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S1223 (s1223-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S1223 (s1223-il)
Reynolds number: 500,000
Max Cl/Cd: 98.85 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1223-il-500000.txt
Download as CSV file: xf-s1223-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250   0.1102   0.09424   0.09192  -0.0898   0.9418   0.0171
  -7.000   0.1307   0.09089   0.08857  -0.0936   0.9397   0.0176
  -6.750   0.1353   0.08865   0.08636  -0.0931   0.9307   0.0179
  -6.500   0.2154   0.06577   0.06359  -0.0983   0.8856   0.0193
  -6.250   0.2372   0.06215   0.05994  -0.1016   0.8715   0.0196
  -6.000   0.1502   0.08059   0.07832  -0.0979   0.9033   0.0189
  -5.750   0.1624   0.07791   0.07565  -0.0969   0.8924   0.0191
  -5.500   0.1830   0.07507   0.07280  -0.0988   0.8812   0.0193
  -5.250   0.2136   0.07167   0.06935  -0.1039   0.8662   0.0197
  -5.000   0.2652   0.06686   0.06438  -0.1153   0.8393   0.0203
  -4.750   0.3237   0.06171   0.05885  -0.1292   0.7801   0.0214
  -4.500   0.3306   0.05955   0.05633  -0.1301   0.7119   0.0220
  -4.250   0.3303   0.05680   0.05335  -0.1316   0.6643   0.0224
  -3.750   0.3379   0.05285   0.04910  -0.1305   0.5962   0.0228
  -3.500   0.3471   0.05148   0.04761  -0.1299   0.5719   0.0230
  -3.250   0.3608   0.04986   0.04590  -0.1305   0.5533   0.0234
  -3.000   0.4487   0.03815   0.03399  -0.1613   0.5391   0.0265
  -2.750   0.4581   0.03829   0.03407  -0.1581   0.5251   0.0268
  -2.500   0.4860   0.03691   0.03260  -0.1608   0.5121   0.0274
  -2.250   0.8394   0.01585   0.00887  -0.2507   0.4852   0.0263
  -2.000   0.8859   0.01498   0.00774  -0.2547   0.4750   0.0262
  -1.750   0.9290   0.01439   0.00699  -0.2580   0.4658   0.0272
  -1.500   0.9657   0.01417   0.00670  -0.2598   0.4575   0.0288
  -1.250   0.9988   0.01418   0.00656  -0.2608   0.4496   0.0307
  -1.000   1.0374   0.01397   0.00635  -0.2631   0.4433   0.0336
  -0.750   1.0715   0.01396   0.00625  -0.2642   0.4369   0.0356
  -0.500   1.1069   0.01398   0.00619  -0.2658   0.4308   0.0393
  -0.250   1.1406   0.01398   0.00616  -0.2669   0.4259   0.0453
   0.000   1.1850   0.01374   0.00623  -0.2706   0.4204   0.1905
   0.250   1.2132   0.01392   0.00640  -0.2705   0.4156   0.2364
   0.500   1.2409   0.01419   0.00659  -0.2703   0.4106   0.2569
   1.000   1.2962   0.01448   0.00691  -0.2699   0.4041   0.2953
   1.250   1.3244   0.01464   0.00709  -0.2698   0.4005   0.3115
   1.500   1.3524   0.01484   0.00726  -0.2697   0.3969   0.3253
   1.750   1.3804   0.01511   0.00747  -0.2696   0.3929   0.3384
   2.000   1.4089   0.01530   0.00767  -0.2696   0.3901   0.3532
   2.250   1.4373   0.01544   0.00786  -0.2696   0.3877   0.3712
   2.500   1.4655   0.01561   0.00807  -0.2695   0.3851   0.3931
   2.750   1.4939   0.01579   0.00830  -0.2696   0.3824   0.4201
   3.000   1.5218   0.01599   0.00855  -0.2695   0.3797   0.4536
   3.250   1.5500   0.01624   0.00883  -0.2695   0.3768   0.4925
   3.500   1.5799   0.01659   0.00921  -0.2699   0.3734   0.5385
   3.750   1.6082   0.01676   0.00951  -0.2699   0.3716   0.5921
   4.250   1.6651   0.01710   0.01017  -0.2700   0.3675   0.7489
   4.500   1.6794   0.01699   0.01030  -0.2669   0.3655   1.0000
   4.750   1.7050   0.01726   0.01054  -0.2664   0.3632   1.0000
   5.000   1.7303   0.01755   0.01081  -0.2658   0.3609   1.0000
   5.250   1.7560   0.01790   0.01111  -0.2654   0.3584   1.0000
   5.500   1.7849   0.01837   0.01151  -0.2656   0.3552   1.0000
   5.750   1.8082   0.01859   0.01180  -0.2646   0.3535   1.0000
   6.000   1.8316   0.01885   0.01209  -0.2637   0.3514   1.0000
   6.250   1.8547   0.01912   0.01239  -0.2627   0.3488   1.0000
   6.500   1.8777   0.01941   0.01269  -0.2617   0.3463   1.0000
   6.750   1.9003   0.01972   0.01302  -0.2606   0.3436   1.0000
   7.000   1.9234   0.02011   0.01337  -0.2597   0.3406   1.0000
   7.250   1.9495   0.02059   0.01382  -0.2594   0.3373   1.0000
   7.500   1.9706   0.02087   0.01418  -0.2581   0.3355   1.0000
   7.750   1.9920   0.02118   0.01457  -0.2568   0.3332   1.0000
   8.000   2.0132   0.02151   0.01495  -0.2555   0.3305   1.0000
   8.250   2.0331   0.02185   0.01532  -0.2540   0.3273   1.0000
   8.500   2.0533   0.02227   0.01575  -0.2525   0.3243   1.0000
   8.750   2.0760   0.02284   0.01627  -0.2517   0.3202   1.0000
   9.000   2.0941   0.02317   0.01672  -0.2498   0.3179   1.0000
   9.250   2.1121   0.02352   0.01717  -0.2480   0.3144   1.0000
   9.500   2.1296   0.02392   0.01762  -0.2461   0.3104   1.0000
   9.750   2.1463   0.02444   0.01814  -0.2441   0.3064   1.0000
  10.000   2.1645   0.02503   0.01875  -0.2425   0.3026   1.0000
  10.250   2.1826   0.02543   0.01928  -0.2408   0.2994   1.0000
  10.500   2.2002   0.02590   0.01984  -0.2390   0.2957   1.0000
  10.750   2.2165   0.02647   0.02044  -0.2371   0.2916   1.0000
  11.000   2.2310   0.02722   0.02120  -0.2349   0.2876   1.0000
  11.250   2.2486   0.02773   0.02183  -0.2333   0.2837   1.0000
  11.500   2.2650   0.02831   0.02250  -0.2315   0.2789   1.0000
  11.750   2.2779   0.02912   0.02334  -0.2291   0.2738   1.0000
  12.000   2.2927   0.02986   0.02416  -0.2272   0.2688   1.0000
  12.250   2.3063   0.03066   0.02503  -0.2251   0.2619   1.0000
  12.500   2.3169   0.03171   0.02610  -0.2226   0.2556   1.0000
  12.750   2.3293   0.03266   0.02714  -0.2205   0.2482   1.0000
  13.000   2.3370   0.03399   0.02847  -0.2177   0.2405   1.0000
  13.250   2.3453   0.03532   0.02986  -0.2152   0.2316   1.0000
  13.500   2.3509   0.03692   0.03149  -0.2125   0.2225   1.0000
  13.750   2.3523   0.03894   0.03352  -0.2094   0.2123   1.0000
  14.000   2.3534   0.04107   0.03567  -0.2065   0.2015   1.0000
  14.250   2.3524   0.04349   0.03812  -0.2036   0.1914   1.0000
  14.500   2.3470   0.04644   0.04109  -0.2005   0.1816   1.0000
  14.750   2.3388   0.04985   0.04453  -0.1976   0.1727   1.0000
  15.000   2.3327   0.05321   0.04796  -0.1952   0.1644   1.0000
  15.250   2.3201   0.05751   0.05231  -0.1929   0.1569   1.0000
  15.500   2.3096   0.06179   0.05668  -0.1911   0.1498   1.0000
  15.750   2.2926   0.06719   0.06216  -0.1897   0.1437   1.0000
  16.000   2.2771   0.07270   0.06778  -0.1889   0.1374   1.0000
  16.250   2.2516   0.08003   0.07520  -0.1888   0.1321   1.0000
  16.500   2.2347   0.08627   0.08158  -0.1890   0.1270   1.0000
  16.750   2.2066   0.09454   0.08997  -0.1900   0.1222   1.0000
  17.000   2.1825   0.10230   0.09785  -0.1913   0.1183   1.0000
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