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GOE 499 AIRFOIL (goe499-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 499 AIRFOIL (goe499-il)
Reynolds number: 200,000
Max Cl/Cd: 99.07 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe499-il-200000-n5.txt
Download as CSV file: xf-goe499-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 499 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2095   0.09106   0.08749  -0.0669   0.9700   0.0187
  -8.000  -0.1948   0.08714   0.08357  -0.0714   0.9667   0.0198
  -7.750  -0.1859   0.08321   0.07966  -0.0754   0.9604   0.0209
  -7.500  -0.1740   0.07893   0.07537  -0.0802   0.9551   0.0213
  -7.250  -0.1587   0.07404   0.07048  -0.0864   0.9495   0.0219
  -7.000  -0.1434   0.06882   0.06527  -0.0931   0.9432   0.0228
  -6.750  -0.1226   0.06714   0.06355  -0.0952   0.9408   0.0243
  -6.500  -0.0975   0.06498   0.06133  -0.0992   0.9388   0.0272
  -6.250  -0.0828   0.06117   0.05750  -0.1038   0.9310   0.0282
  -6.000  -0.0533   0.05577   0.05203  -0.1134   0.9269   0.0297
  -5.750  -0.0183   0.04884   0.04500  -0.1260   0.9215   0.0323
  -5.500   0.0336   0.03665   0.03246  -0.1463   0.9160   0.0332
  -5.250   0.0828   0.02770   0.02285  -0.1611   0.9135   0.0362
  -5.000   0.1224   0.02381   0.01838  -0.1670   0.9118   0.0371
  -4.750   0.1539   0.02159   0.01573  -0.1694   0.9085   0.0379
  -4.500   0.1831   0.02000   0.01376  -0.1707   0.9049   0.0383
  -4.250   0.2137   0.01892   0.01240  -0.1719   0.9020   0.0397
  -4.000   0.2460   0.01785   0.01105  -0.1732   0.8994   0.0407
  -3.750   0.2798   0.01669   0.00959  -0.1746   0.8970   0.0403
  -3.500   0.3055   0.01595   0.00865  -0.1744   0.8912   0.0400
  -3.250   0.3356   0.01520   0.00773  -0.1748   0.8869   0.0398
  -3.000   0.3674   0.01451   0.00691  -0.1756   0.8838   0.0397
  -2.750   0.3942   0.01405   0.00635  -0.1754   0.8786   0.0397
  -2.500   0.4228   0.01362   0.00584  -0.1756   0.8740   0.0399
  -2.250   0.4535   0.01319   0.00533  -0.1761   0.8705   0.0402
  -2.000   0.4809   0.01291   0.00499  -0.1760   0.8653   0.0408
  -1.750   0.5092   0.01265   0.00465  -0.1760   0.8602   0.0418
  -1.500   0.5397   0.01236   0.00427  -0.1764   0.8561   0.0432
  -1.250   0.5659   0.01221   0.00407  -0.1760   0.8496   0.0453
  -1.000   0.5948   0.01200   0.00382  -0.1761   0.8448   0.0501
  -0.750   0.6244   0.01168   0.00366  -0.1764   0.8411   0.0832
  -0.500   0.6505   0.01153   0.00369  -0.1762   0.8353   0.1393
  -0.250   0.6788   0.01137   0.00373  -0.1763   0.8308   0.2022
   0.000   0.7071   0.01126   0.00374  -0.1764   0.8264   0.2466
   0.250   0.7332   0.01123   0.00380  -0.1761   0.8202   0.2760
   0.500   0.7617   0.01110   0.00379  -0.1761   0.8152   0.3132
   0.750   0.7878   0.01090   0.00395  -0.1759   0.8085   0.4129
   1.000   0.8148   0.01073   0.00404  -0.1756   0.8022   0.5211
   1.250   0.8410   0.01060   0.00413  -0.1752   0.7956   0.6014
   1.500   0.8646   0.00995   0.00406  -0.1739   0.7877   1.0000
   1.750   0.8910   0.01001   0.00410  -0.1734   0.7777   1.0000
   2.000   0.9179   0.01005   0.00414  -0.1730   0.7672   1.0000
   2.250   0.9448   0.01010   0.00416  -0.1726   0.7558   1.0000
   2.500   0.9710   0.01017   0.00424  -0.1721   0.7433   1.0000
   2.750   0.9968   0.01024   0.00432  -0.1715   0.7272   1.0000
   3.000   1.0204   0.01030   0.00423  -0.1701   0.6797   1.0000
   3.250   1.0400   0.01073   0.00416  -0.1679   0.5958   1.0000
   3.500   1.0587   0.01134   0.00443  -0.1659   0.5417   1.0000
   3.750   1.0724   0.01231   0.00492  -0.1632   0.4687   1.0000
   4.000   1.0884   0.01316   0.00544  -0.1610   0.4054   1.0000
   4.250   1.0929   0.01503   0.00630  -0.1573   0.2298   1.0000
   4.500   1.0947   0.01763   0.00779  -0.1534   0.0325   1.0000
   4.750   1.1145   0.01837   0.00854  -0.1519   0.0231   1.0000
   5.000   1.1342   0.01912   0.00942  -0.1504   0.0201   1.0000
   5.250   1.1542   0.01979   0.01022  -0.1489   0.0186   1.0000
   5.500   1.1731   0.02053   0.01111  -0.1473   0.0165   1.0000
   5.750   1.1899   0.02144   0.01214  -0.1454   0.0155   1.0000
   6.000   1.2045   0.02250   0.01330  -0.1431   0.0146   1.0000
   6.250   1.2167   0.02365   0.01455  -0.1404   0.0140   1.0000
   6.500   1.2274   0.02492   0.01588  -0.1376   0.0133   1.0000
   6.750   1.2367   0.02650   0.01751  -0.1347   0.0122   1.0000
   7.000   1.2485   0.02915   0.02024  -0.1323   0.0111   1.0000
   7.250   1.2689   0.03053   0.02172  -0.1310   0.0108   1.0000
   7.500   1.2926   0.03219   0.02349  -0.1303   0.0105   1.0000
   7.750   1.3199   0.03418   0.02562  -0.1301   0.0102   1.0000
   8.000   1.3480   0.03647   0.02812  -0.1301   0.0100   1.0000
   8.250   1.3730   0.03896   0.03085  -0.1295   0.0098   1.0000
   8.500   1.3926   0.04105   0.03320  -0.1281   0.0093   1.0000
   8.750   1.4086   0.04292   0.03529  -0.1264   0.0087   1.0000
   9.000   1.4223   0.04492   0.03755  -0.1245   0.0082   1.0000
   9.250   1.4343   0.04751   0.04041  -0.1224   0.0079   1.0000
   9.500   1.4424   0.05041   0.04361  -0.1198   0.0078   1.0000
   9.750   1.4452   0.05343   0.04695  -0.1165   0.0078   1.0000
  10.000   1.4433   0.05654   0.05037  -0.1128   0.0078   1.0000
  10.250   1.4372   0.05980   0.05393  -0.1089   0.0078   1.0000
  10.500   1.4273   0.06341   0.05787  -0.1050   0.0079   1.0000
  10.750   1.4145   0.06731   0.06208  -0.1014   0.0080   1.0000
  11.000   1.3995   0.07153   0.06659  -0.0984   0.0081   1.0000
  11.250   1.3826   0.07605   0.07138  -0.0959   0.0082   1.0000
  11.500   1.3640   0.08095   0.07655  -0.0943   0.0083   1.0000
  11.750   1.3449   0.08616   0.08200  -0.0935   0.0084   1.0000
  12.000   1.3249   0.09184   0.08791  -0.0936   0.0085   1.0000
  12.250   1.3040   0.09805   0.09432  -0.0947   0.0086   1.0000
  12.500   1.2836   0.10470   0.10117  -0.0970   0.0087   1.0000
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