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GOE 533 AIRFOIL (goe533-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 533 AIRFOIL (goe533-il)
Reynolds number: 100,000
Max Cl/Cd: 46.53 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe533-il-100000.txt
Download as CSV file: xf-goe533-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 533 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2722   0.09785   0.09339  -0.0372   1.0000   0.1277
  -8.250  -0.3107   0.09856   0.09435  -0.0342   1.0000   0.1287
  -8.000  -0.3459   0.09692   0.09289  -0.0449   0.9863   0.1300
  -7.750  -0.2942   0.09224   0.08815  -0.0361   0.9901   0.1332
  -7.500  -0.2603   0.08820   0.08408  -0.0419   0.9816   0.1411
  -7.250  -0.2495   0.08275   0.07865  -0.0537   0.9628   0.1484
  -7.000  -0.2096   0.07926   0.07511  -0.0561   0.9569   0.1566
  -6.750  -0.1884   0.07347   0.06930  -0.0676   0.9420   0.1661
  -6.500  -0.1675   0.06751   0.06325  -0.0820   0.9266   0.1809
  -6.250  -0.1256   0.06517   0.06093  -0.0793   0.9232   0.1865
  -6.000  -0.1201   0.06055   0.05597  -0.0954   0.9010   0.2137
  -5.750  -0.0869   0.05733   0.05294  -0.0912   0.8942   0.2172
  -5.500  -0.0648   0.05480   0.05036  -0.0927   0.8824   0.2348
  -5.250  -0.0384   0.05241   0.04792  -0.0936   0.8731   0.2534
  -5.000  -0.0147   0.03417   0.02738  -0.1145   0.8578   0.1103
  -4.750   0.0117   0.03114   0.02344  -0.1147   0.8467   0.1003
  -4.500   0.0444   0.02930   0.02126  -0.1153   0.8387   0.0987
  -4.250   0.0691   0.02801   0.01967  -0.1147   0.8271   0.0990
  -4.000   0.0990   0.02640   0.01776  -0.1148   0.8188   0.1000
  -3.750   0.1250   0.02512   0.01630  -0.1143   0.8082   0.1005
  -3.500   0.1528   0.02395   0.01499  -0.1139   0.7990   0.1015
  -3.250   0.1804   0.02298   0.01394  -0.1134   0.7895   0.1033
  -3.000   0.2066   0.02231   0.01321  -0.1128   0.7798   0.1062
  -2.750   0.2350   0.02169   0.01249  -0.1123   0.7711   0.1115
  -2.500   0.2596   0.02109   0.01190  -0.1114   0.7611   0.1164
  -2.250   0.2869   0.02043   0.01129  -0.1107   0.7530   0.1237
  -2.000   0.3102   0.02002   0.01094  -0.1097   0.7427   0.1341
  -1.750   0.3379   0.01932   0.01033  -0.1093   0.7350   0.1654
  -1.500   0.3518   0.01786   0.01067  -0.1067   0.7251   0.5812
  -1.250   0.3748   0.01805   0.01087  -0.1043   0.7177   0.6639
  -1.000   0.3933   0.01831   0.01119  -0.1018   0.7073   0.7112
  -0.750   0.4146   0.01829   0.01115  -0.0991   0.7002   0.7588
  -0.500   0.4282   0.01837   0.01135  -0.0953   0.6900   0.8068
  -0.250   0.4450   0.01814   0.01115  -0.0914   0.6831   0.8596
   0.000   0.4667   0.01811   0.01122  -0.0893   0.6732   0.9118
   0.250   0.5269   0.01795   0.01085  -0.0948   0.6650   0.9690
   0.500   0.5618   0.01824   0.01104  -0.0977   0.6538   1.0000
   0.750   0.5926   0.01842   0.01094  -0.0988   0.6468   1.0000
   1.000   0.6170   0.01888   0.01133  -0.0991   0.6362   1.0000
   1.250   0.6488   0.01910   0.01130  -0.0999   0.6296   1.0000
   1.500   0.6724   0.01961   0.01177  -0.0997   0.6192   1.0000
   1.750   0.7033   0.01982   0.01176  -0.1000   0.6125   1.0000
   2.000   0.7262   0.02035   0.01229  -0.0996   0.6025   1.0000
   2.250   0.7558   0.02060   0.01237  -0.0997   0.5959   1.0000
   2.500   0.7789   0.02119   0.01296  -0.0993   0.5872   1.0000
   2.750   0.8066   0.02150   0.01317  -0.0992   0.5801   1.0000
   3.000   0.8320   0.02197   0.01358  -0.0989   0.5728   1.0000
   3.250   0.8569   0.02238   0.01396  -0.0984   0.5646   1.0000
   3.500   0.8876   0.02254   0.01397  -0.0986   0.5591   1.0000
   3.750   0.9070   0.02325   0.01478  -0.0976   0.5498   1.0000
   4.000   0.9374   0.02331   0.01470  -0.0977   0.5438   1.0000
   4.250   0.9580   0.02389   0.01536  -0.0967   0.5347   1.0000
   4.500   0.9873   0.02392   0.01528  -0.0966   0.5280   1.0000
   4.750   1.0095   0.02447   0.01588  -0.0959   0.5204   1.0000
   5.000   1.0359   0.02465   0.01603  -0.0955   0.5130   1.0000
   5.250   1.0623   0.02488   0.01622  -0.0951   0.5062   1.0000
   5.500   1.0848   0.02529   0.01669  -0.0943   0.4981   1.0000
   5.750   1.1165   0.02529   0.01657  -0.0945   0.4932   1.0000
   6.000   1.1325   0.02622   0.01768  -0.0932   0.4851   1.0000
   6.250   1.1606   0.02641   0.01784  -0.0930   0.4793   1.0000
   6.500   1.1840   0.02694   0.01842  -0.0924   0.4731   1.0000
   6.750   1.2050   0.02752   0.01909  -0.0915   0.4657   1.0000
   7.000   1.2381   0.02744   0.01891  -0.0919   0.4605   1.0000
   7.250   1.2509   0.02847   0.02015  -0.0901   0.4520   1.0000
   7.500   1.2814   0.02847   0.02009  -0.0902   0.4457   1.0000
   7.750   1.2982   0.02930   0.02106  -0.0888   0.4378   1.0000
   8.000   1.3247   0.02951   0.02128  -0.0884   0.4307   1.0000
   8.250   1.3457   0.03014   0.02199  -0.0875   0.4234   1.0000
   8.500   1.3678   0.03055   0.02246  -0.0866   0.4152   1.0000
   8.750   1.3901   0.03099   0.02295  -0.0858   0.4071   1.0000
   9.000   1.4142   0.03110   0.02307  -0.0850   0.3978   1.0000
   9.250   1.4303   0.03172   0.02379  -0.0834   0.3882   1.0000
   9.500   1.4634   0.03145   0.02339  -0.0837   0.3795   1.0000
   9.750   1.4700   0.03248   0.02466  -0.0810   0.3696   1.0000
  10.000   1.5005   0.03248   0.02455  -0.0811   0.3613   1.0000
  10.250   1.5078   0.03336   0.02563  -0.0785   0.3517   1.0000
  10.500   1.5294   0.03375   0.02604  -0.0776   0.3433   1.0000
  10.750   1.5418   0.03447   0.02687  -0.0756   0.3348   1.0000
  11.000   1.5597   0.03510   0.02755  -0.0743   0.3272   1.0000
  11.250   1.5694   0.03585   0.02842  -0.0721   0.3190   1.0000
  11.500   1.5855   0.03644   0.02907  -0.0706   0.3116   1.0000
  11.750   1.5876   0.03747   0.03025  -0.0675   0.3044   1.0000
  12.000   1.6059   0.03778   0.03056  -0.0662   0.2969   1.0000
  12.250   1.5950   0.03915   0.03213  -0.0618   0.2901   1.0000
  12.500   1.6162   0.03927   0.03220  -0.0608   0.2823   1.0000
  12.750   1.5982   0.04132   0.03451  -0.0565   0.2763   1.0000
  13.000   1.6189   0.04129   0.03440  -0.0556   0.2678   1.0000
  13.250   1.5951   0.04408   0.03748  -0.0519   0.2619   1.0000
  13.500   1.6075   0.04442   0.03775  -0.0505   0.2527   1.0000
  13.750   1.5834   0.04783   0.04143  -0.0481   0.2461   1.0000
  14.000   1.5831   0.04931   0.04290  -0.0467   0.2364   1.0000
  14.250   1.5677   0.05245   0.04616  -0.0456   0.2273   1.0000
  14.500   1.5515   0.05606   0.04989  -0.0450   0.2177   1.0000
  14.750   1.5410   0.05920   0.05301  -0.0446   0.2063   1.0000
  15.000   1.5302   0.06256   0.05630  -0.0445   0.1940   1.0000
  15.250   1.5199   0.06614   0.05977  -0.0444   0.1811   1.0000
  15.500   1.4987   0.07153   0.06527  -0.0453   0.1704   1.0000
  15.750   1.4844   0.07626   0.07001  -0.0460   0.1594   1.0000
  16.000   1.4757   0.08038   0.07409  -0.0466   0.1493   1.0000
  16.250   1.4696   0.08422   0.07788  -0.0473   0.1402   1.0000
  16.500   1.4522   0.09021   0.08406  -0.0492   0.1334   1.0000
  16.750   1.4503   0.09361   0.08737  -0.0500   0.1260   1.0000
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