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S1223 RTL (s1223rtl-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S1223 RTL (s1223rtl-il)
Reynolds number: 200,000
Max Cl/Cd: 98.03 at α=-1.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1223rtl-il-200000.txt
Download as CSV file: xf-s1223rtl-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1223 RTL                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.250   0.1145   0.08921   0.08609  -0.0834   0.9043   0.0417
  -6.000   0.1188   0.08675   0.08365  -0.0845   0.8921   0.0430
  -5.750   0.1056   0.08536   0.08230  -0.0864   0.8792   0.0437
  -5.500   0.1250   0.08139   0.07834  -0.0863   0.8645   0.0441
  -5.250   0.1583   0.07728   0.07417  -0.0882   0.8400   0.0459
  -5.000   0.2853   0.06628   0.06199  -0.1204   0.6366   0.0513
  -4.750   0.2674   0.06673   0.06172  -0.1131   0.5227   0.0519
  -4.500   0.2656   0.06572   0.06053  -0.1104   0.4958   0.0531
  -4.250   0.2779   0.04885   0.04369  -0.1030   0.4613   0.0586
  -4.000   0.2872   0.04737   0.04218  -0.1015   0.4528   0.0608
  -3.750   0.2874   0.05957   0.05410  -0.1133   0.4605   0.0594
  -3.250   0.3961   0.04745   0.04164  -0.1514   0.4434   0.0754
  -3.000   0.3954   0.04723   0.04144  -0.1436   0.4373   0.0761
  -2.750   0.4040   0.04660   0.04082  -0.1392   0.4313   0.0773
  -2.500   0.5209   0.03875   0.03242  -0.1716   0.4223   0.0986
  -2.250   0.5887   0.03447   0.02787  -0.1852   0.4158   0.1149
  -2.000   0.6052   0.03385   0.02734  -0.1824   0.4110   0.1173
  -1.750   0.8488   0.01008   0.00086  -0.2283   0.3968   0.0588
  -1.500   0.8853   0.00973   0.00049  -0.2300   0.3926   0.0638
  -1.250   0.9244   0.00943   0.00019  -0.2323   0.3883   0.0722
  -1.000   0.9737   0.01995   0.01033  -0.2421   0.3867   0.0797
  -0.750   1.0287   0.01957   0.01029  -0.2482   0.3824   0.2244
  -0.500   1.0632   0.02011   0.01079  -0.2494   0.3788   0.3083
  -0.250   1.0904   0.02039   0.01105  -0.2490   0.3757   0.3395
   0.000   1.1180   0.02070   0.01138  -0.2487   0.3723   0.3653
   0.250   1.1458   0.02107   0.01173  -0.2485   0.3691   0.3917
   0.500   1.1748   0.02144   0.01203  -0.2485   0.3663   0.4144
   0.750   1.2056   0.02178   0.01230  -0.2490   0.3635   0.4296
   1.000   1.2408   0.02236   0.01275  -0.2505   0.3605   0.4454
   1.250   1.2699   0.02265   0.01306  -0.2506   0.3583   0.4604
   1.500   1.2975   0.02290   0.01334  -0.2504   0.3559   0.4767
   1.750   1.3254   0.02319   0.01363  -0.2503   0.3530   0.4935
   2.000   1.3535   0.02347   0.01393  -0.2503   0.3502   0.5092
   2.250   1.3820   0.02378   0.01424  -0.2504   0.3477   0.5268
   2.500   1.4115   0.02415   0.01457  -0.2506   0.3454   0.5453
   2.750   1.4424   0.02462   0.01499  -0.2513   0.3432   0.5641
   3.000   1.4760   0.02545   0.01577  -0.2526   0.3407   0.5848
   3.250   1.5020   0.02573   0.01616  -0.2521   0.3390   0.6049
   3.500   1.5283   0.02606   0.01660  -0.2518   0.3370   0.6257
   3.750   1.5546   0.02641   0.01706  -0.2515   0.3346   0.6488
   4.000   1.5811   0.02677   0.01750  -0.2512   0.3322   0.6765
   4.250   1.6070   0.02710   0.01790  -0.2508   0.3299   0.7095
   4.500   1.6316   0.02738   0.01830  -0.2501   0.3280   0.7625
   4.750   1.6476   0.02745   0.01853  -0.2476   0.3264   1.0000
   5.000   1.6775   0.02809   0.01906  -0.2482   0.3245   1.0000
   5.250   1.7090   0.02914   0.02000  -0.2493   0.3224   1.0000
   5.500   1.7331   0.02976   0.02069  -0.2486   0.3209   1.0000
   5.750   1.7559   0.03028   0.02131  -0.2477   0.3191   1.0000
   6.000   1.7789   0.03085   0.02195  -0.2469   0.3170   1.0000
   6.250   1.8021   0.03142   0.02257  -0.2461   0.3148   1.0000
   6.500   1.8254   0.03202   0.02321  -0.2454   0.3128   1.0000
   6.750   1.8491   0.03263   0.02387  -0.2447   0.3110   1.0000
   7.000   1.8731   0.03324   0.02450  -0.2441   0.3093   1.0000
   7.250   1.8980   0.03387   0.02513  -0.2438   0.3078   1.0000
   7.500   1.9241   0.03462   0.02587  -0.2437   0.3063   1.0000
   7.750   1.9519   0.03582   0.02703  -0.2441   0.3045   1.0000
   8.000   1.9701   0.03673   0.02810  -0.2425   0.3029   1.0000
   8.250   1.9861   0.03749   0.02905  -0.2405   0.3010   1.0000
   8.500   2.0031   0.03836   0.03009  -0.2387   0.2991   1.0000
   8.750   2.0211   0.03929   0.03115  -0.2372   0.2973   1.0000
   9.000   2.0398   0.04019   0.03216  -0.2359   0.2956   1.0000
   9.250   2.0583   0.04107   0.03314  -0.2345   0.2940   1.0000
   9.500   2.0775   0.04190   0.03405  -0.2332   0.2924   1.0000
   9.750   2.0975   0.04271   0.03493  -0.2321   0.2910   1.0000
  10.000   2.1187   0.04348   0.03573  -0.2312   0.2897   1.0000
  10.250   2.1432   0.04436   0.03661  -0.2311   0.2882   1.0000
  10.500   2.1622   0.04600   0.03835  -0.2302   0.2865   1.0000
  10.750   2.1622   0.04750   0.04014  -0.2258   0.2850   1.0000
  11.000   2.1605   0.04929   0.04222  -0.2213   0.2833   1.0000
  11.250   2.1571   0.05117   0.04435  -0.2166   0.2816   1.0000
  11.500   2.1518   0.05303   0.04642  -0.2118   0.2800   1.0000
  11.750   2.1490   0.05482   0.04839  -0.2075   0.2784   1.0000
  12.000   2.1528   0.05627   0.04997  -0.2042   0.2769   1.0000
  12.250   2.1595   0.05754   0.05135  -0.2015   0.2755   1.0000
  12.500   2.1704   0.05863   0.05252  -0.1994   0.2741   1.0000
  12.750   2.1858   0.05963   0.05358  -0.1980   0.2729   1.0000
  13.000   2.2018   0.06089   0.05490  -0.1969   0.2718   1.0000
  13.250   2.2204   0.06284   0.05691  -0.1965   0.2705   1.0000
  13.500   2.1175   0.07124   0.06589  -0.1824   0.2688   1.0000
  13.750   1.3542   0.20888   0.20484  -0.2345   0.2501   1.0000
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