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S1223 (s1223-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S1223 (s1223-il)
Reynolds number: 500,000
Max Cl/Cd: 97.44 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1223-il-500000-n5.txt
Download as CSV file: xf-s1223-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1223                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250   0.0436   0.11148   0.10895  -0.0851   0.9422   0.0125
  -9.000   0.0483   0.10878   0.10626  -0.0854   0.9340   0.0126
  -8.250   0.0686   0.10056   0.09807  -0.0879   0.9120   0.0127
  -7.750   0.1049   0.09444   0.09193  -0.0922   0.8896   0.0129
  -7.500   0.1606   0.08870   0.08605  -0.1050   0.8698   0.0134
  -7.250   0.2416   0.08095   0.07795  -0.1268   0.8261   0.0154
  -7.000   0.2676   0.07759   0.07406  -0.1336   0.7367   0.0156
  -6.750   0.2651   0.07643   0.07260  -0.1312   0.6753   0.0156
  -6.500   0.2636   0.07513   0.07110  -0.1291   0.6316   0.0156
  -6.250   0.2640   0.07361   0.06945  -0.1275   0.6022   0.0156
  -6.000   0.2642   0.07203   0.06780  -0.1259   0.5789   0.0156
  -5.750   0.2635   0.07043   0.06613  -0.1242   0.5614   0.0156
  -5.500   0.2621   0.06904   0.06470  -0.1220   0.5463   0.0156
  -5.250   0.2601   0.06749   0.06314  -0.1200   0.5343   0.0156
  -5.000   0.2636   0.06555   0.06118  -0.1192   0.5234   0.0156
  -4.500   0.2713   0.06049   0.05607  -0.1182   0.5052   0.0126
  -4.000   0.5776   0.01777   0.01162  -0.2346   0.4835   0.0123
  -3.750   0.6441   0.01604   0.00930  -0.2443   0.4704   0.0129
  -3.500   0.6801   0.01579   0.00893  -0.2463   0.4616   0.0134
  -3.250   0.7163   0.01556   0.00854  -0.2483   0.4530   0.0141
  -3.000   0.7573   0.01511   0.00785  -0.2512   0.4456   0.0151
  -2.750   0.7974   0.01472   0.00722  -0.2538   0.4384   0.0157
  -2.500   0.8359   0.01443   0.00683  -0.2562   0.4313   0.0164
  -2.250   0.8713   0.01427   0.00659  -0.2578   0.4256   0.0172
  -2.000   0.9065   0.01413   0.00636  -0.2593   0.4197   0.0182
  -1.750   0.9414   0.01405   0.00617  -0.2607   0.4136   0.0193
  -1.500   0.9745   0.01402   0.00609  -0.2618   0.4083   0.0209
  -1.250   1.0076   0.01399   0.00598  -0.2628   0.4031   0.0223
  -1.000   1.0417   0.01395   0.00588  -0.2640   0.3980   0.0236
  -0.750   1.0733   0.01401   0.00586  -0.2647   0.3934   0.0252
  -0.500   1.1048   0.01405   0.00585  -0.2653   0.3897   0.0278
  -0.250   1.1355   0.01409   0.00585  -0.2658   0.3861   0.0307
   0.000   1.1665   0.01415   0.00590  -0.2663   0.3824   0.0376
   0.250   1.2030   0.01410   0.00600  -0.2682   0.3782   0.1183
   0.500   1.2343   0.01420   0.00619  -0.2689   0.3742   0.1954
   0.750   1.2630   0.01432   0.00636  -0.2690   0.3713   0.2244
   1.000   1.2912   0.01445   0.00652  -0.2689   0.3686   0.2498
   1.250   1.3189   0.01460   0.00667  -0.2687   0.3658   0.2658
   1.500   1.3462   0.01477   0.00683  -0.2684   0.3629   0.2791
   1.750   1.3733   0.01496   0.00700  -0.2681   0.3598   0.2895
   2.000   1.3999   0.01517   0.00718  -0.2677   0.3569   0.2985
   2.250   1.4267   0.01537   0.00738  -0.2674   0.3544   0.3097
   2.500   1.4539   0.01553   0.00757  -0.2671   0.3526   0.3218
   2.750   1.4808   0.01571   0.00777  -0.2668   0.3506   0.3366
   3.250   1.5340   0.01610   0.00823  -0.2661   0.3462   0.3731
   3.750   1.5862   0.01656   0.00874  -0.2652   0.3414   0.4159
   4.000   1.6120   0.01683   0.00904  -0.2647   0.3391   0.4414
   4.500   1.6647   0.01729   0.00963  -0.2640   0.3358   0.5049
   4.750   1.6915   0.01750   0.00994  -0.2637   0.3342   0.5465
   5.000   1.7182   0.01773   0.01028  -0.2635   0.3323   0.5929
   5.250   1.7449   0.01797   0.01062  -0.2632   0.3300   0.6456
   5.500   1.7715   0.01822   0.01099  -0.2629   0.3278   0.7119
   5.750   1.7968   0.01844   0.01138  -0.2624   0.3256   0.8176
   6.250   1.8326   0.01892   0.01193  -0.2582   0.3207   1.0000
   6.500   1.8563   0.01920   0.01225  -0.2574   0.3187   1.0000
   6.750   1.8799   0.01948   0.01258  -0.2565   0.3163   1.0000
   7.000   1.9028   0.01978   0.01291  -0.2555   0.3134   1.0000
   7.250   1.9251   0.02013   0.01327  -0.2544   0.3103   1.0000
   7.500   1.9467   0.02051   0.01366  -0.2533   0.3076   1.0000
   7.750   1.9679   0.02094   0.01410  -0.2520   0.3051   1.0000
   8.000   1.9893   0.02136   0.01454  -0.2508   0.3026   1.0000
   8.250   2.0117   0.02166   0.01492  -0.2498   0.2997   1.0000
   8.500   2.0330   0.02203   0.01534  -0.2486   0.2962   1.0000
   8.750   2.0530   0.02247   0.01580  -0.2472   0.2919   1.0000
   9.000   2.0719   0.02299   0.01632  -0.2456   0.2883   1.0000
   9.250   2.0924   0.02341   0.01680  -0.2443   0.2843   1.0000
   9.500   2.1121   0.02386   0.01730  -0.2429   0.2785   1.0000
   9.750   2.1285   0.02450   0.01792  -0.2410   0.2720   1.0000
  10.000   2.1478   0.02499   0.01848  -0.2395   0.2664   1.0000
  10.250   2.1652   0.02561   0.01912  -0.2378   0.2603   1.0000
  10.500   2.1814   0.02631   0.01984  -0.2359   0.2551   1.0000
  10.750   2.1977   0.02700   0.02057  -0.2341   0.2477   1.0000
  11.000   2.2117   0.02787   0.02145  -0.2319   0.2409   1.0000
  11.250   2.2261   0.02871   0.02233  -0.2299   0.2334   1.0000
  11.500   2.2379   0.02976   0.02339  -0.2275   0.2256   1.0000
  11.750   2.2488   0.03089   0.02454  -0.2250   0.2161   1.0000
  12.000   2.2586   0.03213   0.02579  -0.2225   0.2072   1.0000
  12.250   2.2639   0.03375   0.02739  -0.2194   0.1954   1.0000
  12.500   2.2680   0.03550   0.02914  -0.2164   0.1853   1.0000
  12.750   2.2723   0.03729   0.03095  -0.2134   0.1754   1.0000
  13.000   2.2750   0.03928   0.03296  -0.2105   0.1671   1.0000
  13.250   2.2750   0.04157   0.03528  -0.2075   0.1587   1.0000
  13.500   2.2765   0.04379   0.03755  -0.2048   0.1515   1.0000
  13.750   2.2735   0.04656   0.04036  -0.2020   0.1446   1.0000
  14.000   2.2721   0.04927   0.04313  -0.1995   0.1378   1.0000
  14.250   2.2659   0.05264   0.04656  -0.1970   0.1320   1.0000
  14.500   2.2614   0.05598   0.04999  -0.1950   0.1260   1.0000
  14.750   2.2525   0.06002   0.05411  -0.1932   0.1210   1.0000
  15.000   2.2438   0.06426   0.05845  -0.1918   0.1163   1.0000
  15.250   2.2313   0.06927   0.06356  -0.1908   0.1112   1.0000
  15.500   2.2156   0.07501   0.06942  -0.1902   0.1074   1.0000
  15.750   2.2020   0.08068   0.07522  -0.1902   0.1038   1.0000
  16.000   2.1834   0.08736   0.08204  -0.1906   0.1003   1.0000
  16.250   2.1607   0.09491   0.08971  -0.1916   0.0973   1.0000
  16.500   2.1422   0.10184   0.09679  -0.1927   0.0947   1.0000
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