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S1223 (s1223-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S1223 (s1223-il)
Reynolds number: 200,000
Max Cl/Cd: 75.26 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1223-il-200000-n5.txt
Download as CSV file: xf-s1223-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000   0.0667   0.09842   0.09487  -0.0763   0.9040   0.0254
  -6.750   0.0725   0.09608   0.09256  -0.0767   0.8926   0.0259
  -6.500   0.0805   0.09346   0.08995  -0.0782   0.8821   0.0262
  -6.000   0.0941   0.08841   0.08490  -0.0820   0.8553   0.0264
  -5.750   0.1166   0.08481   0.08128  -0.0834   0.8412   0.0268
  -5.500   0.1460   0.08112   0.07753  -0.0878   0.8237   0.0273
  -5.250   0.1899   0.07651   0.07276  -0.0968   0.7995   0.0283
  -5.000   0.2411   0.07140   0.06739  -0.1088   0.7613   0.0297
  -4.750   0.2695   0.06699   0.06271  -0.1186   0.7172   0.0307
  -4.500   0.2893   0.06363   0.05909  -0.1239   0.6727   0.0308
  -4.250   0.3000   0.06209   0.05734  -0.1225   0.6362   0.0311
  -4.000   0.3079   0.06067   0.05576  -0.1211   0.6086   0.0316
  -3.750   0.3164   0.05900   0.05398  -0.1208   0.5878   0.0322
  -3.500   0.3360   0.05240   0.04729  -0.1297   0.5753   0.0225
  -3.250   0.3493   0.05111   0.04591  -0.1295   0.5594   0.0221
  -3.000   0.3716   0.04831   0.04301  -0.1334   0.5462   0.0214
  -2.750   0.7154   0.02037   0.01253  -0.2351   0.5196   0.0222
  -2.500   0.7671   0.01927   0.01095  -0.2408   0.5067   0.0230
  -2.250   0.8084   0.01871   0.01016  -0.2439   0.4952   0.0241
  -2.000   0.8473   0.01838   0.00949  -0.2463   0.4856   0.0264
  -1.750   0.8846   0.01807   0.00913  -0.2485   0.4766   0.0284
  -1.500   0.9219   0.01787   0.00875  -0.2504   0.4689   0.0299
  -1.250   0.9601   0.01767   0.00849  -0.2526   0.4617   0.0316
  -1.000   0.9950   0.01766   0.00838  -0.2540   0.4548   0.0353
  -0.500   1.0668   0.01767   0.00817  -0.2573   0.4429   0.0430
  -0.250   1.1020   0.01768   0.00812  -0.2588   0.4368   0.0557
   0.000   1.1435   0.01758   0.00827  -0.2620   0.4310   0.1819
   0.250   1.1730   0.01778   0.00846  -0.2622   0.4265   0.2324
   0.500   1.2015   0.01799   0.00872  -0.2622   0.4220   0.2776
   0.750   1.2298   0.01822   0.00893  -0.2622   0.4177   0.3013
   1.000   1.2582   0.01846   0.00908  -0.2622   0.4139   0.3130
   1.250   1.2871   0.01873   0.00927  -0.2623   0.4103   0.3233
   1.750   1.3446   0.01911   0.00966  -0.2624   0.4026   0.3463
   2.000   1.3729   0.01935   0.00989  -0.2623   0.3990   0.3609
   2.250   1.4012   0.01961   0.01014  -0.2623   0.3958   0.3782
   2.500   1.4297   0.01991   0.01041  -0.2624   0.3930   0.3977
   2.750   1.4584   0.02020   0.01070  -0.2625   0.3901   0.4199
   3.000   1.4865   0.02043   0.01102  -0.2625   0.3870   0.4460
   3.250   1.5143   0.02069   0.01134  -0.2624   0.3838   0.4772
   3.500   1.5420   0.02096   0.01168  -0.2623   0.3809   0.5148
   3.750   1.5696   0.02125   0.01203  -0.2622   0.3783   0.5584
   4.000   1.5966   0.02156   0.01240  -0.2620   0.3759   0.6082
   4.250   1.6235   0.02189   0.01277  -0.2617   0.3735   0.6698
   4.500   1.6469   0.02207   0.01314  -0.2607   0.3711   0.7589
   5.000   1.6836   0.02237   0.01365  -0.2565   0.3661   1.0000
   5.250   1.7090   0.02274   0.01402  -0.2560   0.3637   1.0000
   5.500   1.7340   0.02313   0.01440  -0.2554   0.3614   1.0000
   5.750   1.7587   0.02353   0.01478  -0.2548   0.3591   1.0000
   6.000   1.7838   0.02397   0.01519  -0.2543   0.3568   1.0000
   6.250   1.8091   0.02442   0.01562  -0.2538   0.3544   1.0000
   6.500   1.8319   0.02482   0.01610  -0.2529   0.3520   1.0000
   6.750   1.8545   0.02524   0.01659  -0.2519   0.3494   1.0000
   7.000   1.8763   0.02566   0.01708  -0.2507   0.3465   1.0000
   7.250   1.8978   0.02610   0.01756  -0.2495   0.3437   1.0000
   7.500   1.9192   0.02656   0.01803  -0.2483   0.3410   1.0000
   7.750   1.9420   0.02707   0.01850  -0.2474   0.3383   1.0000
   8.000   1.9617   0.02757   0.01910  -0.2460   0.3354   1.0000
   8.250   1.9798   0.02806   0.01972  -0.2442   0.3321   1.0000
   8.500   1.9980   0.02858   0.02033  -0.2424   0.3287   1.0000
   8.750   2.0163   0.02911   0.02093  -0.2408   0.3256   1.0000
   9.000   2.0348   0.02967   0.02152  -0.2391   0.3227   1.0000
   9.250   2.0542   0.03028   0.02213  -0.2377   0.3198   1.0000
   9.500   2.0691   0.03091   0.02295  -0.2355   0.3163   1.0000
   9.750   2.0837   0.03155   0.02373  -0.2332   0.3123   1.0000
  10.000   2.0975   0.03223   0.02450  -0.2309   0.3082   1.0000
  10.250   2.1117   0.03295   0.02523  -0.2286   0.3046   1.0000
  10.500   2.1247   0.03374   0.02617  -0.2263   0.3005   1.0000
  10.750   2.1370   0.03456   0.02715  -0.2238   0.2958   1.0000
  11.000   2.1469   0.03545   0.02811  -0.2211   0.2906   1.0000
  11.250   2.1566   0.03643   0.02917  -0.2184   0.2857   1.0000
  11.500   2.1669   0.03743   0.03035  -0.2159   0.2798   1.0000
  11.750   2.1749   0.03858   0.03158  -0.2131   0.2744   1.0000
  12.000   2.1832   0.03979   0.03290  -0.2105   0.2692   1.0000
  12.250   2.1911   0.04109   0.03435  -0.2080   0.2630   1.0000
  12.500   2.1951   0.04265   0.03597  -0.2051   0.2571   1.0000
  12.750   2.2015   0.04419   0.03767  -0.2027   0.2506   1.0000
  13.000   2.2033   0.04609   0.03965  -0.1999   0.2439   1.0000
  13.250   2.2055   0.04811   0.04178  -0.1974   0.2366   1.0000
  13.500   2.2037   0.05057   0.04432  -0.1947   0.2291   1.0000
  13.750   2.2028   0.05312   0.04699  -0.1924   0.2216   1.0000
  14.000   2.1966   0.05632   0.05026  -0.1900   0.2141   1.0000
  14.250   2.1912   0.05965   0.05371  -0.1881   0.2059   1.0000
  14.500   2.1798   0.06386   0.05799  -0.1863   0.1984   1.0000
  14.750   2.1685   0.06833   0.06258  -0.1849   0.1902   1.0000
  15.000   2.1524   0.07369   0.06803  -0.1841   0.1835   1.0000
  15.250   2.1359   0.07943   0.07390  -0.1837   0.1762   1.0000
  15.500   2.1150   0.08606   0.08064  -0.1840   0.1701   1.0000
  15.750   2.0959   0.09269   0.08740  -0.1847   0.1635   1.0000
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