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GOE 645 AIRFOIL (goe645-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 645 AIRFOIL (goe645-il)
Reynolds number: 100,000
Max Cl/Cd: 48.7 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe645-il-100000-n5.txt
Download as CSV file: xf-goe645-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 645 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6545   0.04760   0.04190  -0.0766   1.0000   0.0504
 -10.500  -0.6647   0.04531   0.03951  -0.0754   0.9980   0.0509
 -10.250  -0.6411   0.04208   0.03606  -0.0801   0.9868   0.0523
 -10.000  -0.6189   0.03889   0.03255  -0.0839   0.9750   0.0536
  -9.750  -0.5958   0.03607   0.02935  -0.0866   0.9631   0.0552
  -9.500  -0.5699   0.03376   0.02671  -0.0889   0.9524   0.0569
  -9.250  -0.5390   0.03232   0.02527  -0.0907   0.9434   0.0586
  -9.000  -0.5115   0.03086   0.02369  -0.0919   0.9324   0.0603
  -8.750  -0.4789   0.02927   0.02189  -0.0939   0.9245   0.0624
  -8.500  -0.4513   0.02789   0.02030  -0.0947   0.9129   0.0647
  -8.250  -0.4216   0.02689   0.01930  -0.0957   0.9024   0.0671
  -8.000  -0.3896   0.02582   0.01812  -0.0970   0.8929   0.0700
  -7.750  -0.3620   0.02482   0.01695  -0.0973   0.8808   0.0729
  -7.500  -0.3307   0.02403   0.01613  -0.0983   0.8707   0.0765
  -7.250  -0.3017   0.02326   0.01520  -0.0987   0.8590   0.0817
  -7.000  -0.2739   0.02261   0.01451  -0.0989   0.8471   0.0875
  -6.750  -0.2436   0.02188   0.01364  -0.0994   0.8369   0.0956
  -6.500  -0.2178   0.02127   0.01289  -0.0990   0.8242   0.1060
  -6.250  -0.1908   0.02072   0.01221  -0.0989   0.8128   0.1181
  -6.000  -0.1627   0.02021   0.01164  -0.0989   0.8022   0.1305
  -5.750  -0.1375   0.01985   0.01124  -0.0984   0.7897   0.1416
  -5.500  -0.1100   0.01955   0.01085  -0.0982   0.7788   0.1533
  -5.250  -0.0827   0.01930   0.01050  -0.0979   0.7676   0.1648
  -5.000  -0.0566   0.01915   0.01027  -0.0974   0.7559   0.1766
  -4.750  -0.0288   0.01905   0.01009  -0.0971   0.7455   0.1894
  -4.500  -0.0032   0.01899   0.01000  -0.0965   0.7336   0.2019
  -4.250   0.0233   0.01895   0.00987  -0.0960   0.7226   0.2149
  -4.000   0.0503   0.01886   0.00963  -0.0955   0.7119   0.2276
  -3.750   0.0758   0.01877   0.00952  -0.0948   0.7003   0.2369
  -3.500   0.1029   0.01861   0.00922  -0.0943   0.6903   0.2467
  -3.250   0.1285   0.01852   0.00906  -0.0936   0.6787   0.2562
  -3.000   0.1547   0.01843   0.00887  -0.0931   0.6680   0.2658
  -2.750   0.1813   0.01836   0.00868  -0.0925   0.6578   0.2758
  -2.500   0.2069   0.01830   0.00857  -0.0919   0.6468   0.2850
  -2.250   0.2338   0.01826   0.00838  -0.0914   0.6374   0.2955
  -2.000   0.2591   0.01820   0.00831  -0.0907   0.6264   0.3042
  -1.750   0.2856   0.01818   0.00817  -0.0902   0.6170   0.3140
  -1.500   0.3115   0.01813   0.00808  -0.0896   0.6071   0.3220
  -1.250   0.3377   0.01811   0.00799  -0.0890   0.5978   0.3309
  -1.000   0.3637   0.01808   0.00790  -0.0885   0.5887   0.3395
  -0.750   0.3896   0.01810   0.00786  -0.0879   0.5795   0.3510
  -0.500   0.4155   0.01809   0.00784  -0.0873   0.5709   0.3626
  -0.250   0.4411   0.01810   0.00783  -0.0867   0.5619   0.3748
   0.000   0.4671   0.01811   0.00777  -0.0862   0.5530   0.3868
   0.250   0.4921   0.01810   0.00778  -0.0855   0.5428   0.3979
   0.750   0.5433   0.01812   0.00774  -0.0843   0.5233   0.4212
   1.000   0.5696   0.01814   0.00771  -0.0838   0.5152   0.4340
   1.250   0.5947   0.01818   0.00782  -0.0832   0.5063   0.4502
   1.500   0.6209   0.01821   0.00785  -0.0827   0.4994   0.4716
   1.750   0.6456   0.01824   0.00802  -0.0820   0.4916   0.5008
   2.000   0.6702   0.01822   0.00812  -0.0813   0.4847   0.5466
   2.250   0.6933   0.01804   0.00824  -0.0802   0.4781   0.6336
   2.500   0.7526   0.01767   0.00844  -0.0861   0.4675   1.0000
   2.750   0.7762   0.01792   0.00856  -0.0852   0.4600   1.0000
   3.000   0.7988   0.01816   0.00872  -0.0842   0.4514   1.0000
   3.250   0.8224   0.01842   0.00884  -0.0833   0.4444   1.0000
   3.500   0.8445   0.01868   0.00908  -0.0823   0.4360   1.0000
   3.750   0.8678   0.01894   0.00920  -0.0814   0.4290   1.0000
   4.000   0.8898   0.01924   0.00950  -0.0803   0.4214   1.0000
   4.250   0.9123   0.01952   0.00972  -0.0793   0.4145   1.0000
   4.500   0.9350   0.01983   0.00997  -0.0784   0.4082   1.0000
   4.750   0.9566   0.02015   0.01029  -0.0773   0.4010   1.0000
   5.000   0.9790   0.02045   0.01051  -0.0764   0.3948   1.0000
   5.250   0.9997   0.02080   0.01088  -0.0752   0.3874   1.0000
   5.500   1.0206   0.02112   0.01117  -0.0740   0.3803   1.0000
   5.750   1.0411   0.02148   0.01150  -0.0728   0.3733   1.0000
   6.000   1.0605   0.02183   0.01186  -0.0714   0.3656   1.0000
   6.250   1.0806   0.02219   0.01216  -0.0701   0.3592   1.0000
   6.500   1.0993   0.02260   0.01263  -0.0687   0.3521   1.0000
   6.750   1.1185   0.02299   0.01299  -0.0674   0.3463   1.0000
   7.000   1.1371   0.02343   0.01345  -0.0660   0.3404   1.0000
   7.250   1.1552   0.02389   0.01394  -0.0646   0.3347   1.0000
   7.500   1.1735   0.02433   0.01437  -0.0631   0.3300   1.0000
   7.750   1.1909   0.02484   0.01491  -0.0617   0.3251   1.0000
   8.000   1.2066   0.02535   0.01549  -0.0599   0.3200   1.0000
   8.250   1.2218   0.02585   0.01600  -0.0581   0.3155   1.0000
   8.500   1.2368   0.02638   0.01653  -0.0563   0.3111   1.0000
   8.750   1.2495   0.02701   0.01725  -0.0543   0.3059   1.0000
   9.000   1.2627   0.02762   0.01790  -0.0524   0.3013   1.0000
   9.250   1.2774   0.02821   0.01847  -0.0507   0.2975   1.0000
   9.500   1.2889   0.02898   0.01934  -0.0488   0.2929   1.0000
   9.750   1.2998   0.02977   0.02022  -0.0469   0.2883   1.0000
  10.000   1.3119   0.03053   0.02101  -0.0453   0.2844   1.0000
  10.250   1.3255   0.03127   0.02174  -0.0438   0.2809   1.0000
  10.500   1.3324   0.03237   0.02299  -0.0419   0.2761   1.0000
  10.750   1.3402   0.03344   0.02416  -0.0402   0.2715   1.0000
  11.000   1.3500   0.03442   0.02516  -0.0387   0.2675   1.0000
  11.250   1.3594   0.03551   0.02630  -0.0373   0.2636   1.0000
  11.500   1.3634   0.03701   0.02796  -0.0358   0.2593   1.0000
  11.750   1.3686   0.03848   0.02953  -0.0344   0.2551   1.0000
  12.000   1.3763   0.03978   0.03086  -0.0332   0.2511   1.0000
  12.250   1.3833   0.04121   0.03234  -0.0322   0.2472   1.0000
  12.500   1.3819   0.04340   0.03473  -0.0310   0.2428   1.0000
  12.750   1.3823   0.04549   0.03693  -0.0301   0.2383   1.0000
  13.000   1.3882   0.04712   0.03860  -0.0293   0.2341   1.0000
  13.250   1.3890   0.04931   0.04087  -0.0286   0.2298   1.0000
  13.500   1.3801   0.05259   0.04433  -0.0282   0.2247   1.0000
  13.750   1.3778   0.05525   0.04708  -0.0278   0.2199   1.0000
  14.000   1.3879   0.05655   0.04834  -0.0272   0.2157   1.0000
  14.250   1.3671   0.06161   0.05367  -0.0277   0.2102   1.0000
  14.500   1.3577   0.06548   0.05765  -0.0280   0.2050   1.0000
  14.750   1.3648   0.06728   0.05945  -0.0278   0.2008   1.0000
  15.000   1.3438   0.07303   0.06539  -0.0290   0.1955   1.0000
  15.250   1.3282   0.07824   0.07074  -0.0302   0.1904   1.0000
  15.500   1.3321   0.08070   0.07324  -0.0304   0.1870   1.0000
  15.750   1.3203   0.08560   0.07824  -0.0316   0.1830   1.0000
  16.000   1.2801   0.09516   0.08801  -0.0349   0.1776   1.0000
  16.250   1.2771   0.09897   0.09188  -0.0359   0.1745   1.0000
  16.500   1.2886   0.10043   0.09337  -0.0359   0.1727   1.0000
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