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GOE 501 AIRFOIL (goe501-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 501 AIRFOIL (goe501-il)
Reynolds number: 500,000
Max Cl/Cd: 106.17 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe501-il-500000-n5.txt
Download as CSV file: xf-goe501-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.5399   0.04619   0.04298  -0.1351   0.9624   0.0281
 -12.750  -0.5661   0.03666   0.03322  -0.1474   0.9486   0.0283
 -12.500  -0.5709   0.02939   0.02566  -0.1584   0.9364   0.0287
 -12.250  -0.5539   0.02507   0.02101  -0.1659   0.9289   0.0292
 -12.000  -0.5362   0.02362   0.01949  -0.1672   0.9217   0.0299
 -11.750  -0.5140   0.02256   0.01834  -0.1683   0.9157   0.0304
 -11.500  -0.4908   0.02169   0.01736  -0.1690   0.9102   0.0311
 -11.250  -0.4681   0.02090   0.01647  -0.1693   0.9031   0.0319
 -11.000  -0.4437   0.02004   0.01547  -0.1699   0.8974   0.0327
 -10.750  -0.4203   0.01926   0.01453  -0.1701   0.8904   0.0334
 -10.500  -0.3956   0.01849   0.01360  -0.1705   0.8839   0.0341
 -10.250  -0.3704   0.01784   0.01289  -0.1707   0.8776   0.0348
 -10.000  -0.3444   0.01740   0.01238  -0.1709   0.8705   0.0355
  -9.750  -0.3178   0.01694   0.01183  -0.1711   0.8644   0.0362
  -9.500  -0.2917   0.01647   0.01126  -0.1712   0.8572   0.0371
  -9.250  -0.2651   0.01597   0.01062  -0.1713   0.8506   0.0378
  -9.000  -0.2386   0.01550   0.01002  -0.1714   0.8440   0.0386
  -8.750  -0.2119   0.01507   0.00945  -0.1714   0.8366   0.0393
  -8.500  -0.1856   0.01453   0.00884  -0.1715   0.8289   0.0401
  -8.250  -0.1588   0.01417   0.00839  -0.1715   0.8202   0.0408
  -8.000  -0.1317   0.01385   0.00799  -0.1715   0.8125   0.0415
  -7.750  -0.1045   0.01357   0.00762  -0.1715   0.8054   0.0424
  -7.500  -0.0771   0.01329   0.00723  -0.1715   0.7997   0.0435
  -7.250  -0.0496   0.01299   0.00685  -0.1715   0.7939   0.0444
  -7.000  -0.0221   0.01271   0.00647  -0.1715   0.7881   0.0451
  -6.750   0.0053   0.01236   0.00604  -0.1715   0.7828   0.0461
  -6.500   0.0330   0.01207   0.00573  -0.1715   0.7778   0.0471
  -6.250   0.0609   0.01186   0.00547  -0.1715   0.7728   0.0482
  -6.000   0.0887   0.01169   0.00522  -0.1715   0.7676   0.0494
  -5.750   0.1167   0.01150   0.00498  -0.1715   0.7627   0.0508
  -5.500   0.1447   0.01132   0.00474  -0.1715   0.7581   0.0519
  -5.250   0.1726   0.01111   0.00446  -0.1715   0.7532   0.0530
  -5.000   0.2005   0.01089   0.00420  -0.1715   0.7483   0.0545
  -4.750   0.2285   0.01072   0.00401  -0.1715   0.7433   0.0560
  -4.500   0.2566   0.01059   0.00384  -0.1715   0.7386   0.0576
  -4.250   0.2847   0.01048   0.00368  -0.1714   0.7342   0.0594
  -4.000   0.3129   0.01039   0.00353  -0.1714   0.7301   0.0608
  -3.750   0.3411   0.01017   0.00332  -0.1715   0.7258   0.0629
  -3.500   0.3692   0.01004   0.00317  -0.1715   0.7211   0.0649
  -3.250   0.3972   0.00995   0.00303  -0.1714   0.7163   0.0673
  -3.000   0.4254   0.00987   0.00292  -0.1714   0.7118   0.0695
  -2.750   0.4534   0.00976   0.00279  -0.1713   0.7065   0.0718
  -2.500   0.4811   0.00966   0.00266  -0.1712   0.6998   0.0750
  -2.250   0.5087   0.00958   0.00256  -0.1710   0.6924   0.0787
  -2.000   0.5360   0.00952   0.00246  -0.1708   0.6837   0.0831
  -1.750   0.5635   0.00942   0.00237  -0.1707   0.6757   0.0910
  -1.500   0.5905   0.00927   0.00234  -0.1705   0.6656   0.1284
  -1.250   0.6175   0.00925   0.00232  -0.1702   0.6540   0.1472
  -1.000   0.6441   0.00923   0.00229  -0.1699   0.6410   0.1607
  -0.750   0.6701   0.00925   0.00227  -0.1694   0.6241   0.1700
  -0.500   0.6950   0.00932   0.00227  -0.1687   0.6019   0.1793
  -0.250   0.7187   0.00944   0.00230  -0.1679   0.5773   0.1920
   0.000   0.7422   0.00959   0.00238  -0.1670   0.5551   0.2101
   0.250   0.7661   0.00973   0.00248  -0.1662   0.5378   0.2330
   0.500   0.7908   0.00985   0.00259  -0.1656   0.5248   0.2564
   0.750   0.8155   0.00998   0.00272  -0.1649   0.5138   0.2813
   1.000   0.8406   0.01010   0.00284  -0.1644   0.5031   0.3052
   1.250   0.8658   0.01023   0.00296  -0.1638   0.4944   0.3217
   1.500   0.8911   0.01035   0.00308  -0.1633   0.4860   0.3371
   1.750   0.9161   0.01048   0.00321  -0.1627   0.4783   0.3524
   2.000   0.9413   0.01060   0.00334  -0.1621   0.4700   0.3673
   2.250   0.9659   0.01074   0.00348  -0.1615   0.4630   0.3817
   2.500   0.9914   0.01083   0.00360  -0.1610   0.4562   0.3943
   3.000   1.0407   0.01108   0.00388  -0.1597   0.4442   0.4224
   3.250   1.0655   0.01117   0.00403  -0.1592   0.4378   0.4427
   3.500   1.0891   0.01130   0.00422  -0.1584   0.4311   0.4747
   3.750   1.1134   0.01136   0.00442  -0.1577   0.4253   0.5288
   4.000   1.1371   0.01145   0.00462  -0.1569   0.4190   0.5812
   4.250   1.1594   0.01158   0.00483  -0.1559   0.4123   0.6238
   4.500   1.1823   0.01161   0.00503  -0.1550   0.4054   0.6879
   5.000   1.2252   0.01154   0.00540  -0.1524   0.3929   1.0000
   5.250   1.2458   0.01178   0.00561  -0.1510   0.3838   1.0000
   5.500   1.2651   0.01207   0.00585  -0.1495   0.3719   1.0000
   5.750   1.2834   0.01240   0.00612  -0.1477   0.3594   1.0000
   6.000   1.3019   0.01273   0.00641  -0.1461   0.3478   1.0000
   6.250   1.3204   0.01308   0.00671  -0.1445   0.3343   1.0000
   6.500   1.3350   0.01360   0.00711  -0.1423   0.3131   1.0000
   6.750   1.3482   0.01421   0.00759  -0.1399   0.2868   1.0000
   7.000   1.3553   0.01516   0.00830  -0.1366   0.2445   1.0000
   7.250   1.3574   0.01646   0.00929  -0.1328   0.1953   1.0000
   7.500   1.3708   0.01716   0.00992  -0.1307   0.1832   1.0000
   7.750   1.3863   0.01776   0.01051  -0.1290   0.1765   1.0000
   8.000   1.4024   0.01833   0.01108  -0.1273   0.1720   1.0000
   8.250   1.4180   0.01895   0.01169  -0.1257   0.1679   1.0000
   8.500   1.4331   0.01959   0.01234  -0.1240   0.1641   1.0000
   8.750   1.4502   0.02013   0.01293  -0.1226   0.1614   1.0000
   9.000   1.4663   0.02073   0.01357  -0.1211   0.1586   1.0000
   9.250   1.4815   0.02141   0.01427  -0.1195   0.1557   1.0000
   9.500   1.4956   0.02216   0.01505  -0.1179   0.1527   1.0000
   9.750   1.5091   0.02297   0.01589  -0.1162   0.1498   1.0000
  10.000   1.5240   0.02370   0.01667  -0.1148   0.1470   1.0000
  10.250   1.5401   0.02437   0.01740  -0.1135   0.1432   1.0000
  10.500   1.5533   0.02525   0.01829  -0.1120   0.1375   1.0000
  10.750   1.5654   0.02623   0.01929  -0.1105   0.1316   1.0000
  11.000   1.5771   0.02726   0.02030  -0.1089   0.1205   1.0000
  11.250   1.5822   0.02881   0.02171  -0.1069   0.0960   1.0000
  11.500   1.5839   0.03069   0.02349  -0.1047   0.0817   1.0000
  11.750   1.5882   0.03242   0.02521  -0.1028   0.0747   1.0000
  12.000   1.5961   0.03392   0.02675  -0.1013   0.0707   1.0000
  12.250   1.6025   0.03559   0.02847  -0.0998   0.0672   1.0000
  12.500   1.6075   0.03744   0.03034  -0.0983   0.0636   1.0000
  12.750   1.6155   0.03906   0.03202  -0.0971   0.0612   1.0000
  13.000   1.6215   0.04091   0.03392  -0.0959   0.0585   1.0000
  13.250   1.6263   0.04293   0.03599  -0.0948   0.0562   1.0000
  13.500   1.6311   0.04500   0.03812  -0.0937   0.0540   1.0000
  13.750   1.6381   0.04690   0.04009  -0.0928   0.0522   1.0000
  14.000   1.6435   0.04901   0.04226  -0.0919   0.0503   1.0000
  14.250   1.6473   0.05135   0.04465  -0.0911   0.0481   1.0000
  14.500   1.6495   0.05393   0.04729  -0.0904   0.0461   1.0000
  14.750   1.6549   0.05621   0.04965  -0.0898   0.0443   1.0000
  15.000   1.6585   0.05874   0.05225  -0.0894   0.0420   1.0000
  15.250   1.6598   0.06162   0.05517  -0.0890   0.0395   1.0000
  15.500   1.6628   0.06437   0.05800  -0.0887   0.0372   1.0000
  15.750   1.6636   0.06747   0.06116  -0.0886   0.0341   1.0000
  16.000   1.6637   0.07072   0.06446  -0.0886   0.0308   1.0000
  16.250   1.6621   0.07429   0.06806  -0.0887   0.0270   1.0000
  16.500   1.6586   0.07818   0.07199  -0.0890   0.0232   1.0000
  16.750   1.6548   0.08221   0.07608  -0.0895   0.0206   1.0000
  17.000   1.6511   0.08629   0.08022  -0.0900   0.0187   1.0000
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