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WACO COOTIE AIRFOIL (cootie-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: WACO COOTIE AIRFOIL (cootie-il)
Reynolds number: 100,000
Max Cl/Cd: 62.82 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cootie-il-100000-n5.txt
Download as CSV file: xf-cootie-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WACO COOTIE 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2839   0.10293   0.09834  -0.0325   1.0000   0.0451
  -8.500  -0.2937   0.10180   0.09729  -0.0302   1.0000   0.0464
  -8.250  -0.3026   0.10060   0.09618  -0.0292   0.9981   0.0480
  -8.000  -0.2856   0.09755   0.09313  -0.0414   0.9858   0.0497
  -7.750  -0.2612   0.09337   0.08890  -0.0532   0.9764   0.0500
  -7.500  -0.2497   0.08800   0.08357  -0.0484   0.9747   0.0512
  -7.250  -0.2322   0.08437   0.07992  -0.0499   0.9686   0.0534
  -7.000  -0.1999   0.08090   0.07636  -0.0626   0.9598   0.0602
  -6.750  -0.1688   0.07592   0.07126  -0.0732   0.9524   0.0613
  -6.500  -0.1543   0.07174   0.06710  -0.0717   0.9480   0.0626
  -6.250  -0.1339   0.06829   0.06362  -0.0739   0.9408   0.0646
  -6.000  -0.1034   0.06450   0.05973  -0.0796   0.9358   0.0684
  -5.750  -0.0502   0.06106   0.05579  -0.0946   0.9256   0.0731
  -5.500  -0.0187   0.05660   0.05115  -0.0988   0.9209   0.0731
  -5.250  -0.0108   0.05117   0.04589  -0.0964   0.9134   0.0578
  -5.000   0.0227   0.04709   0.04158  -0.1010   0.9076   0.0560
  -4.500   0.0986   0.03676   0.03023  -0.1106   0.8938   0.0499
  -4.250   0.1293   0.03375   0.02689  -0.1124   0.8872   0.0499
  -4.000   0.1557   0.03231   0.02539  -0.1132   0.8794   0.0519
  -3.750   0.1854   0.03047   0.02329  -0.1142   0.8722   0.0534
  -3.500   0.2169   0.02771   0.02006  -0.1153   0.8646   0.0525
  -3.250   0.2477   0.02546   0.01736  -0.1160   0.8572   0.0523
  -3.000   0.2775   0.02376   0.01529  -0.1164   0.8493   0.0526
  -2.750   0.3062   0.02244   0.01366  -0.1165   0.8408   0.0532
  -2.500   0.3358   0.02132   0.01226  -0.1166   0.8331   0.0543
  -2.250   0.3630   0.02061   0.01136  -0.1163   0.8234   0.0574
  -2.000   0.3925   0.01966   0.01012  -0.1163   0.8160   0.0599
  -1.750   0.4193   0.01888   0.00921  -0.1158   0.8057   0.0610
  -1.500   0.4463   0.01836   0.00866  -0.1155   0.7960   0.0629
  -1.250   0.4743   0.01786   0.00810  -0.1152   0.7868   0.0657
  -1.000   0.5004   0.01742   0.00760  -0.1146   0.7741   0.0701
  -0.750   0.5267   0.01705   0.00720  -0.1140   0.7615   0.0769
  -0.500   0.5532   0.01677   0.00687  -0.1134   0.7495   0.0906
  -0.250   0.5801   0.01660   0.00662  -0.1130   0.7385   0.1095
   0.000   0.6074   0.01648   0.00644  -0.1127   0.7279   0.1308
   0.250   0.6341   0.01637   0.00633  -0.1125   0.7164   0.1520
   0.500   0.6612   0.01627   0.00618  -0.1122   0.7058   0.1632
   0.750   0.6886   0.01613   0.00604  -0.1120   0.6957   0.1856
   1.000   0.7157   0.01588   0.00602  -0.1120   0.6850   0.2462
   1.500   0.7667   0.01460   0.00596  -0.1106   0.6643   1.0000
   1.750   0.7937   0.01475   0.00596  -0.1102   0.6541   1.0000
   2.000   0.8202   0.01494   0.00605  -0.1099   0.6430   1.0000
   2.250   0.8467   0.01514   0.00614  -0.1096   0.6323   1.0000
   2.500   0.8735   0.01533   0.00623  -0.1093   0.6223   1.0000
   2.750   0.8996   0.01557   0.00643  -0.1090   0.6111   1.0000
   3.000   0.9256   0.01581   0.00663  -0.1087   0.5998   1.0000
   3.250   0.9517   0.01606   0.00683  -0.1084   0.5889   1.0000
   3.500   0.9777   0.01632   0.00705  -0.1080   0.5780   1.0000
   3.750   1.0030   0.01659   0.00735  -0.1077   0.5659   1.0000
   4.000   1.0283   0.01687   0.00765  -0.1073   0.5539   1.0000
   4.250   1.0536   0.01715   0.00796  -0.1069   0.5419   1.0000
   4.500   1.0787   0.01744   0.00826  -0.1065   0.5301   1.0000
   4.750   1.1035   0.01774   0.00858  -0.1060   0.5178   1.0000
   5.000   1.1277   0.01805   0.00895  -0.1054   0.5036   1.0000
   5.250   1.1515   0.01837   0.00930  -0.1048   0.4889   1.0000
   5.500   1.1750   0.01871   0.00968  -0.1041   0.4743   1.0000
   5.750   1.1980   0.01907   0.01007  -0.1034   0.4594   1.0000
   6.000   1.2206   0.01946   0.01052  -0.1026   0.4442   1.0000
   6.250   1.2426   0.01988   0.01096  -0.1017   0.4286   1.0000
   6.500   1.2628   0.02033   0.01143  -0.1005   0.4078   1.0000
   6.750   1.2812   0.02086   0.01190  -0.0991   0.3844   1.0000
   7.000   1.2994   0.02142   0.01247  -0.0977   0.3617   1.0000
   7.250   1.3167   0.02207   0.01312  -0.0962   0.3400   1.0000
   7.500   1.3319   0.02279   0.01381  -0.0944   0.3126   1.0000
   7.750   1.3451   0.02364   0.01459  -0.0924   0.2804   1.0000
   8.000   1.3581   0.02452   0.01543  -0.0905   0.2452   1.0000
   8.250   1.3684   0.02559   0.01639  -0.0882   0.2056   1.0000
   8.500   1.3687   0.02729   0.01773  -0.0847   0.1541   1.0000
   9.000   1.3600   0.03156   0.02143  -0.0772   0.0749   1.0000
   9.250   1.3602   0.03354   0.02333  -0.0744   0.0450   1.0000
   9.750   1.3595   0.03783   0.02759  -0.0695   0.0280   1.0000
  10.000   1.3593   0.04010   0.02996  -0.0675   0.0258   1.0000
  10.250   1.3577   0.04259   0.03257  -0.0656   0.0242   1.0000
  10.500   1.3570   0.04511   0.03528  -0.0640   0.0230   1.0000
  10.750   1.3550   0.04786   0.03822  -0.0627   0.0219   1.0000
  11.000   1.3514   0.05089   0.04144  -0.0616   0.0210   1.0000
  11.250   1.3468   0.05417   0.04489  -0.0607   0.0204   1.0000
  11.500   1.3414   0.05767   0.04861  -0.0601   0.0199   1.0000
  11.750   1.3353   0.06138   0.05250  -0.0597   0.0196   1.0000
  12.000   1.3286   0.06528   0.05656  -0.0595   0.0192   1.0000
  12.250   1.3216   0.06928   0.06071  -0.0594   0.0189   1.0000
  12.500   1.3152   0.07328   0.06486  -0.0594   0.0186   1.0000
  12.750   1.3098   0.07717   0.06888  -0.0593   0.0183   1.0000
  13.000   1.3058   0.08078   0.07259  -0.0590   0.0180   1.0000
  13.250   1.3055   0.08393   0.07585  -0.0585   0.0176   1.0000
  13.500   1.3066   0.08706   0.07914  -0.0584   0.0172   1.0000
  13.750   1.3078   0.09023   0.08248  -0.0583   0.0168   1.0000
  14.000   1.3087   0.09347   0.08588  -0.0583   0.0163   1.0000
  14.250   1.3093   0.09680   0.08938  -0.0583   0.0159   1.0000
  14.500   1.3099   0.10019   0.09294  -0.0584   0.0156   1.0000
  14.750   1.3101   0.10376   0.09673  -0.0587   0.0154   1.0000
  15.000   1.3087   0.10769   0.10086  -0.0593   0.0152   1.0000
  15.250   1.3058   0.11197   0.10534  -0.0603   0.0151   1.0000
  15.500   1.3013   0.11669   0.11028  -0.0618   0.0150   1.0000
  15.750   1.2951   0.12189   0.11569  -0.0637   0.0149   1.0000
  16.000   1.2875   0.12754   0.12156  -0.0663   0.0149   1.0000
  16.250   1.2785   0.13373   0.12797  -0.0694   0.0149   1.0000
  16.500   1.2682   0.14047   0.13493  -0.0731   0.0149   1.0000
  16.750   1.2565   0.14781   0.14249  -0.0775   0.0149   1.0000
  17.000   1.2436   0.15589   0.15077  -0.0825   0.0150   1.0000
  17.250   1.2293   0.16485   0.15994  -0.0884   0.0151   1.0000
  17.500   1.2134   0.17502   0.17028  -0.0951   0.0153   1.0000
  17.750   1.1956   0.18683   0.18224  -0.1029   0.0156   1.0000
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