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GOE 522 AIRFOIL (goe522-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 522 AIRFOIL (goe522-il)
Reynolds number: 100,000
Max Cl/Cd: 32.13 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe522-il-100000.txt
Download as CSV file: xf-goe522-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 522 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.5402   0.08483   0.07954  -0.0770   0.9835   0.0885
 -11.500  -0.6231   0.06999   0.06431  -0.0889   0.9780   0.0872
 -11.250  -0.6801   0.06274   0.05675  -0.0928   0.9678   0.0866
 -11.000  -0.7190   0.05887   0.05260  -0.0927   0.9584   0.0863
 -10.750  -0.7374   0.05551   0.04891  -0.0922   0.9495   0.0865
 -10.500  -0.7463   0.05273   0.04582  -0.0910   0.9407   0.0870
 -10.250  -0.7447   0.04986   0.04251  -0.0908   0.9324   0.0881
 -10.000  -0.7237   0.04835   0.04094  -0.0915   0.9255   0.0895
  -9.750  -0.7062   0.04734   0.03996  -0.0910   0.9166   0.0913
  -9.500  -0.6735   0.04568   0.03810  -0.0936   0.9111   0.0941
  -9.250  -0.6723   0.04417   0.03633  -0.0907   0.9000   0.0959
  -9.000  -0.6358   0.04306   0.03529  -0.0928   0.8938   0.0988
  -8.750  -0.6192   0.04210   0.03428  -0.0918   0.8847   0.1019
  -8.500  -0.5949   0.04076   0.03280  -0.0921   0.8765   0.1061
  -8.250  -0.5533   0.03950   0.03143  -0.0950   0.8719   0.1140
  -8.000  -0.5473   0.03901   0.03111  -0.0919   0.8589   0.1186
  -7.750  -0.5097   0.03783   0.02985  -0.0940   0.8533   0.1331
  -7.500  -0.4994   0.03737   0.02941  -0.0916   0.8412   0.1431
  -7.250  -0.4650   0.03658   0.02851  -0.0931   0.8347   0.1580
  -7.000  -0.4418   0.03616   0.02816  -0.0926   0.8253   0.1681
  -6.750  -0.4138   0.03558   0.02754  -0.0927   0.8163   0.1784
  -6.500  -0.3688   0.03478   0.02665  -0.0954   0.8123   0.1906
  -6.250  -0.3586   0.03478   0.02673  -0.0927   0.7984   0.1960
  -6.000  -0.3173   0.03393   0.02572  -0.0946   0.7937   0.2053
  -5.750  -0.2977   0.03382   0.02570  -0.0932   0.7828   0.2110
  -5.500  -0.2640   0.03316   0.02484  -0.0939   0.7757   0.2198
  -5.250  -0.2171   0.03239   0.02421  -0.0964   0.7726   0.2297
  -5.000  -0.2075   0.03242   0.02406  -0.0936   0.7591   0.2364
  -4.750  -0.1661   0.03173   0.02349  -0.0951   0.7548   0.2461
  -4.500  -0.1201   0.03080   0.02251  -0.0974   0.7523   0.2589
  -4.250  -0.1123   0.03114   0.02285  -0.0942   0.7392   0.2666
  -4.000  -0.0711   0.03037   0.02208  -0.0957   0.7350   0.2808
  -3.750  -0.0223   0.02949   0.02120  -0.0984   0.7324   0.2993
  -3.500   0.0328   0.02864   0.02038  -0.1022   0.7304   0.3218
  -3.250   0.0224   0.02934   0.02103  -0.0961   0.7156   0.3313
  -3.000   0.0705   0.02858   0.02025  -0.0988   0.7126   0.3553
  -2.750   0.1277   0.02772   0.01940  -0.1030   0.7103   0.3806
  -2.500   0.1134   0.02855   0.02036  -0.0961   0.6966   0.3873
  -2.250   0.1618   0.02794   0.01974  -0.0988   0.6929   0.4090
  -2.000   0.2184   0.02727   0.01902  -0.1028   0.6900   0.4308
  -1.750   0.2028   0.02826   0.02007  -0.0958   0.6782   0.4375
  -1.500   0.2409   0.02798   0.01973  -0.0971   0.6733   0.4542
  -1.250   0.2944   0.02741   0.01900  -0.1009   0.6700   0.4728
  -1.000   0.3150   0.02756   0.01925  -0.0995   0.6634   0.4825
  -0.750   0.3120   0.02819   0.01987  -0.0945   0.6540   0.4909
  -0.500   0.3623   0.02762   0.01925  -0.0978   0.6505   0.5050
  -0.250   0.4161   0.02708   0.01852  -0.1019   0.6476   0.5212
   0.000   0.3648   0.02898   0.02057  -0.0896   0.6357   0.5224
   0.250   0.4086   0.02855   0.02018  -0.0917   0.6317   0.5370
   0.500   0.4658   0.02787   0.01945  -0.0960   0.6287   0.5554
   0.750   0.4248   0.02969   0.02137  -0.0856   0.6191   0.5596
   1.000   0.4351   0.03026   0.02193  -0.0830   0.6130   0.5724
   1.250   0.4875   0.02954   0.02116  -0.0864   0.6101   0.5923
   1.500   0.5532   0.02864   0.02023  -0.0920   0.6076   0.6121
   1.750   0.4423   0.03337   0.02520  -0.0727   0.5933   0.6075
   2.000   0.4938   0.03226   0.02408  -0.0754   0.5910   0.6284
   2.250   0.5610   0.03067   0.02248  -0.0804   0.5889   0.6562
   2.500   0.5638   0.03151   0.02341  -0.0767   0.5825   0.6751
   2.750   0.5166   0.03455   0.02656  -0.0672   0.5712   0.6868
   3.000   0.6177   0.03088   0.02288  -0.0753   0.5697   0.7347
   3.250   0.7299   0.02818   0.02013  -0.0867   0.5662   0.7925
   3.750   0.7414   0.03000   0.02247  -0.0809   0.5511   0.9257
   4.000   0.8727   0.02859   0.02069  -0.0984   0.5467   1.0000
   4.250   0.8257   0.03057   0.02271  -0.0877   0.5398   1.0000
   4.500   0.8092   0.03211   0.02422  -0.0818   0.5326   1.0000
   4.750   0.8761   0.03118   0.02307  -0.0874   0.5286   1.0000
   5.000   0.9700   0.03019   0.02176  -0.0976   0.5245   1.0000
   5.250   0.8162   0.03586   0.02783  -0.0728   0.5130   1.0000
   5.500   0.8851   0.03427   0.02605  -0.0776   0.5094   1.0000
   5.750   0.9791   0.03245   0.02396  -0.0865   0.5057   1.0000
   6.000   0.6912   0.04968   0.04182  -0.0558   0.4775   1.0000
   6.250   0.7574   0.04639   0.03838  -0.0576   0.4774   1.0000
   6.500   0.8352   0.04281   0.03464  -0.0608   0.4773   1.0000
   6.750   0.8384   0.04431   0.03611  -0.0587   0.4691   1.0000
   7.000   0.9208   0.04094   0.03257  -0.0629   0.4681   1.0000
   7.250   1.0163   0.03779   0.02920  -0.0697   0.4659   1.0000
   7.500   0.8700   0.04764   0.03937  -0.0543   0.4477   1.0000
   7.750   0.9508   0.04397   0.03554  -0.0578   0.4471   1.0000
   8.000   1.0494   0.04019   0.03153  -0.0640   0.4456   1.0000
   8.250   0.9098   0.05041   0.04206  -0.0508   0.4271   1.0000
   8.500   0.9934   0.04623   0.03771  -0.0540   0.4268   1.0000
   8.750   1.0958   0.04190   0.03315  -0.0600   0.4254   1.0000
   9.000   0.9038   0.05736   0.04900  -0.0458   0.4022   1.0000
   9.250   0.9729   0.05346   0.04498  -0.0471   0.4022   1.0000
   9.500   1.0663   0.04845   0.03980  -0.0506   0.4026   1.0000
   9.750   0.9433   0.06090   0.05248  -0.0435   0.3852   1.0000
  10.000   1.0106   0.05699   0.04847  -0.0445   0.3852   1.0000
  10.250   1.0984   0.05208   0.04339  -0.0471   0.3855   1.0000
  10.500   0.5010   0.13489   0.12735  -0.0549   0.4021   1.0000
  10.750   0.4923   0.13712   0.12958  -0.0552   0.3965   1.0000
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