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GOE 610 B AIRFOIL (goe610b-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 610 B AIRFOIL (goe610b-il)
Reynolds number: 100,000
Max Cl/Cd: 62.67 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe610b-il-100000-n5.txt
Download as CSV file: xf-goe610b-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 610 B 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2864   0.10376   0.09907  -0.0362   1.0000   0.0421
  -8.250  -0.2913   0.10194   0.09736  -0.0352   1.0000   0.0422
  -8.000  -0.3021   0.10073   0.09626  -0.0332   1.0000   0.0422
  -7.750  -0.2989   0.09812   0.09371  -0.0357   0.9940   0.0423
  -7.500  -0.2804   0.09401   0.08959  -0.0431   0.9824   0.0425
  -7.250  -0.2597   0.08954   0.08510  -0.0504   0.9720   0.0426
  -7.000  -0.2375   0.08479   0.08031  -0.0564   0.9642   0.0426
  -6.750  -0.2190   0.08033   0.07582  -0.0602   0.9549   0.0425
  -6.500  -0.2020   0.07578   0.07127  -0.0597   0.9508   0.0406
  -6.250  -0.1810   0.07159   0.06703  -0.0652   0.9403   0.0407
  -6.000  -0.1495   0.06661   0.06190  -0.0756   0.9300   0.0423
  -5.750  -0.1261   0.06226   0.05746  -0.0793   0.9227   0.0418
  -5.500  -0.1031   0.05811   0.05320  -0.0832   0.9132   0.0415
  -5.250  -0.0775   0.05530   0.05033  -0.0860   0.9065   0.0476
  -5.000  -0.0489   0.05140   0.04621  -0.0909   0.8962   0.0517
  -4.750  -0.0231   0.04910   0.04382  -0.0934   0.8888   0.0653
  -4.500   0.0068   0.04384   0.03820  -0.0973   0.8797   0.0553
  -4.250   0.0343   0.04106   0.03515  -0.0992   0.8713   0.0599
  -4.000   0.0627   0.03759   0.03137  -0.1010   0.8637   0.0589
  -3.750   0.0908   0.03419   0.02742  -0.1022   0.8547   0.0628
  -3.500   0.1174   0.03260   0.02574  -0.1029   0.8478   0.0656
  -3.250   0.1426   0.03000   0.02271  -0.1029   0.8383   0.0647
  -3.000   0.1705   0.02800   0.02032  -0.1031   0.8306   0.0651
  -2.750   0.1966   0.02683   0.01888  -0.1030   0.8214   0.0695
  -2.500   0.2232   0.02530   0.01697  -0.1027   0.8126   0.0697
  -2.250   0.2509   0.02385   0.01519  -0.1025   0.8045   0.0688
  -2.000   0.2764   0.02266   0.01368  -0.1020   0.7950   0.0682
  -1.750   0.3051   0.02152   0.01221  -0.1019   0.7878   0.0681
  -1.500   0.3303   0.02066   0.01111  -0.1012   0.7779   0.0684
  -1.250   0.3577   0.01986   0.01007  -0.1008   0.7701   0.0693
  -1.000   0.3842   0.01920   0.00922  -0.1004   0.7613   0.0707
  -0.750   0.4108   0.01868   0.00852  -0.0999   0.7531   0.0721
  -0.500   0.4374   0.01815   0.00796  -0.0996   0.7452   0.0739
  -0.250   0.4629   0.01784   0.00765  -0.0991   0.7367   0.0761
   0.000   0.4898   0.01765   0.00741  -0.0988   0.7296   0.0814
   0.250   0.5153   0.01746   0.00718  -0.0982   0.7211   0.0850
   0.500   0.5420   0.01711   0.00681  -0.0978   0.7139   0.0863
   0.750   0.5670   0.01690   0.00660  -0.0972   0.7041   0.0874
   1.000   0.5944   0.01671   0.00635  -0.0969   0.6956   0.0891
   1.250   0.6211   0.01659   0.00617  -0.0964   0.6867   0.0916
   1.500   0.6476   0.01653   0.00604  -0.0960   0.6785   0.0953
   1.750   0.6746   0.01646   0.00593  -0.0957   0.6708   0.1009
   2.000   0.7007   0.01643   0.00593  -0.0953   0.6629   0.1146
   2.250   0.7277   0.01625   0.00591  -0.0950   0.6559   0.1754
   2.750   0.8091   0.01495   0.00603  -0.1006   0.6379   1.0000
   3.000   0.8328   0.01511   0.00613  -0.0996   0.6271   1.0000
   3.250   0.8565   0.01528   0.00626  -0.0987   0.6165   1.0000
   3.500   0.8807   0.01545   0.00635  -0.0978   0.6060   1.0000
   3.750   0.9046   0.01563   0.00650  -0.0968   0.5953   1.0000
   4.000   0.9278   0.01585   0.00675  -0.0959   0.5861   1.0000
   4.250   0.9528   0.01606   0.00694  -0.0953   0.5789   1.0000
   4.500   0.9756   0.01632   0.00727  -0.0943   0.5700   1.0000
   4.750   0.9997   0.01654   0.00754  -0.0935   0.5619   1.0000
   5.000   1.0224   0.01679   0.00786  -0.0925   0.5517   1.0000
   5.250   1.0448   0.01704   0.00817  -0.0914   0.5404   1.0000
   5.500   1.0669   0.01728   0.00850  -0.0903   0.5280   1.0000
   5.750   1.0890   0.01753   0.00881  -0.0891   0.5158   1.0000
   6.000   1.1106   0.01780   0.00918  -0.0879   0.5029   1.0000
   6.250   1.1312   0.01808   0.00959  -0.0866   0.4884   1.0000
   6.500   1.1512   0.01837   0.01002  -0.0851   0.4715   1.0000
   6.750   1.1698   0.01869   0.01048  -0.0834   0.4495   1.0000
   7.000   1.1873   0.01902   0.01086  -0.0815   0.4201   1.0000
   7.250   1.2038   0.01944   0.01123  -0.0794   0.3902   1.0000
   7.500   1.2187   0.01998   0.01168  -0.0772   0.3659   1.0000
   7.750   1.2296   0.02077   0.01231  -0.0743   0.3382   1.0000
   8.000   1.2380   0.02175   0.01311  -0.0713   0.3102   1.0000
   8.250   1.2465   0.02271   0.01399  -0.0684   0.2823   1.0000
   8.500   1.2546   0.02363   0.01488  -0.0655   0.2531   1.0000
   8.750   1.2587   0.02462   0.01578  -0.0621   0.2165   1.0000
   9.000   1.2582   0.02593   0.01682  -0.0582   0.1596   1.0000
   9.250   1.2527   0.02777   0.01825  -0.0542   0.1273   1.0000
   9.500   1.2530   0.02946   0.01984  -0.0512   0.1097   1.0000
   9.750   1.2601   0.03081   0.02133  -0.0489   0.0763   1.0000
  10.250   1.2553   0.03514   0.02530  -0.0435   0.0402   1.0000
  10.500   1.2552   0.03724   0.02748  -0.0413   0.0352   1.0000
  10.750   1.2554   0.03939   0.02972  -0.0393   0.0321   1.0000
  11.000   1.2547   0.04170   0.03214  -0.0376   0.0296   1.0000
  11.250   1.2531   0.04416   0.03470  -0.0361   0.0277   1.0000
  11.500   1.2523   0.04666   0.03737  -0.0348   0.0261   1.0000
  11.750   1.2501   0.04941   0.04026  -0.0336   0.0249   1.0000
  12.000   1.2482   0.05219   0.04318  -0.0326   0.0240   1.0000
  12.250   1.2458   0.05513   0.04623  -0.0318   0.0233   1.0000
  12.500   1.2416   0.05834   0.04951  -0.0311   0.0225   1.0000
  12.750   1.2419   0.06113   0.05242  -0.0303   0.0217   1.0000
  13.000   1.2450   0.06372   0.05519  -0.0296   0.0210   1.0000
  13.250   1.2480   0.06640   0.05806  -0.0289   0.0201   1.0000
  13.500   1.2511   0.06915   0.06107  -0.0282   0.0193   1.0000
  13.750   1.2547   0.07197   0.06408  -0.0276   0.0188   1.0000
  14.000   1.2575   0.07502   0.06732  -0.0271   0.0183   1.0000
  14.250   1.2585   0.07837   0.07088  -0.0268   0.0179   1.0000
  14.500   1.2570   0.08212   0.07486  -0.0269   0.0176   1.0000
  14.750   1.2528   0.08629   0.07926  -0.0274   0.0173   1.0000
  15.000   1.2464   0.09087   0.08407  -0.0284   0.0170   1.0000
  15.250   1.2377   0.09589   0.08931  -0.0298   0.0167   1.0000
  15.500   1.2281   0.10122   0.09486  -0.0317   0.0166   1.0000
  15.750   1.2163   0.10709   0.10094  -0.0341   0.0163   1.0000
  16.000   1.2039   0.11331   0.10738  -0.0371   0.0161   1.0000
  16.250   1.1903   0.12011   0.11439  -0.0405   0.0160   1.0000
  16.500   1.1747   0.12781   0.12231  -0.0448   0.0161   1.0000
  16.750   1.1573   0.13645   0.13117  -0.0500   0.0163   1.0000
  17.000   1.1363   0.14683   0.14177  -0.0565   0.0166   1.0000
  17.250   1.1072   0.16076   0.15590  -0.0653   0.0175   1.0000
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