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GOE 284 AIRFOIL (goe284-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 284 AIRFOIL (goe284-il)
Reynolds number: 100,000
Max Cl/Cd: 45.19 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe284-il-100000-n5.txt
Download as CSV file: xf-goe284-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 284 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  -0.2510   0.09628   0.09084  -0.0623   0.8987   0.0632
 -10.500  -0.2699   0.08875   0.08327  -0.0663   0.8807   0.0649
 -10.250  -0.2847   0.08240   0.07690  -0.0694   0.8617   0.0662
 -10.000  -0.2841   0.07925   0.07370  -0.0703   0.8406   0.0672
  -9.750  -0.4862   0.04168   0.03508  -0.0967   0.8281   0.0724
  -9.500  -0.4668   0.04135   0.03469  -0.0957   0.8105   0.0736
  -9.250  -0.4561   0.03954   0.03262  -0.0950   0.7938   0.0760
  -9.000  -0.4512   0.03643   0.02898  -0.0943   0.7790   0.0799
  -8.750  -0.4290   0.03621   0.02867  -0.0935   0.7646   0.0821
  -8.500  -0.4172   0.03387   0.02576  -0.0928   0.7509   0.0872
  -8.250  -0.3922   0.03387   0.02576  -0.0923   0.7385   0.0894
  -8.000  -0.3723   0.03277   0.02430  -0.0917   0.7278   0.0936
  -7.750  -0.3506   0.03184   0.02311  -0.0914   0.7173   0.0970
  -7.500  -0.3260   0.03154   0.02272  -0.0910   0.7081   0.0998
  -7.250  -0.3040   0.03055   0.02132  -0.0906   0.6994   0.1043
  -7.000  -0.2795   0.02998   0.02062  -0.0903   0.6910   0.1072
  -6.750  -0.2539   0.02971   0.02026  -0.0900   0.6839   0.1102
  -6.500  -0.2293   0.02920   0.01949  -0.0898   0.6760   0.1151
  -6.250  -0.2039   0.02883   0.01903  -0.0896   0.6694   0.1191
  -6.000  -0.1776   0.02869   0.01884  -0.0895   0.6638   0.1233
  -5.750  -0.1519   0.02814   0.01804  -0.0894   0.6578   0.1276
  -5.500  -0.1259   0.02740   0.01705  -0.0893   0.6524   0.1301
  -5.250  -0.0992   0.02680   0.01639  -0.0892   0.6479   0.1320
  -5.000  -0.0721   0.02629   0.01576  -0.0892   0.6438   0.1340
  -4.750  -0.0449   0.02576   0.01515  -0.0892   0.6388   0.1359
  -4.500  -0.0176   0.02526   0.01451  -0.0892   0.6341   0.1377
  -4.250   0.0099   0.02480   0.01389  -0.0891   0.6298   0.1399
  -4.000   0.0378   0.02440   0.01328  -0.0891   0.6262   0.1420
  -3.750   0.0656   0.02401   0.01278  -0.0891   0.6225   0.1438
  -3.500   0.0931   0.02360   0.01241  -0.0891   0.6185   0.1454
  -3.250   0.1208   0.02329   0.01211  -0.0892   0.6149   0.1473
  -3.000   0.1486   0.02303   0.01182  -0.0892   0.6116   0.1497
  -2.750   0.1766   0.02280   0.01153  -0.0892   0.6085   0.1525
  -2.500   0.2048   0.02259   0.01122  -0.0891   0.6056   0.1554
  -2.250   0.2324   0.02245   0.01103  -0.0891   0.6022   0.1579
  -2.000   0.2593   0.02224   0.01091  -0.0890   0.5985   0.1604
  -1.750   0.2865   0.02210   0.01083  -0.0890   0.5954   0.1636
  -1.500   0.3139   0.02201   0.01075  -0.0889   0.5923   0.1678
  -1.250   0.3416   0.02193   0.01062  -0.0889   0.5893   0.1727
  -1.000   0.3693   0.02180   0.01051  -0.0888   0.5866   0.1778
  -0.750   0.3968   0.02176   0.01048  -0.0887   0.5839   0.1841
  -0.250   0.4491   0.02177   0.01071  -0.0884   0.5763   0.2032
   0.000   0.4760   0.02166   0.01069  -0.0882   0.5716   0.2214
   0.250   0.5038   0.02147   0.01057  -0.0881   0.5673   0.2538
   0.500   0.5307   0.02131   0.01058  -0.0880   0.5628   0.3080
   0.750   0.5548   0.02113   0.01079  -0.0877   0.5573   0.3903
   1.000   0.5774   0.02066   0.01097  -0.0867   0.5529   0.5581
   1.250   0.5986   0.02012   0.01115  -0.0843   0.5492   0.7915
   1.500   0.6515   0.02002   0.01108  -0.0883   0.5453   0.9598
   1.750   0.6888   0.02031   0.01136  -0.0906   0.5400   1.0000
   2.000   0.7115   0.02057   0.01157  -0.0898   0.5351   1.0000
   2.250   0.7363   0.02074   0.01163  -0.0892   0.5307   1.0000
   2.500   0.7629   0.02086   0.01161  -0.0889   0.5269   1.0000
   2.750   0.7871   0.02111   0.01180  -0.0883   0.5226   1.0000
   3.000   0.8086   0.02145   0.01216  -0.0875   0.5169   1.0000
   3.250   0.8330   0.02166   0.01232  -0.0869   0.5121   1.0000
   3.500   0.8598   0.02178   0.01232  -0.0866   0.5079   1.0000
   3.750   0.8849   0.02200   0.01249  -0.0862   0.5035   1.0000
   4.000   0.9051   0.02241   0.01296  -0.0852   0.4974   1.0000
   4.250   0.9293   0.02262   0.01314  -0.0846   0.4922   1.0000
   4.500   0.9565   0.02271   0.01313  -0.0844   0.4879   1.0000
   4.750   0.9774   0.02308   0.01355  -0.0835   0.4820   1.0000
   5.000   0.9982   0.02341   0.01392  -0.0825   0.4755   1.0000
   5.250   1.0238   0.02352   0.01396  -0.0821   0.4703   1.0000
   5.500   1.0448   0.02384   0.01430  -0.0811   0.4643   1.0000
   5.750   1.0637   0.02424   0.01476  -0.0799   0.4571   1.0000
   6.000   1.0883   0.02436   0.01483  -0.0794   0.4518   1.0000
   6.250   1.1053   0.02485   0.01539  -0.0780   0.4446   1.0000
   6.500   1.1244   0.02520   0.01577  -0.0768   0.4376   1.0000
   6.750   1.1470   0.02538   0.01591  -0.0760   0.4320   1.0000
   7.000   1.1591   0.02607   0.01670  -0.0740   0.4235   1.0000
   7.250   1.1802   0.02627   0.01686  -0.0730   0.4175   1.0000
   7.500   1.1909   0.02700   0.01768  -0.0709   0.4093   1.0000
   7.750   1.2060   0.02739   0.01805  -0.0692   0.4027   1.0000
   8.000   1.2166   0.02807   0.01874  -0.0670   0.3957   1.0000
   8.250   1.2279   0.02877   0.01946  -0.0651   0.3887   1.0000
   8.500   1.2445   0.02924   0.01989  -0.0638   0.3830   1.0000
   8.750   1.2510   0.03037   0.02108  -0.0617   0.3757   1.0000
   9.000   1.2675   0.03093   0.02158  -0.0605   0.3702   1.0000
   9.250   1.2773   0.03200   0.02267  -0.0590   0.3642   1.0000
   9.500   1.2865   0.03315   0.02386  -0.0575   0.3583   1.0000
   9.750   1.3051   0.03367   0.02430  -0.0566   0.3535   1.0000
  10.000   1.3113   0.03515   0.02584  -0.0552   0.3478   1.0000
  10.250   1.3194   0.03653   0.02726  -0.0539   0.3424   1.0000
  10.500   1.3375   0.03715   0.02784  -0.0531   0.3380   1.0000
  10.750   1.3479   0.03846   0.02918  -0.0521   0.3336   1.0000
  11.000   1.3515   0.04036   0.03118  -0.0509   0.3289   1.0000
  11.250   1.3628   0.04166   0.03251  -0.0501   0.3250   1.0000
  11.500   1.3825   0.04225   0.03308  -0.0495   0.3218   1.0000
  11.750   1.3966   0.04335   0.03421  -0.0488   0.3185   1.0000
  12.000   1.3920   0.04613   0.03715  -0.0477   0.3142   1.0000
  12.250   1.3962   0.04815   0.03925  -0.0469   0.3102   1.0000
  12.500   1.4109   0.04918   0.04031  -0.0463   0.3067   1.0000
  12.750   1.4381   0.04905   0.04011  -0.0459   0.3037   1.0000
  13.000   1.4222   0.05309   0.04437  -0.0450   0.2998   1.0000
  13.250   1.4109   0.05687   0.04832  -0.0444   0.2958   1.0000
  13.500   1.4130   0.05931   0.05085  -0.0439   0.2925   1.0000
  13.750   1.4274   0.06043   0.05202  -0.0434   0.2899   1.0000
  14.000   1.4525   0.06039   0.05198  -0.0429   0.2876   1.0000
  14.250   1.4097   0.06802   0.05988  -0.0429   0.2829   1.0000
  14.500   1.3480   0.07871   0.07083  -0.0439   0.2759   1.0000
  14.750   1.3739   0.07821   0.07033  -0.0433   0.2732   1.0000
  15.000   1.4115   0.07624   0.06835  -0.0425   0.2711   1.0000
  15.500   1.2368   0.10754   0.10013  -0.0488   0.2515   1.0000
  15.750   1.3007   0.10079   0.09337  -0.0464   0.2526   1.0000
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