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WACO COOTIE AIRFOIL (cootie-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: WACO COOTIE AIRFOIL (cootie-il)
Reynolds number: 200,000
Max Cl/Cd: 83.43 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cootie-il-200000-n5.txt
Download as CSV file: xf-cootie-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2907   0.10887   0.10544  -0.0369   1.0000   0.0226
  -9.500  -0.2929   0.10652   0.10315  -0.0374   1.0000   0.0227
  -9.250  -0.2883   0.10333   0.10000  -0.0399   0.9956   0.0227
  -8.750  -0.2587   0.09461   0.09128  -0.0430   0.9841   0.0236
  -8.500  -0.2436   0.09113   0.08780  -0.0459   0.9759   0.0242
  -8.250  -0.2297   0.08763   0.08429  -0.0494   0.9658   0.0247
  -8.000  -0.2164   0.08396   0.08062  -0.0533   0.9552   0.0250
  -7.750  -0.1929   0.08029   0.07691  -0.0654   0.9425   0.0298
  -7.500  -0.1706   0.07569   0.07225  -0.0728   0.9342   0.0300
  -7.250  -0.1521   0.07137   0.06788  -0.0772   0.9254   0.0300
  -7.000  -0.1428   0.06798   0.06446  -0.0754   0.9197   0.0289
  -6.750  -0.1259   0.06414   0.06058  -0.0786   0.9110   0.0277
  -6.500  -0.0906   0.05734   0.05358  -0.0909   0.9029   0.0305
  -6.250  -0.0746   0.05762   0.05386  -0.0894   0.8955   0.0387
  -6.000  -0.0578   0.05372   0.04990  -0.0908   0.8890   0.0344
  -5.750  -0.0224   0.04569   0.04156  -0.1001   0.8811   0.0313
  -5.500  -0.0025   0.04508   0.04092  -0.0998   0.8748   0.0339
  -5.250   0.0257   0.04154   0.03720  -0.1031   0.8671   0.0352
  -4.750   0.0856   0.03343   0.02851  -0.1089   0.8533   0.0350
  -4.500   0.1156   0.02998   0.02470  -0.1107   0.8471   0.0366
  -4.250   0.1450   0.02648   0.02082  -0.1120   0.8394   0.0365
  -4.000   0.1745   0.02304   0.01689  -0.1130   0.8328   0.0367
  -3.750   0.2036   0.02015   0.01349  -0.1136   0.8251   0.0378
  -3.500   0.2321   0.01831   0.01118  -0.1138   0.8179   0.0385
  -3.250   0.2601   0.01694   0.00947  -0.1138   0.8092   0.0386
  -3.000   0.2881   0.01593   0.00817  -0.1137   0.8016   0.0388
  -2.750   0.3158   0.01515   0.00720  -0.1136   0.7917   0.0392
  -2.500   0.3434   0.01453   0.00641  -0.1135   0.7826   0.0395
  -2.250   0.3709   0.01391   0.00566  -0.1133   0.7722   0.0401
  -2.000   0.3980   0.01340   0.00505  -0.1130   0.7587   0.0410
  -1.750   0.4250   0.01303   0.00460  -0.1127   0.7436   0.0424
  -1.500   0.4521   0.01278   0.00427  -0.1125   0.7284   0.0447
  -1.000   0.5070   0.01238   0.00372  -0.1121   0.7024   0.0475
  -0.750   0.5345   0.01224   0.00351  -0.1120   0.6902   0.0491
  -0.500   0.5620   0.01215   0.00338  -0.1119   0.6787   0.0528
  -0.250   0.5894   0.01211   0.00334  -0.1117   0.6675   0.0635
   0.000   0.6168   0.01214   0.00334  -0.1116   0.6565   0.0837
   0.250   0.6442   0.01220   0.00335  -0.1115   0.6465   0.0970
   0.500   0.6715   0.01227   0.00335  -0.1114   0.6369   0.1056
   0.750   0.6987   0.01235   0.00338  -0.1113   0.6269   0.1153
   1.000   0.7259   0.01240   0.00343  -0.1112   0.6174   0.1255
   1.250   0.7531   0.01246   0.00347  -0.1112   0.6086   0.1353
   1.500   0.7803   0.01249   0.00354  -0.1112   0.5994   0.1504
   1.750   0.8072   0.01249   0.00361  -0.1111   0.5904   0.1793
   2.250   0.8563   0.01117   0.00384  -0.1098   0.5714   1.0000
   2.500   0.8830   0.01136   0.00395  -0.1097   0.5621   1.0000
   2.750   0.9099   0.01153   0.00409  -0.1096   0.5519   1.0000
   3.000   0.9364   0.01171   0.00423  -0.1094   0.5413   1.0000
   3.250   0.9627   0.01190   0.00439  -0.1092   0.5302   1.0000
   3.500   0.9887   0.01211   0.00455  -0.1090   0.5172   1.0000
   3.750   1.0144   0.01232   0.00473  -0.1087   0.5026   1.0000
   4.000   1.0397   0.01255   0.00492  -0.1083   0.4870   1.0000
   4.250   1.0649   0.01280   0.00515  -0.1080   0.4715   1.0000
   4.500   1.0900   0.01307   0.00539  -0.1076   0.4571   1.0000
   4.750   1.1146   0.01336   0.00565  -0.1072   0.4412   1.0000
   5.000   1.1386   0.01369   0.00596  -0.1067   0.4228   1.0000
   5.250   1.1619   0.01407   0.00627  -0.1061   0.4036   1.0000
   5.500   1.1841   0.01452   0.00663  -0.1053   0.3815   1.0000
   5.750   1.2057   0.01500   0.00702  -0.1045   0.3576   1.0000
   6.000   1.2272   0.01550   0.00746  -0.1036   0.3368   1.0000
   6.250   1.2489   0.01598   0.00791  -0.1028   0.3169   1.0000
   6.500   1.2701   0.01649   0.00838  -0.1020   0.2974   1.0000
   6.750   1.2890   0.01714   0.00891  -0.1008   0.2658   1.0000
   7.000   1.3045   0.01804   0.00959  -0.0992   0.2143   1.0000
   7.250   1.3122   0.01959   0.01066  -0.0966   0.1439   1.0000
   7.500   1.3162   0.02142   0.01204  -0.0936   0.0826   1.0000
   7.750   1.3291   0.02244   0.01300  -0.0916   0.0618   1.0000
   8.000   1.3313   0.02403   0.01433  -0.0881   0.0237   1.0000
   8.250   1.3392   0.02517   0.01550  -0.0853   0.0202   1.0000
   8.500   1.3480   0.02630   0.01673  -0.0828   0.0177   1.0000
   8.750   1.3583   0.02738   0.01798  -0.0807   0.0165   1.0000
   9.000   1.3670   0.02861   0.01936  -0.0786   0.0155   1.0000
   9.250   1.3743   0.02999   0.02090  -0.0765   0.0148   1.0000
   9.500   1.3801   0.03157   0.02262  -0.0744   0.0142   1.0000
   9.750   1.3841   0.03335   0.02455  -0.0723   0.0137   1.0000
  10.000   1.3856   0.03542   0.02678  -0.0703   0.0132   1.0000
  10.250   1.3836   0.03791   0.02942  -0.0683   0.0126   1.0000
  10.500   1.3773   0.04093   0.03259  -0.0664   0.0121   1.0000
  10.750   1.3783   0.04335   0.03512  -0.0651   0.0118   1.0000
  11.000   1.3807   0.04570   0.03764  -0.0640   0.0114   1.0000
  11.250   1.3805   0.04840   0.04047  -0.0630   0.0111   1.0000
  11.500   1.3793   0.05131   0.04350  -0.0621   0.0109   1.0000
  11.750   1.3778   0.05430   0.04662  -0.0614   0.0106   1.0000
  12.000   1.3761   0.05738   0.04982  -0.0607   0.0104   1.0000
  12.250   1.3747   0.06049   0.05304  -0.0601   0.0102   1.0000
  12.500   1.3736   0.06360   0.05627  -0.0596   0.0100   1.0000
  12.750   1.3730   0.06670   0.05947  -0.0591   0.0099   1.0000
  13.000   1.3728   0.06978   0.06267  -0.0586   0.0097   1.0000
  13.250   1.3730   0.07285   0.06584  -0.0582   0.0095   1.0000
  13.500   1.3734   0.07594   0.06904  -0.0579   0.0093   1.0000
  13.750   1.3736   0.07907   0.07230  -0.0576   0.0091   1.0000
  14.000   1.3735   0.08227   0.07559  -0.0575   0.0089   1.0000
  14.250   1.3736   0.08542   0.07879  -0.0573   0.0086   1.0000
  14.500   1.3763   0.08799   0.08140  -0.0559   0.0083   1.0000
  14.750   1.3724   0.09210   0.08571  -0.0568   0.0081   1.0000
  15.000   1.3681   0.09638   0.09020  -0.0579   0.0080   1.0000
  15.250   1.3638   0.10073   0.09474  -0.0590   0.0079   1.0000
  15.500   1.3589   0.10526   0.09948  -0.0603   0.0078   1.0000
  15.750   1.3528   0.11008   0.10449  -0.0618   0.0077   1.0000
  16.000   1.3458   0.11519   0.10980  -0.0637   0.0077   1.0000
  16.250   1.3379   0.12063   0.11544  -0.0659   0.0076   1.0000
  16.500   1.3292   0.12641   0.12142  -0.0686   0.0076   1.0000
  16.750   1.3200   0.13248   0.12768  -0.0717   0.0075   1.0000
  17.000   1.3103   0.13889   0.13429  -0.0752   0.0075   1.0000
  17.250   1.3000   0.14566   0.14125  -0.0791   0.0075   1.0000
  17.500   1.2892   0.15278   0.14855  -0.0834   0.0075   1.0000
  17.750   1.2784   0.16020   0.15615  -0.0881   0.0075   1.0000
  18.000   1.2671   0.16815   0.16427  -0.0933   0.0076   1.0000
  18.250   1.2556   0.17653   0.17281  -0.0988   0.0076   1.0000
  18.500   1.2437   0.18552   0.18195  -0.1049   0.0076   1.0000
  18.750   1.2320   0.19507   0.19164  -0.1113   0.0077   1.0000
  19.000   1.2195   0.20576   0.20245  -0.1183   0.0078   1.0000
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