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GOE 501 AIRFOIL (goe501-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 501 AIRFOIL (goe501-il)
Reynolds number: 100,000
Max Cl/Cd: 56.48 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe501-il-100000.txt
Download as CSV file: xf-goe501-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.2665   0.10308   0.09858  -0.0439   0.9611   0.1467
  -6.750  -0.3119   0.10392   0.09951  -0.0554   0.9481   0.1509
  -6.500  -0.2849   0.09872   0.09431  -0.0491   0.9458   0.1526
  -6.250  -0.2518   0.09539   0.09093  -0.0484   0.9425   0.1572
  -6.000  -0.2510   0.09348   0.08903  -0.0496   0.9348   0.1634
  -5.750  -0.2468   0.08930   0.08485  -0.0592   0.9267   0.1691
  -5.500  -0.2314   0.08692   0.08246  -0.0563   0.9213   0.1716
  -5.250  -0.2117   0.08233   0.07774  -0.0748   0.9111   0.1845
  -5.000  -0.1999   0.07953   0.07499  -0.0696   0.9058   0.1859
  -4.750  -0.1446   0.05646   0.05096  -0.1068   0.8996   0.1351
  -4.500  -0.1163   0.05538   0.05007  -0.1060   0.8947   0.1376
  -4.250  -0.0449   0.04260   0.03612  -0.1254   0.8932   0.1250
  -4.000  -0.0164   0.03926   0.03220  -0.1283   0.8852   0.1250
  -3.750   0.0265   0.03741   0.02998  -0.1319   0.8801   0.1291
  -3.500   0.0742   0.03545   0.02741  -0.1361   0.8758   0.1337
  -3.250   0.0995   0.03430   0.02599  -0.1362   0.8666   0.1367
  -3.000   0.1445   0.03342   0.02508  -0.1392   0.8622   0.1440
  -2.750   0.1693   0.03288   0.02425  -0.1388   0.8525   0.1498
  -2.500   0.2118   0.03185   0.02322  -0.1412   0.8474   0.1579
  -2.250   0.2413   0.03141   0.02260  -0.1415   0.8387   0.1683
  -2.000   0.2800   0.03063   0.02186  -0.1431   0.8323   0.1822
  -1.750   0.3285   0.02962   0.02100  -0.1461   0.8290   0.2078
  -1.500   0.3490   0.02946   0.02095  -0.1449   0.8171   0.2382
  -1.250   0.3958   0.02888   0.02052  -0.1474   0.8133   0.2906
  -1.000   0.4169   0.02907   0.02074  -0.1461   0.8015   0.3174
  -0.750   0.4633   0.02843   0.02015  -0.1484   0.7977   0.3504
  -0.500   0.4864   0.02852   0.02024  -0.1474   0.7865   0.3758
  -0.250   0.5315   0.02776   0.01952  -0.1495   0.7825   0.4093
   0.000   0.5816   0.02676   0.01868  -0.1523   0.7803   0.4488
   0.250   0.6008   0.02682   0.01879  -0.1506   0.7680   0.4775
   0.500   0.6477   0.02588   0.01795  -0.1528   0.7648   0.5153
   0.750   0.6959   0.02489   0.01704  -0.1552   0.7624   0.5531
   1.000   0.7140   0.02506   0.01726  -0.1534   0.7494   0.5831
   1.250   0.7615   0.02402   0.01631  -0.1556   0.7463   0.6292
   1.500   0.7796   0.02409   0.01653  -0.1537   0.7338   0.6718
   1.750   0.8197   0.02271   0.01556  -0.1544   0.7300   0.7872
   2.000   0.8447   0.02274   0.01561  -0.1539   0.7178   1.0000
   2.250   0.8932   0.02202   0.01466  -0.1567   0.7129   1.0000
   2.500   0.9134   0.02238   0.01493  -0.1553   0.7006   1.0000
   2.750   0.9593   0.02172   0.01409  -0.1576   0.6954   1.0000
   3.000   0.9761   0.02225   0.01459  -0.1557   0.6832   1.0000
   3.250   1.0137   0.02195   0.01417  -0.1568   0.6763   1.0000
   3.500   1.0364   0.02218   0.01436  -0.1557   0.6655   1.0000
   3.750   1.0633   0.02229   0.01443  -0.1553   0.6564   1.0000
   4.000   1.0937   0.02227   0.01435  -0.1553   0.6482   1.0000
   4.250   1.1174   0.02264   0.01471  -0.1546   0.6399   1.0000
   4.500   1.1461   0.02277   0.01482  -0.1545   0.6323   1.0000
   4.750   1.1717   0.02305   0.01509  -0.1540   0.6247   1.0000
   5.000   1.1981   0.02325   0.01528  -0.1536   0.6166   1.0000
   5.250   1.2254   0.02346   0.01549  -0.1533   0.6091   1.0000
   5.500   1.2498   0.02376   0.01580  -0.1527   0.6010   1.0000
   5.750   1.2796   0.02391   0.01593  -0.1527   0.5941   1.0000
   6.000   1.3012   0.02432   0.01640  -0.1516   0.5855   1.0000
   6.250   1.3328   0.02442   0.01647  -0.1520   0.5785   1.0000
   6.500   1.3529   0.02487   0.01697  -0.1506   0.5692   1.0000
   6.750   1.3819   0.02505   0.01716  -0.1506   0.5611   1.0000
   7.000   1.4046   0.02543   0.01758  -0.1496   0.5520   1.0000
   7.250   1.4299   0.02581   0.01799  -0.1491   0.5436   1.0000
   7.500   1.4539   0.02622   0.01846  -0.1483   0.5351   1.0000
   7.750   1.4762   0.02670   0.01900  -0.1473   0.5259   1.0000
   8.000   1.5091   0.02672   0.01895  -0.1477   0.5151   1.0000
   8.250   1.5196   0.02736   0.01973  -0.1448   0.5033   1.0000
   8.500   1.5400   0.02768   0.02009  -0.1433   0.4911   1.0000
   8.750   1.5644   0.02783   0.02022  -0.1424   0.4782   1.0000
   9.000   1.5819   0.02808   0.02049  -0.1404   0.4647   1.0000
   9.250   1.5887   0.02860   0.02115  -0.1369   0.4513   1.0000
   9.500   1.5980   0.02904   0.02168  -0.1337   0.4378   1.0000
   9.750   1.6055   0.02940   0.02210  -0.1302   0.4234   1.0000
  10.000   1.6088   0.02982   0.02255  -0.1260   0.4085   1.0000
  10.250   1.6090   0.03040   0.02316  -0.1216   0.3929   1.0000
  10.500   1.6067   0.03119   0.02399  -0.1172   0.3762   1.0000
  10.750   1.6035   0.03219   0.02503  -0.1129   0.3586   1.0000
  11.000   1.6008   0.03337   0.02624  -0.1090   0.3405   1.0000
  11.250   1.5987   0.03473   0.02757  -0.1055   0.3226   1.0000
  11.500   1.5973   0.03623   0.02904  -0.1023   0.3055   1.0000
  11.750   1.5963   0.03789   0.03066  -0.0995   0.2894   1.0000
  12.000   1.5953   0.03971   0.03245  -0.0968   0.2743   1.0000
  12.250   1.5939   0.04169   0.03440  -0.0943   0.2597   1.0000
  12.500   1.5919   0.04385   0.03652  -0.0920   0.2454   1.0000
  12.750   1.5894   0.04618   0.03880  -0.0899   0.2311   1.0000
  13.000   1.5866   0.04866   0.04122  -0.0879   0.2166   1.0000
  13.250   1.5849   0.05125   0.04369  -0.0860   0.2016   1.0000
  13.500   1.5852   0.05384   0.04615  -0.0844   0.1864   1.0000
  13.750   1.5871   0.05644   0.04864  -0.0829   0.1722   1.0000
  14.000   1.5904   0.05898   0.05111  -0.0817   0.1600   1.0000
  14.250   1.5977   0.06116   0.05314  -0.0806   0.1489   1.0000
  14.500   1.5875   0.06468   0.05696  -0.0795   0.1418   1.0000
  14.750   1.5923   0.06699   0.05918  -0.0787   0.1339   1.0000
  15.000   1.5836   0.07066   0.06314  -0.0780   0.1278   1.0000
  15.250   1.5850   0.07324   0.06567  -0.0774   0.1216   1.0000
  15.500   1.5773   0.07712   0.06982  -0.0772   0.1160   1.0000
  15.750   1.5746   0.08035   0.07309  -0.0771   0.1106   1.0000
  16.000   1.5709   0.08397   0.07683  -0.0771   0.1052   1.0000
  16.250   1.5666   0.08766   0.08062  -0.0774   0.0999   1.0000
  16.500   1.5661   0.09095   0.08392  -0.0775   0.0946   1.0000
  16.750   1.5622   0.09486   0.08795  -0.0779   0.0895   1.0000
  17.000   1.5674   0.09748   0.09049  -0.0777   0.0839   1.0000
  17.250   1.5612   0.10192   0.09514  -0.0785   0.0797   1.0000
  17.500   1.5767   0.10325   0.09628  -0.0776   0.0740   1.0000
  17.750   1.5649   0.10860   0.10197  -0.0789   0.0717   1.0000
  18.000   1.5585   0.11319   0.10677  -0.0802   0.0690   1.0000
  18.250   1.5817   0.11357   0.10692  -0.0788   0.0643   1.0000
  18.500   1.5632   0.11991   0.11363  -0.0813   0.0634   1.0000
  18.750   1.5454   0.12646   0.12050  -0.0842   0.0624   1.0000
  19.000   1.5270   0.13335   0.12769  -0.0876   0.0615   1.0000
  19.250   1.5058   0.14100   0.13563  -0.0918   0.0609   1.0000
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