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S1223 (s1223-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S1223 (s1223-il)
Reynolds number: 1,000,000
Max Cl/Cd: 120 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1223-il-1000000-n5.txt
Download as CSV file: xf-s1223-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500   0.2171   0.08935   0.08587  -0.1305   0.6425   0.0098
  -8.250   0.2211   0.08676   0.08312  -0.1311   0.6075   0.0099
  -8.000   0.2287   0.08476   0.08101  -0.1311   0.5785   0.0099
  -7.750   0.2358   0.08273   0.07889  -0.1313   0.5578   0.0099
  -7.500   0.2427   0.08069   0.07679  -0.1315   0.5408   0.0099
  -7.250   0.2489   0.07865   0.07470  -0.1315   0.5275   0.0099
  -7.000   0.2549   0.07668   0.07271  -0.1312   0.5166   0.0099
  -6.750   0.2605   0.07482   0.07082  -0.1307   0.5062   0.0099
  -5.750   0.3867   0.01674   0.01177  -0.2348   0.4926   0.0088
  -5.500   0.4539   0.01482   0.00938  -0.2456   0.4791   0.0092
  -5.250   0.5022   0.01397   0.00822  -0.2508   0.4670   0.0096
  -5.000   0.5450   0.01341   0.00744  -0.2544   0.4566   0.0098
  -4.750   0.5837   0.01307   0.00691  -0.2570   0.4472   0.0099
  -4.500   0.6249   0.01263   0.00634  -0.2601   0.4397   0.0103
  -4.250   0.6595   0.01249   0.00609  -0.2615   0.4319   0.0106
  -4.000   0.6931   0.01237   0.00589  -0.2627   0.4258   0.0109
  -3.750   0.7271   0.01224   0.00568  -0.2639   0.4195   0.0113
  -3.500   0.7611   0.01214   0.00547  -0.2651   0.4128   0.0118
  -3.250   0.7940   0.01207   0.00531  -0.2661   0.4077   0.0124
  -3.000   0.8275   0.01197   0.00514  -0.2672   0.4025   0.0130
  -2.750   0.8593   0.01195   0.00507  -0.2679   0.3968   0.0136
  -2.500   0.8911   0.01195   0.00500  -0.2686   0.3910   0.0142
  -2.250   0.9234   0.01190   0.00489  -0.2694   0.3866   0.0150
  -2.000   0.9549   0.01190   0.00482  -0.2700   0.3820   0.0156
  -1.750   0.9880   0.01186   0.00473  -0.2710   0.3774   0.0164
  -1.500   1.0189   0.01189   0.00471  -0.2715   0.3729   0.0173
  -1.250   1.0493   0.01191   0.00469  -0.2719   0.3702   0.0185
  -1.000   1.0805   0.01191   0.00466  -0.2724   0.3670   0.0195
  -0.750   1.1112   0.01194   0.00465  -0.2729   0.3633   0.0206
  -0.500   1.1409   0.01201   0.00467  -0.2731   0.3593   0.0218
   0.000   1.2001   0.01215   0.00475  -0.2735   0.3532   0.0260
   0.250   1.2301   0.01219   0.00481  -0.2737   0.3510   0.0342
   0.500   1.2637   0.01217   0.00490  -0.2749   0.3484   0.0967
   0.750   1.2971   0.01217   0.00506  -0.2761   0.3454   0.1844
   1.000   1.3255   0.01229   0.00520  -0.2761   0.3425   0.2112
   1.250   1.3534   0.01243   0.00535  -0.2760   0.3397   0.2312
   1.500   1.3808   0.01257   0.00549  -0.2757   0.3373   0.2423
   1.750   1.4082   0.01268   0.00561  -0.2755   0.3361   0.2549
   2.000   1.4357   0.01280   0.00576  -0.2752   0.3347   0.2681
   2.250   1.4625   0.01294   0.00589  -0.2748   0.3329   0.2754
   2.500   1.4895   0.01308   0.00605  -0.2745   0.3310   0.2855
   2.750   1.5159   0.01323   0.00621  -0.2741   0.3289   0.2951
   3.000   1.5425   0.01340   0.00639  -0.2737   0.3268   0.3075
   3.250   1.5687   0.01358   0.00658  -0.2733   0.3248   0.3209
   3.500   1.5949   0.01376   0.00678  -0.2728   0.3228   0.3373
   3.750   1.6208   0.01397   0.00701  -0.2723   0.3206   0.3543
   4.000   1.6470   0.01413   0.00721  -0.2719   0.3196   0.3724
   4.250   1.6734   0.01428   0.00741  -0.2715   0.3184   0.3921
   4.500   1.6996   0.01444   0.00762  -0.2711   0.3169   0.4137
   4.750   1.7258   0.01461   0.00785  -0.2706   0.3152   0.4379
   5.000   1.7517   0.01480   0.00808  -0.2702   0.3132   0.4647
   5.250   1.7776   0.01500   0.00834  -0.2698   0.3107   0.4960
   5.500   1.8035   0.01523   0.00861  -0.2694   0.3080   0.5356
   5.750   1.8290   0.01549   0.00893  -0.2689   0.3048   0.5757
   6.000   1.8549   0.01570   0.00921  -0.2685   0.3024   0.6192
   6.250   1.8815   0.01587   0.00949  -0.2682   0.3002   0.6717
   6.500   1.9083   0.01607   0.00981  -0.2680   0.2978   0.7400
   6.750   1.9284   0.01607   0.01008  -0.2663   0.2956   0.9917
   7.250   1.9746   0.01667   0.01067  -0.2644   0.2893   1.0000
   7.500   1.9973   0.01697   0.01099  -0.2634   0.2859   1.0000
   7.750   2.0203   0.01725   0.01128  -0.2624   0.2825   1.0000
   8.000   2.0427   0.01756   0.01160  -0.2614   0.2785   1.0000
   8.250   2.0640   0.01797   0.01198  -0.2602   0.2728   1.0000
   8.500   2.0859   0.01832   0.01233  -0.2591   0.2667   1.0000
   8.750   2.1062   0.01881   0.01278  -0.2577   0.2576   1.0000
   9.000   2.1271   0.01923   0.01320  -0.2564   0.2510   1.0000
   9.250   2.1463   0.01977   0.01371  -0.2549   0.2434   1.0000
   9.500   2.1659   0.02026   0.01420  -0.2534   0.2373   1.0000
   9.750   2.1841   0.02086   0.01478  -0.2517   0.2296   1.0000
  10.000   2.2023   0.02145   0.01537  -0.2500   0.2224   1.0000
  10.250   2.2185   0.02221   0.01609  -0.2480   0.2130   1.0000
  10.500   2.2334   0.02305   0.01689  -0.2458   0.2015   1.0000
  10.750   2.2462   0.02406   0.01785  -0.2434   0.1887   1.0000
  11.000   2.2598   0.02498   0.01875  -0.2410   0.1797   1.0000
  11.250   2.2706   0.02612   0.01985  -0.2383   0.1691   1.0000
  11.500   2.2814   0.02725   0.02097  -0.2356   0.1598   1.0000
  11.750   2.2920   0.02838   0.02209  -0.2330   0.1517   1.0000
  12.000   2.3007   0.02969   0.02339  -0.2301   0.1438   1.0000
  12.250   2.3093   0.03099   0.02469  -0.2273   0.1362   1.0000
  12.500   2.3160   0.03246   0.02617  -0.2243   0.1290   1.0000
  12.750   2.3212   0.03407   0.02779  -0.2213   0.1217   1.0000
  13.000   2.3268   0.03568   0.02942  -0.2184   0.1155   1.0000
  13.250   2.3294   0.03761   0.03136  -0.2153   0.1090   1.0000
  13.500   2.3343   0.03937   0.03317  -0.2126   0.1043   1.0000
  13.750   2.3353   0.04156   0.03539  -0.2097   0.0987   1.0000
  14.000   2.3371   0.04374   0.03762  -0.2070   0.0946   1.0000
  14.250   2.3378   0.04611   0.04003  -0.2045   0.0905   1.0000
  14.500   2.3344   0.04901   0.04298  -0.2019   0.0864   1.0000
  14.750   2.3336   0.05175   0.04580  -0.1997   0.0832   1.0000
  15.000   2.3287   0.05510   0.04921  -0.1976   0.0796   1.0000
  15.250   2.3188   0.05923   0.05342  -0.1957   0.0751   1.0000
  15.500   2.3082   0.06370   0.05797  -0.1941   0.0710   1.0000
  15.750   2.2984   0.06830   0.06266  -0.1931   0.0689   1.0000
  16.000   2.2864   0.07347   0.06794  -0.1925   0.0669   1.0000
  16.250   2.2719   0.07925   0.07384  -0.1923   0.0642   1.0000
  16.500   2.2570   0.08529   0.08001  -0.1925   0.0628   1.0000
  16.750   2.2372   0.09231   0.08716  -0.1933   0.0611   1.0000
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