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GOE 530 AIRFOIL (goe530-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 530 AIRFOIL (goe530-il)
Reynolds number: 50,000
Max Cl/Cd: 32.13 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe530-il-50000-n5.txt
Download as CSV file: xf-goe530-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 530 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2879   0.11108   0.10442  -0.0275   1.0000   0.1396
  -8.500  -0.3013   0.11014   0.10359  -0.0253   1.0000   0.1419
  -8.250  -0.3162   0.10896   0.10246  -0.0322   0.9895   0.1469
  -8.000  -0.2975   0.10424   0.09775  -0.0347   0.9832   0.1494
  -7.750  -0.2703   0.10029   0.09379  -0.0355   0.9779   0.1538
  -7.500  -0.2588   0.09719   0.09068  -0.0393   0.9694   0.1588
  -7.250  -0.2799   0.09590   0.08936  -0.0481   0.9515   0.1644
  -7.000  -0.2648   0.09159   0.08506  -0.0492   0.9438   0.1658
  -6.750  -0.2384   0.08746   0.08094  -0.0501   0.9393   0.1682
  -6.500  -0.2256   0.08456   0.07803  -0.0508   0.9304   0.1713
  -6.000  -0.2194   0.07139   0.06425  -0.0640   0.9077   0.1045
  -5.750  -0.1955   0.06769   0.06040  -0.0667   0.9023   0.1005
  -5.500  -0.1899   0.06509   0.05772  -0.0658   0.8911   0.0988
  -5.250  -0.1668   0.06119   0.05358  -0.0686   0.8851   0.0968
  -5.000  -0.1609   0.05883   0.05104  -0.0672   0.8734   0.0971
  -4.750  -0.1345   0.05550   0.04742  -0.0693   0.8672   0.0978
  -4.500  -0.1272   0.05336   0.04507  -0.0673   0.8553   0.0978
  -4.250  -0.0994   0.05020   0.04156  -0.0687   0.8491   0.0974
  -4.000  -0.0909   0.04834   0.03944  -0.0662   0.8373   0.0973
  -3.750  -0.0625   0.04585   0.03657  -0.0669   0.8312   0.0990
  -3.500  -0.0523   0.04437   0.03479  -0.0643   0.8199   0.1004
  -3.250  -0.0240   0.04219   0.03213  -0.0644   0.8136   0.1018
  -3.000  -0.0098   0.04085   0.03044  -0.0621   0.8032   0.1024
  -2.750   0.0189   0.03928   0.02866  -0.0621   0.7964   0.1047
  -2.500   0.0398   0.03839   0.02769  -0.0610   0.7873   0.1072
  -2.000   0.1005   0.03586   0.02462  -0.0609   0.7732   0.1121
  -1.750   0.1191   0.03521   0.02369  -0.0591   0.7621   0.1151
  -1.500   0.1588   0.03392   0.02223  -0.0605   0.7569   0.1189
  -1.250   0.1766   0.03351   0.02175  -0.0587   0.7450   0.1212
  -1.000   0.2166   0.03252   0.02061  -0.0601   0.7391   0.1269
  -0.750   0.2429   0.03217   0.02003  -0.0595   0.7279   0.1313
  -0.500   0.2923   0.03118   0.01903  -0.0628   0.7213   0.1373
  -0.250   0.3224   0.03087   0.01863  -0.0629   0.7107   0.1443
   0.000   0.3626   0.03013   0.01786  -0.0644   0.7027   0.1517
   0.250   0.3889   0.02989   0.01760  -0.0638   0.6918   0.1608
   0.500   0.4243   0.02927   0.01700  -0.0644   0.6833   0.1732
   0.750   0.4465   0.02913   0.01689  -0.0632   0.6714   0.1863
   1.000   0.4818   0.02839   0.01628  -0.0637   0.6632   0.2184
   1.250   0.4997   0.02798   0.01636  -0.0620   0.6506   0.2958
   1.750   0.6734   0.02596   0.01534  -0.0828   0.6269   1.0000
   2.000   0.6914   0.02625   0.01549  -0.0808   0.6137   1.0000
   2.250   0.7170   0.02623   0.01529  -0.0797   0.6027   1.0000
   2.500   0.7368   0.02644   0.01538  -0.0779   0.5898   1.0000
   2.750   0.7542   0.02677   0.01561  -0.0759   0.5769   1.0000
   3.000   0.7784   0.02683   0.01552  -0.0747   0.5659   1.0000
   3.250   0.7974   0.02712   0.01571  -0.0728   0.5537   1.0000
   3.500   0.8145   0.02750   0.01602  -0.0708   0.5415   1.0000
   3.750   0.8396   0.02757   0.01594  -0.0698   0.5313   1.0000
   4.000   0.8551   0.02804   0.01636  -0.0676   0.5192   1.0000
   4.250   0.8738   0.02842   0.01668  -0.0658   0.5083   1.0000
   4.500   0.8973   0.02861   0.01676  -0.0647   0.4985   1.0000
   4.750   0.9114   0.02921   0.01733  -0.0624   0.4872   1.0000
   5.000   0.9371   0.02936   0.01735  -0.0616   0.4781   1.0000
   5.250   0.9495   0.03007   0.01807  -0.0592   0.4674   1.0000
   5.500   0.9726   0.03039   0.01829  -0.0581   0.4585   1.0000
   5.750   0.9867   0.03106   0.01897  -0.0559   0.4484   1.0000
   6.000   1.0090   0.03148   0.01932  -0.0548   0.4400   1.0000
   6.250   1.0215   0.03227   0.02013  -0.0525   0.4307   1.0000
   6.500   1.0479   0.03261   0.02036  -0.0520   0.4234   1.0000
   6.750   1.0542   0.03367   0.02153  -0.0490   0.4144   1.0000
   7.000   1.0793   0.03406   0.02185  -0.0484   0.4072   1.0000
   7.250   1.0863   0.03515   0.02302  -0.0455   0.3992   1.0000
   7.500   1.1017   0.03593   0.02381  -0.0437   0.3921   1.0000
   7.750   1.1267   0.03645   0.02430  -0.0432   0.3861   1.0000
   8.000   1.1248   0.03797   0.02598  -0.0395   0.3792   1.0000
   8.250   1.1405   0.03882   0.02685  -0.0379   0.3733   1.0000
   8.500   1.1663   0.03935   0.02734  -0.0375   0.3682   1.0000
   8.750   1.1506   0.04130   0.02949  -0.0322   0.3621   1.0000
   9.000   1.1577   0.04248   0.03073  -0.0297   0.3565   1.0000
   9.250   1.1867   0.04288   0.03112  -0.0297   0.3521   1.0000
   9.500   1.1690   0.04529   0.03369  -0.0250   0.3471   1.0000
   9.750   1.1504   0.04813   0.03669  -0.0211   0.3419   1.0000
  10.000   1.1589   0.04960   0.03823  -0.0195   0.3377   1.0000
  10.250   1.1936   0.04955   0.03819  -0.0196   0.3342   1.0000
  10.500   1.0851   0.06008   0.04898  -0.0137   0.3258   1.0000
  10.750   1.0737   0.06386   0.05285  -0.0126   0.3204   1.0000
  11.000   1.1092   0.06282   0.05186  -0.0116   0.3178   1.0000
  11.250   0.9638   0.08464   0.07381  -0.0153   0.3030   1.0000
  11.500   0.9845   0.08488   0.07410  -0.0141   0.3007   1.0000
  12.000   0.9267   0.10073   0.09008  -0.0177   0.2856   1.0000
  12.250   0.9616   0.09854   0.08795  -0.0155   0.2831   1.0000
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