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GOE 693 AIRFOIL (goe693-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 693 AIRFOIL (goe693-il)
Reynolds number: 100,000
Max Cl/Cd: 55.66 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe693-il-100000-n5.txt
Download as CSV file: xf-goe693-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 693 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4077   0.09369   0.08841  -0.0468   1.0000   0.0517
  -9.500  -0.4115   0.09038   0.08516  -0.0475   1.0000   0.0526
  -9.250  -0.4207   0.08672   0.08157  -0.0480   1.0000   0.0532
  -9.000  -0.4364   0.08286   0.07780  -0.0482   1.0000   0.0535
  -8.750  -0.4615   0.07911   0.07418  -0.0475   1.0000   0.0534
  -8.500  -0.4944   0.07482   0.07000  -0.0470   1.0000   0.0530
  -8.250  -0.5160   0.06674   0.06189  -0.0524   0.9964   0.0530
  -8.000  -0.5231   0.05190   0.04650  -0.0650   0.9852   0.0535
  -7.750  -0.5154   0.04340   0.03731  -0.0702   0.9761   0.0549
  -7.500  -0.4988   0.03731   0.03036  -0.0732   0.9688   0.0574
  -7.250  -0.4749   0.03329   0.02561  -0.0751   0.9623   0.0589
  -7.000  -0.4439   0.03163   0.02380  -0.0769   0.9575   0.0602
  -6.750  -0.4154   0.03022   0.02219  -0.0779   0.9505   0.0617
  -6.500  -0.3815   0.02882   0.02053  -0.0799   0.9463   0.0642
  -6.250  -0.3534   0.02736   0.01872  -0.0806   0.9391   0.0672
  -6.000  -0.3222   0.02583   0.01684  -0.0817   0.9332   0.0698
  -5.750  -0.2876   0.02490   0.01586  -0.0834   0.9293   0.0721
  -5.500  -0.2618   0.02415   0.01500  -0.0832   0.9202   0.0749
  -5.250  -0.2285   0.02320   0.01382  -0.0844   0.9153   0.0794
  -5.000  -0.2008   0.02257   0.01313  -0.0846   0.9073   0.0837
  -4.750  -0.1694   0.02199   0.01247  -0.0854   0.9012   0.0895
  -4.500  -0.1394   0.02128   0.01162  -0.0858   0.8949   0.0956
  -4.250  -0.1108   0.02081   0.01114  -0.0861   0.8876   0.1025
  -4.000  -0.0780   0.02023   0.01047  -0.0870   0.8830   0.1117
  -3.750  -0.0523   0.01989   0.01010  -0.0867   0.8741   0.1206
  -3.500  -0.0211   0.01941   0.00960  -0.0873   0.8690   0.1305
  -3.250   0.0060   0.01914   0.00923  -0.0872   0.8612   0.1409
  -3.000   0.0355   0.01874   0.00888  -0.0875   0.8553   0.1512
  -2.750   0.0637   0.01842   0.00855  -0.0876   0.8488   0.1619
  -2.500   0.0917   0.01814   0.00826  -0.0876   0.8419   0.1735
  -2.250   0.1224   0.01779   0.00790  -0.0880   0.8373   0.1866
  -2.000   0.1476   0.01758   0.00775  -0.0876   0.8291   0.1995
  -1.750   0.1769   0.01727   0.00749  -0.0878   0.8237   0.2176
  -1.500   0.2038   0.01702   0.00733  -0.0876   0.8170   0.2407
  -1.250   0.2313   0.01673   0.00718  -0.0876   0.8106   0.2772
  -1.000   0.2606   0.01627   0.00697  -0.0878   0.8057   0.3491
  -0.750   0.2836   0.01575   0.00701  -0.0870   0.7973   0.4898
  -0.500   0.3064   0.01492   0.00698  -0.0850   0.7911   0.7248
  -0.250   0.3614   0.01460   0.00698  -0.0893   0.7822   0.9485
   0.000   0.4105   0.01448   0.00667  -0.0933   0.7733   1.0000
   0.250   0.4340   0.01453   0.00659  -0.0923   0.7622   1.0000
   0.500   0.4588   0.01459   0.00653  -0.0916   0.7531   1.0000
   0.750   0.4843   0.01467   0.00649  -0.0910   0.7453   1.0000
   1.000   0.5095   0.01478   0.00652  -0.0904   0.7380   1.0000
   1.250   0.5347   0.01490   0.00655  -0.0898   0.7302   1.0000
   1.500   0.5606   0.01501   0.00659  -0.0893   0.7228   1.0000
   1.750   0.5856   0.01513   0.00665  -0.0887   0.7140   1.0000
   2.000   0.6108   0.01524   0.00670  -0.0881   0.7049   1.0000
   2.250   0.6368   0.01532   0.00671  -0.0875   0.6955   1.0000
   2.500   0.6609   0.01546   0.00683  -0.0867   0.6844   1.0000
   2.750   0.6864   0.01555   0.00687  -0.0860   0.6741   1.0000
   3.000   0.7118   0.01566   0.00694  -0.0854   0.6636   1.0000
   3.250   0.7361   0.01582   0.00711  -0.0846   0.6527   1.0000
   3.500   0.7615   0.01595   0.00723  -0.0840   0.6426   1.0000
   3.750   0.7867   0.01608   0.00734  -0.0834   0.6314   1.0000
   4.000   0.8107   0.01624   0.00752  -0.0825   0.6182   1.0000
   4.250   0.8348   0.01639   0.00769  -0.0817   0.6046   1.0000
   4.500   0.8591   0.01656   0.00786  -0.0810   0.5909   1.0000
   4.750   0.8831   0.01673   0.00805  -0.0801   0.5765   1.0000
   5.000   0.9066   0.01691   0.00824  -0.0792   0.5597   1.0000
   5.250   0.9295   0.01711   0.00842  -0.0782   0.5409   1.0000
   5.500   0.9525   0.01733   0.00861  -0.0771   0.5223   1.0000
   5.750   0.9748   0.01759   0.00885  -0.0760   0.5019   1.0000
   6.000   0.9964   0.01790   0.00912  -0.0748   0.4797   1.0000
   6.500   1.0383   0.01866   0.00975  -0.0723   0.4383   1.0000
   6.750   1.0583   0.01911   0.01016  -0.0709   0.4184   1.0000
   7.000   1.0778   0.01962   0.01060  -0.0695   0.3995   1.0000
   7.250   1.0967   0.02016   0.01108  -0.0681   0.3818   1.0000
   7.500   1.1153   0.02072   0.01162  -0.0666   0.3646   1.0000
   7.750   1.1334   0.02130   0.01221  -0.0651   0.3481   1.0000
   8.000   1.1508   0.02191   0.01282  -0.0635   0.3320   1.0000
   8.250   1.1677   0.02254   0.01346  -0.0618   0.3163   1.0000
   8.500   1.1837   0.02320   0.01414  -0.0601   0.3004   1.0000
   8.750   1.1991   0.02386   0.01486  -0.0582   0.2847   1.0000
   9.000   1.2133   0.02455   0.01563  -0.0562   0.2690   1.0000
   9.250   1.2254   0.02527   0.01639  -0.0539   0.2534   1.0000
   9.500   1.2367   0.02607   0.01722  -0.0516   0.2384   1.0000
   9.750   1.2465   0.02698   0.01812  -0.0492   0.2229   1.0000
  10.000   1.2542   0.02803   0.01913  -0.0467   0.2068   1.0000
  10.250   1.2599   0.02927   0.02031  -0.0442   0.1914   1.0000
  10.500   1.2646   0.03066   0.02162  -0.0418   0.1767   1.0000
  10.750   1.2699   0.03210   0.02305  -0.0397   0.1633   1.0000
  11.000   1.2757   0.03358   0.02453  -0.0377   0.1518   1.0000
  11.250   1.2821   0.03506   0.02608  -0.0360   0.1408   1.0000
  11.500   1.2917   0.03637   0.02755  -0.0346   0.1281   1.0000
  11.750   1.2993   0.03787   0.02914  -0.0333   0.1136   1.0000
  12.000   1.3035   0.03970   0.03100  -0.0319   0.0983   1.0000
  12.250   1.3030   0.04202   0.03326  -0.0305   0.0866   1.0000
  12.500   1.2999   0.04468   0.03589  -0.0291   0.0770   1.0000
  12.750   1.2979   0.04737   0.03865  -0.0279   0.0666   1.0000
  13.000   1.2966   0.05009   0.04145  -0.0269   0.0566   1.0000
  13.250   1.2937   0.05305   0.04447  -0.0261   0.0496   1.0000
  13.500   1.2887   0.05634   0.04780  -0.0255   0.0454   1.0000
  13.750   1.2837   0.05973   0.05128  -0.0251   0.0424   1.0000
  14.000   1.2767   0.06349   0.05512  -0.0249   0.0402   1.0000
  14.250   1.2692   0.06746   0.05918  -0.0250   0.0385   1.0000
  14.500   1.2632   0.07137   0.06326  -0.0253   0.0368   1.0000
  14.750   1.2563   0.07555   0.06757  -0.0258   0.0353   1.0000
  15.000   1.2482   0.08003   0.07217  -0.0266   0.0341   1.0000
  15.250   1.2390   0.08480   0.07704  -0.0277   0.0332   1.0000
  15.500   1.2305   0.08954   0.08187  -0.0288   0.0323   1.0000
  15.750   1.2252   0.09394   0.08644  -0.0299   0.0313   1.0000
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