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GOE 677 (= M 6) AIRFOIL (goe677-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 677 (= M 6) AIRFOIL (goe677-il)
Reynolds number: 50,000
Max Cl/Cd: 29.37 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe677-il-50000.txt
Download as CSV file: xf-goe677-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 677 (= M 6) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5094   0.13113   0.12398   0.0032   1.0000   0.2367
 -10.250  -0.4829   0.12536   0.11817   0.0044   1.0000   0.2451
 -10.000  -0.5126   0.12504   0.11799   0.0013   1.0000   0.2531
  -9.750  -0.4822   0.11940   0.11230   0.0031   1.0000   0.2668
  -9.500  -0.4701   0.11539   0.10830   0.0034   1.0000   0.2783
  -9.250  -0.4704   0.11218   0.10515   0.0030   1.0000   0.2898
  -9.000  -0.4969   0.11128   0.10438   0.0012   1.0000   0.3018
  -8.750  -0.4812   0.10719   0.10028   0.0022   1.0000   0.3174
  -8.500  -0.4685   0.10336   0.09647   0.0030   1.0000   0.3330
  -8.250  -0.4655   0.10025   0.09340   0.0035   1.0000   0.3496
  -8.000  -0.4668   0.09730   0.09054   0.0041   1.0000   0.3673
  -7.750  -0.4338   0.09315   0.08634   0.0063   1.0000   0.3942
  -7.500  -0.4238   0.09007   0.08329   0.0079   1.0000   0.4205
  -6.750  -0.3959   0.08195   0.07530   0.0140   1.0000   0.5142
  -6.500  -0.3632   0.07840   0.07171   0.0153   1.0000   0.5527
  -6.250  -0.3368   0.07553   0.06883   0.0173   1.0000   0.6020
  -6.000  -0.3091   0.07249   0.06579   0.0184   1.0000   0.6486
  -5.500  -0.5326   0.05381   0.04673  -0.0111   1.0000   0.2306
  -5.250  -0.5364   0.04980   0.04213  -0.0093   1.0000   0.2012
  -5.000  -0.5349   0.04679   0.03858  -0.0069   1.0000   0.1873
  -4.750  -0.5275   0.04440   0.03597  -0.0048   1.0000   0.1834
  -4.500  -0.5182   0.04218   0.03341  -0.0029   1.0000   0.1812
  -4.250  -0.5060   0.04009   0.03092  -0.0013   1.0000   0.1797
  -4.000  -0.4905   0.03810   0.02844   0.0001   1.0000   0.1776
  -3.750  -0.4727   0.03636   0.02622   0.0013   1.0000   0.1761
  -3.500  -0.4535   0.03480   0.02440   0.0022   1.0000   0.1771
  -3.250  -0.4335   0.03356   0.02302   0.0029   1.0000   0.1818
  -3.000  -0.4121   0.03248   0.02160   0.0036   1.0000   0.1867
  -2.750  -0.3894   0.03147   0.02024   0.0041   1.0000   0.1904
  -2.500  -0.3668   0.03040   0.01920   0.0044   1.0000   0.1966
  -2.250  -0.3441   0.02973   0.01835   0.0049   1.0000   0.2067
  -2.000  -0.3197   0.02907   0.01770   0.0050   1.0000   0.2184
  -1.750  -0.2872   0.02854   0.01715   0.0037   0.9982   0.2362
  -1.500  -0.1306   0.02518   0.01702  -0.0151   1.0000   1.0000
  -1.250  -0.0843   0.02566   0.01689  -0.0198   0.9897   1.0000
  -1.000  -0.0349   0.02615   0.01698  -0.0252   0.9772   1.0000
  -0.750   0.0122   0.02663   0.01717  -0.0302   0.9646   1.0000
  -0.500   0.0596   0.02710   0.01739  -0.0350   0.9516   1.0000
  -0.250   0.1094   0.02756   0.01765  -0.0402   0.9390   1.0000
   0.000   0.1547   0.02799   0.01793  -0.0445   0.9255   1.0000
   0.250   0.1954   0.02844   0.01826  -0.0478   0.9113   1.0000
   0.500   0.2350   0.02892   0.01865  -0.0508   0.8973   1.0000
   0.750   0.2746   0.02940   0.01906  -0.0538   0.8832   1.0000
   1.000   0.3115   0.02990   0.01950  -0.0560   0.8692   1.0000
   1.250   0.3460   0.03042   0.01999  -0.0578   0.8554   1.0000
   1.500   0.3822   0.03089   0.02042  -0.0596   0.8422   1.0000
   1.750   0.4156   0.03136   0.02089  -0.0608   0.8292   1.0000
   2.000   0.4326   0.03221   0.02172  -0.0595   0.8150   1.0000
   2.250   0.4482   0.03312   0.02262  -0.0580   0.8012   1.0000
   2.500   0.4645   0.03406   0.02356  -0.0567   0.7885   1.0000
   2.750   0.4898   0.03478   0.02430  -0.0565   0.7770   1.0000
   3.000   0.5143   0.03549   0.02503  -0.0561   0.7657   1.0000
   3.250   0.5184   0.03687   0.02641  -0.0532   0.7529   1.0000
   3.500   0.5290   0.03809   0.02765  -0.0512   0.7413   1.0000
   3.750   0.5667   0.03841   0.02803  -0.0521   0.7317   1.0000
   4.000   0.5647   0.04009   0.02972  -0.0488   0.7190   1.0000
   4.250   0.5668   0.04167   0.03132  -0.0459   0.7071   1.0000
   4.500   0.5886   0.04257   0.03228  -0.0450   0.6961   1.0000
   4.750   0.6157   0.04319   0.03298  -0.0444   0.6847   1.0000
   5.000   0.6106   0.04512   0.03492  -0.0410   0.6717   1.0000
   5.250   0.6173   0.04660   0.03644  -0.0386   0.6589   1.0000
   5.500   0.6371   0.04754   0.03747  -0.0373   0.6463   1.0000
   5.750   0.6744   0.04756   0.03763  -0.0371   0.6337   1.0000
   6.000   0.6910   0.04849   0.03866  -0.0353   0.6199   1.0000
   6.250   0.6977   0.04994   0.04017  -0.0329   0.6049   1.0000
   6.500   0.7185   0.05043   0.04078  -0.0310   0.5890   1.0000
   6.750   0.7833   0.04706   0.03766  -0.0299   0.5706   1.0000
   7.000   0.7803   0.04862   0.03928  -0.0263   0.5502   1.0000
   7.250   0.8419   0.04405   0.03493  -0.0239   0.5276   1.0000
   7.500   0.9007   0.03998   0.03102  -0.0221   0.5090   1.0000
   7.750   0.9107   0.04047   0.03165  -0.0190   0.4878   1.0000
   8.000   0.9622   0.03706   0.02832  -0.0172   0.4644   1.0000
   8.250   0.9935   0.03545   0.02670  -0.0146   0.4341   1.0000
   8.500   1.0188   0.03469   0.02581  -0.0118   0.3981   1.0000
   8.750   1.0337   0.03520   0.02625  -0.0087   0.3617   1.0000
   9.000   1.0496   0.03591   0.02685  -0.0060   0.3303   1.0000
   9.250   1.0681   0.03665   0.02743  -0.0038   0.3052   1.0000
   9.500   1.0812   0.03806   0.02889  -0.0015   0.2858   1.0000
   9.750   1.0974   0.03952   0.03039   0.0003   0.2695   1.0000
  10.000   1.1127   0.04102   0.03192   0.0021   0.2541   1.0000
  10.250   1.1269   0.04252   0.03344   0.0040   0.2386   1.0000
  10.500   1.1433   0.04319   0.03383   0.0058   0.2176   1.0000
  10.750   1.1452   0.04466   0.03536   0.0087   0.2001   1.0000
  11.000   1.1490   0.04645   0.03719   0.0114   0.1832   1.0000
  11.250   1.1528   0.04866   0.03945   0.0139   0.1669   1.0000
  11.500   1.1548   0.05130   0.04215   0.0164   0.1522   1.0000
  11.750   1.1541   0.05429   0.04523   0.0189   0.1407   1.0000
  12.000   0.8932   0.08950   0.08179   0.0079   0.2248   1.0000
  12.250   0.8743   0.09748   0.08975   0.0052   0.2208   1.0000
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