   0.8004
   0.250   0.0360   0.00965   0.00337  -0.0016   0.7821   0.8170
   0.500   0.0710   0.00971   0.00341  -0.0029   0.7608   0.8316
   0.750   0.1059   0.00981   0.00345  -0.0043   0.7326   0.8444
   1.000   0.1391   0.00995   0.00349  -0.0052   0.6978   0.8561
   1.250   0.1688   0.01016   0.00352  -0.0054   0.6597   0.8673
   1.500   0.2014   0.01042   0.00364  -0.0063   0.6285   0.8762
   1.750   0.2332   0.01063   0.00381  -0.0071   0.6082   0.8848
   2.000   0.2596   0.01081   0.00395  -0.0068   0.5919   0.8951
   2.250   0.2959   0.01105   0.00416  -0.0086   0.5746   0.9003
   2.500   0.3211   0.01122   0.00434  -0.0080   0.5585   0.9096
   2.750   0.3565   0.01145   0.00457  -0.0097   0.5400   0.9140
   3.000   0.3807   0.01163   0.00476  -0.0089   0.5235   0.9229
   3.250   0.4145   0.01189   0.00502  -0.0102   0.5006   0.9265
   3.500   0.4340   0.01227   0.00517  -0.0086   0.4379   0.9349
   3.750   0.4595   0.01291   0.00540  -0.0085   0.3468   0.9396
   4.000   0.4782   0.01360   0.00572  -0.0070   0.2666   0.9476
   4.250   0.5014   0.01480   0.00629  -0.0070   0.1480   0.9523
   4.500   0.5174   0.01622   0.00711  -0.0054   0.0267   0.9596
   4.750   0.5482   0.01671   0.00774  -0.0063   0.0214   0.9638
   5.000   0.5748   0.01732   0.00850  -0.0062   0.0186   0.9695
   5.250   0.6030   0.01816   0.00955  -0.0066   0.0160   0.9739
   5.500   0.6315   0.01878   0.01033  -0.0072   0.0148   0.9792
   5.750   0.6606   0.01970   0.01139  -0.0079   0.0137   0.9846
   6.000   0.6895   0.02078   0.01257  -0.0088   0.0129   0.9897
   6.250   0.7179   0.02198   0.01384  -0.0095   0.0124   0.9948
   6.500   0.7488   0.02314   0.01505  -0.0110   0.0111   0.9988
   6.750   0.7652   0.02417   0.01612  -0.0094   0.0105   1.0000
   7.000   0.7741   0.02564   0.01757  -0.0064   0.0097   1.0000
   7.250   0.7882   0.02721   0.01919  -0.0041   0.0095   1.0000
   7.500   0.8059   0.02942   0.02150  -0.0026   0.0093   1.0000
   7.750   0.8205   0.03133   0.02361  -0.0004   0.0091   1.0000
   8.000   0.8317   0.03280   0.02527   0.0024   0.0090   1.0000
   8.250   0.8414   0.03438   0.02704   0.0053   0.0090   1.0000
   8.500   0.8488   0.03606   0.02893   0.0086   0.0089   1.0000
   8.750   0.8539   0.03803   0.03113   0.0121   0.0089   1.0000
   9.000   0.8573   0.04000   0.03330   0.0156   0.0090   1.0000
   9.250   0.8568   0.04221   0.03575   0.0197   0.0090   1.0000
   9.500   0.8549   0.04502   0.03877   0.0236   0.0091   1.0000
   9.750   0.8479   0.04578   0.03974   0.0286   0.0089   1.0000
  10.250   0.8242   0.04850   0.04280   0.0394   0.0087   1.0000
  10.500   0.8115   0.05033   0.04480   0.0438   0.0087   1.0000
  10.750   0.8014   0.05127   0.04593   0.0476   0.0082   1.0000
  11.000   0.7901   0.05312   0.04798   0.0505   0.0078   1.0000
  11.250   0.7710   0.05736   0.05236   0.0524   0.0085   1.0000
  11.500   0.7582   0.05977   0.05496   0.0535   0.0082   1.0000
  11.750   0.7433   0.06311   0.05847   0.0537   0.0080   1.0000
  13.500   0.5371   0.09166   0.08796   0.0436   0.0097   1.0000
  13.750   0.5137   0.09910   0.09553   0.0393   0.0099   1.0000
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