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GOE 501 AIRFOIL (goe501-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 501 AIRFOIL (goe501-il)
Reynolds number: 200,000
Max Cl/Cd: 85.45 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe501-il-200000.txt
Download as CSV file: xf-goe501-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 501 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2027   0.11710   0.11348  -0.0619   0.9826   0.0660
 -10.250  -0.2026   0.11381   0.11020  -0.0685   0.9763   0.0704
 -10.000  -0.2003   0.10828   0.10468  -0.0760   0.9723   0.0716
  -9.750  -0.1710   0.10489   0.10126  -0.0758   0.9711   0.0728
  -9.500  -0.1460   0.10180   0.09814  -0.0782   0.9697   0.0746
  -9.250  -0.1350   0.09922   0.09557  -0.0797   0.9631   0.0776
  -9.000  -0.1464   0.09361   0.08998  -0.0958   0.9560   0.0823
  -8.750  -0.1141   0.09017   0.08650  -0.0928   0.9560   0.0838
  -8.500  -0.0983   0.08820   0.08452  -0.0921   0.9498   0.0852
  -8.250  -0.0780   0.08545   0.08175  -0.0946   0.9458   0.0883
  -7.750  -0.0661   0.07790   0.07422  -0.1042   0.9323   0.0963
  -7.500  -0.0362   0.07551   0.07179  -0.1059   0.9299   0.0991
  -7.000  -0.0891   0.04529   0.04114  -0.1448   0.8996   0.0834
  -6.750  -0.0638   0.03758   0.03299  -0.1533   0.8958   0.0794
  -6.500  -0.0305   0.03035   0.02491  -0.1617   0.8935   0.0782
  -6.250  -0.0191   0.02844   0.02265  -0.1605   0.8844   0.0792
  -6.000   0.0160   0.02630   0.02002  -0.1630   0.8814   0.0811
  -5.750   0.0537   0.02439   0.01767  -0.1655   0.8792   0.0825
  -5.500   0.0897   0.02231   0.01544  -0.1676   0.8776   0.0848
  -5.250   0.1053   0.02191   0.01500  -0.1657   0.8699   0.0869
  -5.000   0.1368   0.02106   0.01402  -0.1664   0.8665   0.0898
  -4.750   0.1718   0.02010   0.01287  -0.1676   0.8641   0.0924
  -4.500   0.2078   0.01908   0.01168  -0.1690   0.8621   0.0953
  -4.250   0.2297   0.01860   0.01125  -0.1681   0.8562   0.0986
  -4.000   0.2577   0.01815   0.01077  -0.1680   0.8514   0.1025
  -3.750   0.2918   0.01752   0.01003  -0.1688   0.8484   0.1065
  -3.500   0.3271   0.01680   0.00937  -0.1700   0.8459   0.1125
  -3.250   0.3504   0.01667   0.00921  -0.1691   0.8397   0.1184
  -3.000   0.3794   0.01624   0.00883  -0.1691   0.8347   0.1254
  -2.750   0.4137   0.01577   0.00834  -0.1699   0.8312   0.1373
  -2.500   0.4490   0.01523   0.00785  -0.1710   0.8282   0.1578
  -2.250   0.4697   0.01506   0.00782  -0.1697   0.8201   0.1887
  -2.000   0.5021   0.01470   0.00754  -0.1703   0.8155   0.2264
  -1.750   0.5371   0.01441   0.00724  -0.1713   0.8118   0.2545
  -1.500   0.5589   0.01446   0.00735  -0.1700   0.8033   0.2735
  -1.250   0.5912   0.01426   0.00715  -0.1705   0.7982   0.2966
  -1.000   0.6193   0.01420   0.00709  -0.1702   0.7914   0.3197
  -0.750   0.6471   0.01408   0.00699  -0.1699   0.7839   0.3413
  -0.500   0.6804   0.01388   0.00678  -0.1705   0.7784   0.3649
  -0.250   0.7037   0.01387   0.00681  -0.1694   0.7685   0.3876
   0.000   0.7353   0.01364   0.00658  -0.1697   0.7610   0.4127
   0.250   0.7601   0.01352   0.00651  -0.1687   0.7499   0.4345
   0.500   0.7872   0.01339   0.00640  -0.1682   0.7398   0.4587
   0.750   0.8158   0.01322   0.00626  -0.1680   0.7301   0.4832
   1.000   0.8402   0.01316   0.00628  -0.1671   0.7184   0.5072
   1.250   0.8674   0.01306   0.00622  -0.1666   0.7078   0.5344
   1.500   0.8939   0.01296   0.00616  -0.1660   0.6963   0.5673
   1.750   0.9174   0.01288   0.00620  -0.1649   0.6832   0.6076
   2.000   0.9409   0.01272   0.00620  -0.1638   0.6704   0.6679
   2.250   0.9653   0.01210   0.00605  -0.1625   0.6579   1.0000
   2.500   0.9921   0.01220   0.00598  -0.1621   0.6451   1.0000
   2.750   1.0167   0.01233   0.00603  -0.1613   0.6309   1.0000
   3.000   1.0415   0.01249   0.00610  -0.1607   0.6176   1.0000
   3.250   1.0667   0.01268   0.00618  -0.1600   0.6055   1.0000
   3.500   1.0925   0.01288   0.00626  -0.1595   0.5945   1.0000
   3.750   1.1175   0.01312   0.00641  -0.1589   0.5833   1.0000
   4.000   1.1421   0.01338   0.00660  -0.1583   0.5727   1.0000
   4.250   1.1681   0.01367   0.00677  -0.1578   0.5632   1.0000
   4.500   1.1921   0.01397   0.00703  -0.1571   0.5531   1.0000
   4.750   1.2176   0.01430   0.00728  -0.1566   0.5445   1.0000
   5.000   1.2422   0.01462   0.00758  -0.1561   0.5363   1.0000
   5.250   1.2687   0.01499   0.00787  -0.1558   0.5293   1.0000
   5.500   1.2920   0.01531   0.00822  -0.1550   0.5214   1.0000
   6.000   1.3415   0.01602   0.00892  -0.1540   0.5073   1.0000
   6.250   1.3662   0.01638   0.00924  -0.1534   0.4999   1.0000
   6.500   1.3880   0.01672   0.00962  -0.1523   0.4916   1.0000
   6.750   1.4103   0.01705   0.00994  -0.1513   0.4827   1.0000
   7.000   1.4292   0.01736   0.01030  -0.1497   0.4732   1.0000
   7.250   1.4509   0.01770   0.01059  -0.1486   0.4641   1.0000
   7.500   1.4678   0.01799   0.01101  -0.1467   0.4554   1.0000
   7.750   1.4887   0.01834   0.01132  -0.1454   0.4472   1.0000
   8.000   1.5031   0.01864   0.01175  -0.1431   0.4377   1.0000
   8.250   1.5190   0.01898   0.01208  -0.1410   0.4282   1.0000
   8.500   1.5296   0.01930   0.01250  -0.1379   0.4180   1.0000
   8.750   1.5411   0.01970   0.01294  -0.1350   0.4076   1.0000
   9.000   1.5517   0.02015   0.01338  -0.1321   0.3966   1.0000
   9.250   1.5599   0.02064   0.01396  -0.1290   0.3836   1.0000
   9.500   1.5669   0.02125   0.01461  -0.1257   0.3688   1.0000
   9.750   1.5723   0.02199   0.01536  -0.1224   0.3516   1.0000
  10.000   1.5760   0.02290   0.01624  -0.1190   0.3327   1.0000
  10.250   1.5789   0.02397   0.01729  -0.1157   0.3094   1.0000
  10.500   1.5779   0.02537   0.01858  -0.1122   0.2854   1.0000
  10.750   1.5778   0.02690   0.02002  -0.1090   0.2620   1.0000
  11.000   1.5771   0.02861   0.02164  -0.1060   0.2435   1.0000
  11.250   1.5778   0.03035   0.02332  -0.1034   0.2290   1.0000
  11.500   1.5793   0.03214   0.02508  -0.1010   0.2171   1.0000
  11.750   1.5803   0.03405   0.02695  -0.0988   0.2067   1.0000
  12.000   1.5802   0.03613   0.02898  -0.0966   0.1968   1.0000
  12.250   1.5825   0.03810   0.03098  -0.0948   0.1870   1.0000
  12.500   1.5815   0.04042   0.03328  -0.0929   0.1777   1.0000
  12.750   1.5815   0.04275   0.03563  -0.0912   0.1678   1.0000
  13.000   1.5828   0.04505   0.03800  -0.0898   0.1578   1.0000
  13.250   1.5801   0.04780   0.04071  -0.0884   0.1485   1.0000
  13.500   1.5819   0.05024   0.04328  -0.0874   0.1376   1.0000
  13.750   1.5834   0.05281   0.04593  -0.0865   0.1267   1.0000
  14.000   1.5834   0.05561   0.04878  -0.0857   0.1169   1.0000
  14.500   1.5814   0.06174   0.05495  -0.0847   0.1009   1.0000
  14.750   1.5775   0.06530   0.05850  -0.0843   0.0954   1.0000
  15.000   1.5757   0.06867   0.06193  -0.0840   0.0903   1.0000
  15.250   1.5692   0.07272   0.06595  -0.0840   0.0861   1.0000
  15.500   1.5684   0.07611   0.06944  -0.0839   0.0820   1.0000
  15.750   1.5652   0.07988   0.07327  -0.0841   0.0781   1.0000
  16.000   1.5602   0.08382   0.07717  -0.0842   0.0743   1.0000
  16.250   1.5599   0.08737   0.08089  -0.0845   0.0704   1.0000
  16.500   1.5566   0.09125   0.08480  -0.0850   0.0667   1.0000
  16.750   1.5545   0.09497   0.08857  -0.0854   0.0627   1.0000
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