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GOE 7K AIRFOIL (goe07k-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 7K AIRFOIL (goe07k-il)
Reynolds number: 100,000
Max Cl/Cd: 38.69 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe07k-il-100000.txt
Download as CSV file: xf-goe07k-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 7K 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.5262   0.11180   0.10758  -0.0210   1.0000   0.0744
  -7.250  -0.5492   0.11005   0.10590  -0.0200   1.0000   0.0749
  -7.000  -0.5636   0.10742   0.10328  -0.0212   1.0000   0.0753
  -6.750  -0.5761   0.10443   0.10024  -0.0242   1.0000   0.0758
  -6.500  -0.5854   0.10136   0.09700  -0.0269   1.0000   0.0762
  -6.250  -0.5790   0.09582   0.09170  -0.0208   1.0000   0.0779
  -6.000  -0.5769   0.09292   0.08882  -0.0180   1.0000   0.0798
  -5.750  -0.5762   0.08984   0.08573  -0.0170   1.0000   0.0823
  -5.500  -0.5749   0.08623   0.08206  -0.0177   1.0000   0.0858
  -5.250  -0.5701   0.08261   0.07786  -0.0248   1.0000   0.0908
  -5.000  -0.5666   0.07741   0.07293  -0.0216   1.0000   0.0926
  -4.750  -0.5607   0.07461   0.07016  -0.0194   1.0000   0.0953
  -4.500  -0.5513   0.07153   0.06694  -0.0194   1.0000   0.1016
  -4.250  -0.5416   0.06732   0.06250  -0.0203   1.0000   0.1079
  -4.000  -0.5322   0.06496   0.06011  -0.0186   1.0000   0.1153
  -3.750  -0.5215   0.06170   0.05667  -0.0183   1.0000   0.1247
  -3.500  -0.5104   0.05901   0.05383  -0.0175   1.0000   0.1387
  -3.250  -0.4983   0.05665   0.05129  -0.0165   1.0000   0.1526
  -3.000  -0.4867   0.05437   0.04893  -0.0151   1.0000   0.1679
  -2.750  -0.4751   0.05228   0.04679  -0.0133   1.0000   0.1850
  -2.500  -0.4640   0.05038   0.04479  -0.0115   1.0000   0.2124
  -1.750  -0.3894   0.03975   0.03195  -0.0074   1.0000   0.1180
  -1.500  -0.3648   0.03699   0.02808  -0.0040   1.0000   0.0910
  -1.250  -0.3460   0.03514   0.02599  -0.0023   1.0000   0.0892
  -1.000  -0.3274   0.03368   0.02422  -0.0006   1.0000   0.0928
  -0.750  -0.3070   0.03262   0.02289   0.0009   1.0000   0.0935
  -0.500  -0.2863   0.03182   0.02194   0.0021   1.0000   0.0962
  -0.250  -0.2610   0.03162   0.02153   0.0025   0.9988   0.1033
   0.000  -0.2324   0.03141   0.02120   0.0022   0.9968   0.1080
   0.250  -0.2035   0.03182   0.02157   0.0018   0.9948   0.1189
   0.500  -0.1810   0.03150   0.02136   0.0023   0.9933   0.1263
   0.750  -0.1537   0.03176   0.02163   0.0019   0.9900   0.1385
   1.000  -0.1226   0.03254   0.02246   0.0007   0.9869   0.1578
   1.250   0.0260   0.03365   0.02584  -0.0264   0.9946   1.0000
   1.500   0.0527   0.03436   0.02636  -0.0274   0.9897   1.0000
   1.750   0.0877   0.03601   0.02783  -0.0299   0.9852   1.0000
   2.000   0.1130   0.03645   0.02815  -0.0307   0.9778   1.0000
   2.250   0.1409   0.03748   0.02909  -0.0320   0.9720   1.0000
   2.500   0.1792   0.03889   0.03039  -0.0352   0.9623   1.0000
   2.750   0.2523   0.03881   0.03020  -0.0436   0.9171   1.0000
   3.000   0.2939   0.03930   0.03063  -0.0466   0.9016   1.0000
   3.250   0.3263   0.03972   0.03103  -0.0480   0.8889   1.0000
   3.500   0.3569   0.04017   0.03147  -0.0491   0.8775   1.0000
   3.750   0.3940   0.04073   0.03204  -0.0512   0.8681   1.0000
   4.000   0.4253   0.04114   0.03248  -0.0523   0.8582   1.0000
   4.250   0.4494   0.04149   0.03287  -0.0522   0.8468   1.0000
   4.500   0.4774   0.04192   0.03335  -0.0528   0.8366   1.0000
   4.750   0.5178   0.04233   0.03382  -0.0553   0.8295   1.0000
   5.000   0.5397   0.04266   0.03424  -0.0548   0.8177   1.0000
   5.250   0.5647   0.04302   0.03470  -0.0548   0.8067   1.0000
   5.500   0.6119   0.04303   0.03482  -0.0580   0.8004   1.0000
   5.750   0.6471   0.04260   0.03455  -0.0588   0.7875   1.0000
   6.000   0.6862   0.04176   0.03386  -0.0598   0.7739   1.0000
   6.250   0.7266   0.04063   0.03290  -0.0608   0.7604   1.0000
   6.500   0.7771   0.03848   0.03101  -0.0623   0.7464   1.0000
   6.750   0.8238   0.03625   0.02903  -0.0631   0.7325   1.0000
   7.000   0.8815   0.03259   0.02571  -0.0643   0.7175   1.0000
   7.250   0.9182   0.02917   0.02254  -0.0617   0.6915   1.0000
   7.500   0.9358   0.02732   0.02086  -0.0572   0.6515   1.0000
   7.750   0.9635   0.02490   0.01615  -0.0511   0.2758   1.0000
   8.000   0.9477   0.02780   0.01785  -0.0448   0.1470   1.0000
   8.250   0.9475   0.02973   0.01939  -0.0407   0.1135   1.0000
   8.500   0.9528   0.03140   0.02098  -0.0373   0.0978   1.0000
   8.750   0.9652   0.03303   0.02247  -0.0350   0.0849   1.0000
   9.000   0.9917   0.03443   0.02381  -0.0346   0.0759   1.0000
   9.250   1.0432   0.03637   0.02579  -0.0377   0.0671   1.0000
   9.500   1.1430   0.04120   0.03077  -0.0492   0.0594   1.0000
   9.750   1.1685   0.04350   0.03354  -0.0485   0.0571   1.0000
  10.000   1.1891   0.04607   0.03652  -0.0473   0.0547   1.0000
  10.250   1.2105   0.04971   0.04065  -0.0461   0.0548   1.0000
  10.500   1.2208   0.05351   0.04491  -0.0433   0.0557   1.0000
  10.750   1.2247   0.05746   0.04926  -0.0397   0.0571   1.0000
  11.000   1.2323   0.06260   0.05474  -0.0376   0.0591   1.0000
  11.250   1.2482   0.06712   0.05952  -0.0362   0.0614   1.0000
  11.500   1.1867   0.06822   0.06139  -0.0221   0.0678   1.0000
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