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GOE 177 AIRFOIL (goe177-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 177 AIRFOIL (goe177-il)
Reynolds number: 50,000
Max Cl/Cd: 41.5 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe177-il-50000-n5.txt
Download as CSV file: xf-goe177-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 177 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3052   0.10234   0.09611  -0.0216   1.0000   0.0768
  -7.250  -0.3059   0.10043   0.09432  -0.0227   1.0000   0.0787
  -7.000  -0.3058   0.09880   0.09281  -0.0257   1.0000   0.0801
  -6.750  -0.3027   0.09689   0.09101  -0.0294   1.0000   0.0807
  -6.500  -0.2970   0.09458   0.08878  -0.0330   1.0000   0.0810
  -6.250  -0.2912   0.09030   0.08460  -0.0317   1.0000   0.0818
  -6.000  -0.2854   0.08628   0.08065  -0.0285   1.0000   0.0838
  -5.750  -0.2795   0.08333   0.07777  -0.0288   1.0000   0.0849
  -5.500  -0.2731   0.08044   0.07492  -0.0299   1.0000   0.0854
  -5.250  -0.2654   0.07749   0.07203  -0.0317   1.0000   0.0849
  -5.000  -0.2399   0.07179   0.06622  -0.0416   1.0000   0.0536
  -4.750  -0.2390   0.06897   0.06345  -0.0377   1.0000   0.0508
  -4.500  -0.2296   0.06583   0.06034  -0.0385   1.0000   0.0487
  -4.250  -0.2152   0.06235   0.05683  -0.0409   0.9997   0.0466
  -4.000  -0.1579   0.05497   0.04913  -0.0537   0.9897   0.0428
  -3.750  -0.1110   0.05008   0.04399  -0.0615   0.9794   0.0441
  -3.500  -0.0624   0.04548   0.03907  -0.0689   0.9686   0.0474
  -3.250  -0.0110   0.04012   0.03321  -0.0764   0.9578   0.0484
  -3.000   0.0403   0.03500   0.02736  -0.0827   0.9472   0.0501
  -2.750   0.0874   0.03177   0.02357  -0.0874   0.9357   0.0582
  -2.500   0.1376   0.02810   0.01889  -0.0915   0.9252   0.0665
  -2.250   0.1768   0.02650   0.01700  -0.0938   0.9093   0.0859
  -2.000   0.2163   0.02467   0.01455  -0.0955   0.8931   0.1096
  -1.750   0.2524   0.02346   0.01315  -0.0966   0.8757   0.1342
  -1.500   0.2895   0.02262   0.01203  -0.0978   0.8582   0.1598
  -1.250   0.3249   0.02186   0.01095  -0.0985   0.8400   0.1779
  -1.000   0.3576   0.02125   0.01013  -0.0987   0.8205   0.1954
  -0.750   0.3895   0.02070   0.00945  -0.0987   0.8019   0.2151
  -0.500   0.4197   0.02021   0.00886  -0.0985   0.7833   0.2418
  -0.250   0.4478   0.01973   0.00849  -0.0981   0.7638   0.2998
   0.000   0.4720   0.01781   0.00806  -0.0966   0.7458   1.0000
   0.250   0.5002   0.01799   0.00773  -0.0960   0.7280   1.0000
   0.500   0.5270   0.01822   0.00759  -0.0954   0.7097   1.0000
   0.750   0.5534   0.01848   0.00754  -0.0947   0.6918   1.0000
   1.000   0.5797   0.01874   0.00753  -0.0941   0.6747   1.0000
   1.250   0.6060   0.01902   0.00758  -0.0935   0.6585   1.0000
   1.500   0.6320   0.01932   0.00767  -0.0929   0.6428   1.0000
   1.750   0.6581   0.01963   0.00781  -0.0924   0.6275   1.0000
   2.000   0.6844   0.01996   0.00799  -0.0919   0.6128   1.0000
   2.250   0.7106   0.02031   0.00821  -0.0915   0.5987   1.0000
   2.500   0.7367   0.02067   0.00848  -0.0911   0.5850   1.0000
   2.750   0.7628   0.02105   0.00882  -0.0908   0.5719   1.0000
   3.000   0.7888   0.02145   0.00917  -0.0904   0.5596   1.0000
   3.250   0.8149   0.02187   0.00954  -0.0901   0.5481   1.0000
   3.500   0.8412   0.02227   0.00994  -0.0897   0.5377   1.0000
   3.750   0.8668   0.02275   0.01046  -0.0894   0.5267   1.0000
   4.000   0.8924   0.02326   0.01102  -0.0891   0.5165   1.0000
   4.250   0.9186   0.02373   0.01155  -0.0888   0.5079   1.0000
   4.500   0.9437   0.02426   0.01219  -0.0884   0.4979   1.0000
   4.750   0.9683   0.02477   0.01280  -0.0880   0.4873   1.0000
   5.000   0.9932   0.02522   0.01332  -0.0874   0.4770   1.0000
   5.250   1.0179   0.02565   0.01389  -0.0868   0.4667   1.0000
   5.500   1.0415   0.02621   0.01463  -0.0862   0.4560   1.0000
   5.750   1.0657   0.02673   0.01531  -0.0856   0.4468   1.0000
   6.000   1.0884   0.02706   0.01576  -0.0847   0.4332   1.0000
   6.250   1.1068   0.02694   0.01559  -0.0827   0.4066   1.0000
   6.500   1.1259   0.02725   0.01611  -0.0813   0.3853   1.0000
   6.750   1.1457   0.02761   0.01658  -0.0799   0.3664   1.0000
   7.000   1.1646   0.02809   0.01720  -0.0785   0.3455   1.0000
   7.250   1.1845   0.02867   0.01803  -0.0773   0.3290   1.0000
   7.500   1.2010   0.02930   0.01878  -0.0757   0.3012   1.0000
   7.750   1.2148   0.03017   0.01970  -0.0739   0.2553   1.0000
   8.000   1.2227   0.03166   0.02079  -0.0717   0.1577   1.0000
   8.500   1.2111   0.03842   0.02667  -0.0666   0.0514   1.0000
   8.750   1.2136   0.04065   0.02914  -0.0644   0.0387   1.0000
   9.000   1.2135   0.04302   0.03175  -0.0624   0.0326   1.0000
   9.250   1.2110   0.04578   0.03470  -0.0608   0.0293   1.0000
   9.500   1.2059   0.04904   0.03810  -0.0599   0.0275   1.0000
   9.750   1.1995   0.05275   0.04201  -0.0598   0.0265   1.0000
  10.000   1.1925   0.05689   0.04637  -0.0602   0.0259   1.0000
  10.250   1.1849   0.06134   0.05103  -0.0610   0.0255   1.0000
  10.500   1.1771   0.06598   0.05588  -0.0620   0.0251   1.0000
  10.750   1.1694   0.07068   0.06077  -0.0630   0.0248   1.0000
  11.000   1.1620   0.07535   0.06562  -0.0640   0.0246   1.0000
  11.250   1.1552   0.07991   0.07034  -0.0648   0.0243   1.0000
  11.500   1.1493   0.08431   0.07489  -0.0655   0.0240   1.0000
  11.750   1.1447   0.08845   0.07918  -0.0661   0.0238   1.0000
  12.000   1.1415   0.09232   0.08319  -0.0664   0.0235   1.0000
  12.250   1.1399   0.09589   0.08688  -0.0664   0.0232   1.0000
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