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GOE 598 AIRFOIL (goe598-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 598 AIRFOIL (goe598-il)
Reynolds number: 50,000
Max Cl/Cd: 30.5 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe598-il-50000-n5.txt
Download as CSV file: xf-goe598-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 598 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.6100   0.10522   0.09851   0.0039   1.0000   0.0457
  -8.750  -0.6087   0.10073   0.09407   0.0016   1.0000   0.0448
  -8.250  -0.6155   0.08800   0.08149  -0.0118   1.0000   0.0387
  -8.000  -0.6126   0.08297   0.07647  -0.0149   1.0000   0.0385
  -7.750  -0.6094   0.07790   0.07136  -0.0179   1.0000   0.0383
  -7.500  -0.6055   0.07276   0.06615  -0.0208   1.0000   0.0381
  -7.250  -0.6002   0.06759   0.06085  -0.0235   1.0000   0.0380
  -7.000  -0.5930   0.06246   0.05551  -0.0257   1.0000   0.0379
  -6.750  -0.5835   0.05741   0.05018  -0.0274   1.0000   0.0377
  -6.500  -0.5714   0.05250   0.04492  -0.0286   1.0000   0.0375
  -6.250  -0.5567   0.04777   0.03967  -0.0293   1.0000   0.0374
  -6.000  -0.5394   0.04325   0.03462  -0.0295   1.0000   0.0375
  -5.750  -0.5195   0.03902   0.02973  -0.0294   1.0000   0.0383
  -5.500  -0.4992   0.03584   0.02622  -0.0292   1.0000   0.0414
  -5.250  -0.4762   0.03306   0.02300  -0.0288   1.0000   0.0451
  -5.000  -0.4510   0.02999   0.01933  -0.0280   1.0000   0.0475
  -4.750  -0.4270   0.02788   0.01700  -0.0274   1.0000   0.0540
  -4.500  -0.4009   0.02591   0.01458  -0.0263   1.0000   0.0617
  -4.250  -0.3762   0.02440   0.01284  -0.0255   1.0000   0.0747
  -4.000  -0.3515   0.02277   0.01105  -0.0245   1.0000   0.0881
  -3.750  -0.3265   0.02117   0.00934  -0.0238   1.0000   0.1065
  -3.500  -0.3032   0.01970   0.00809  -0.0234   1.0000   0.1544
  -3.250  -0.2800   0.01826   0.00704  -0.0230   1.0000   0.2415
  -3.000  -0.2627   0.01650   0.00649  -0.0213   1.0000   0.4794
  -2.750  -0.2468   0.01561   0.00626  -0.0176   1.0000   0.6757
  -2.500  -0.2201   0.01510   0.00601  -0.0152   1.0000   0.8392
  -2.250  -0.1444   0.01482   0.00524  -0.0238   1.0000   1.0000
  -2.000  -0.1258   0.01470   0.00484  -0.0226   1.0000   1.0000
  -1.750  -0.1064   0.01462   0.00451  -0.0215   1.0000   1.0000
  -1.500  -0.0865   0.01457   0.00424  -0.0204   1.0000   1.0000
  -1.250  -0.0661   0.01455   0.00400  -0.0194   1.0000   1.0000
  -1.000  -0.0454   0.01456   0.00385  -0.0185   1.0000   1.0000
  -0.750  -0.0244   0.01460   0.00375  -0.0176   1.0000   1.0000
  -0.500  -0.0034   0.01466   0.00370  -0.0168   1.0000   1.0000
  -0.250   0.0177   0.01475   0.00370  -0.0160   1.0000   1.0000
   0.000   0.0388   0.01488   0.00375  -0.0153   1.0000   1.0000
   0.250   0.0598   0.01504   0.00387  -0.0146   1.0000   1.0000
   0.500   0.0809   0.01523   0.00404  -0.0140   1.0000   1.0000
   0.750   0.1020   0.01547   0.00427  -0.0134   1.0000   1.0000
   1.000   0.1229   0.01574   0.00456  -0.0130   1.0000   1.0000
   1.250   0.1438   0.01606   0.00490  -0.0126   1.0000   1.0000
   1.500   0.1771   0.01641   0.00534  -0.0146   0.9927   1.0000
   1.750   0.2180   0.01678   0.00587  -0.0181   0.9806   1.0000
   2.000   0.2605   0.01713   0.00640  -0.0218   0.9674   1.0000
   2.250   0.3074   0.01738   0.00695  -0.0259   0.9480   1.0000
   2.500   0.3577   0.01752   0.00742  -0.0302   0.9272   1.0000
   2.750   0.3972   0.01767   0.00791  -0.0323   0.9062   1.0000
   3.000   0.4374   0.01769   0.00837  -0.0340   0.8806   1.0000
   3.250   0.4751   0.01751   0.00857  -0.0340   0.8425   1.0000
   3.500   0.5052   0.01744   0.00886  -0.0326   0.8006   1.0000
   3.750   0.5265   0.01726   0.00878  -0.0280   0.7099   1.0000
   4.000   0.5288   0.01863   0.00816  -0.0199   0.3271   1.0000
   4.250   0.5419   0.02198   0.00987  -0.0186   0.0853   1.0000
   4.500   0.5641   0.02380   0.01155  -0.0177   0.0593   1.0000
   4.750   0.5867   0.02553   0.01348  -0.0165   0.0510   1.0000
   5.000   0.6090   0.02748   0.01545  -0.0154   0.0429   1.0000
   5.250   0.6351   0.02929   0.01761  -0.0141   0.0395   1.0000
   5.500   0.6616   0.03156   0.02024  -0.0131   0.0373   1.0000
   5.750   0.6862   0.03403   0.02291  -0.0123   0.0345   1.0000
   6.000   0.7099   0.03688   0.02622  -0.0114   0.0322   1.0000
   6.250   0.7324   0.04002   0.02996  -0.0103   0.0311   1.0000
   6.500   0.7522   0.04360   0.03409  -0.0092   0.0309   1.0000
   6.750   0.7690   0.04746   0.03849  -0.0082   0.0309   1.0000
   7.000   0.7826   0.05160   0.04314  -0.0073   0.0312   1.0000
   7.250   0.7931   0.05593   0.04791  -0.0067   0.0315   1.0000
   7.500   0.8007   0.06039   0.05275  -0.0062   0.0319   1.0000
   7.750   0.8054   0.06494   0.05760  -0.0060   0.0323   1.0000
   8.000   0.8073   0.06953   0.06243  -0.0061   0.0326   1.0000
   8.250   0.8069   0.07412   0.06721  -0.0065   0.0329   1.0000
   8.500   0.8047   0.07872   0.07194  -0.0071   0.0332   1.0000
   8.750   0.8017   0.08330   0.07660  -0.0079   0.0334   1.0000
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