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S1223 RTL (s1223rtl-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S1223 RTL (s1223rtl-il)
Reynolds number: 500,000
Max Cl/Cd: 84.04 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1223rtl-il-500000.txt
Download as CSV file: xf-s1223rtl-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500   0.0942   0.10030   0.09800  -0.0912   0.9338   0.0184
  -8.250   0.1068   0.09753   0.09523  -0.0926   0.9271   0.0187
  -7.750   0.1259   0.09240   0.09011  -0.0939   0.9065   0.0198
  -7.500   0.1434   0.08858   0.08626  -0.0982   0.8953   0.0209
  -7.250   0.1625   0.08329   0.08093  -0.1073   0.8838   0.0212
  -7.000   0.2733   0.07620   0.07226  -0.1304   0.6144   0.0220
  -6.750   0.2657   0.07611   0.07152  -0.1263   0.4826   0.0221
  -6.500   0.2680   0.07476   0.07004  -0.1249   0.4524   0.0226
  -6.250   0.2698   0.07326   0.06848  -0.1236   0.4376   0.0231
  -6.000   0.2702   0.07172   0.06691  -0.1221   0.4267   0.0233
  -5.750   0.2652   0.07011   0.06530  -0.1201   0.4191   0.0242
  -5.500   0.2530   0.06865   0.06390  -0.1171   0.4150   0.0245
  -5.250   0.2399   0.06478   0.06011  -0.1181   0.4128   0.0248
  -5.000   0.2448   0.06318   0.05848  -0.1163   0.4053   0.0250
  -4.750   0.2515   0.06208   0.05735  -0.1143   0.3984   0.0252
  -4.500   0.2595   0.06053   0.05581  -0.1137   0.3937   0.0255
  -4.250   0.2682   0.05885   0.05413  -0.1135   0.3891   0.0262
  -4.000   0.2779   0.05663   0.05189  -0.1147   0.3847   0.0269
  -3.750   0.2922   0.03601   0.03153  -0.1116   0.3771   0.0294
  -3.500   0.6155   0.01873   0.01159  -0.2247   0.3714   0.0250
  -3.250   0.6643   0.01735   0.00984  -0.2297   0.3661   0.0251
  -3.000   0.7018   0.01679   0.00911  -0.2320   0.3605   0.0259
  -2.750   0.7386   0.01632   0.00853  -0.2338   0.3575   0.0268
  -2.500   0.7748   0.01593   0.00801  -0.2355   0.3543   0.0279
  -2.250   0.8106   0.01561   0.00760  -0.2371   0.3509   0.0297
  -2.000   0.8432   0.01550   0.00743  -0.2380   0.3476   0.0317
  -1.750   0.8769   0.01541   0.00722  -0.2391   0.3441   0.0334
  -1.500   0.9121   0.01537   0.00713  -0.2407   0.3405   0.0361
  -1.250   0.9464   0.01523   0.00698  -0.2420   0.3385   0.0399
  -1.000   0.9795   0.01516   0.00689  -0.2430   0.3359   0.0456
  -0.750   1.0126   0.01512   0.00682  -0.2440   0.3332   0.0554
  -0.500   1.0546   0.01482   0.00684  -0.2472   0.3304   0.1856
  -0.250   1.0843   0.01493   0.00701  -0.2476   0.3280   0.2497
   0.000   1.1119   0.01515   0.00720  -0.2474   0.3254   0.2782
   0.250   1.1407   0.01551   0.00750  -0.2475   0.3221   0.3010
   0.500   1.1679   0.01562   0.00765  -0.2472   0.3209   0.3209
   0.750   1.1950   0.01576   0.00782  -0.2468   0.3193   0.3433
   1.000   1.2217   0.01593   0.00801  -0.2464   0.3174   0.3666
   1.250   1.2484   0.01609   0.00817  -0.2461   0.3153   0.3817
   1.500   1.2750   0.01627   0.00833  -0.2456   0.3132   0.3961
   1.750   1.3018   0.01645   0.00852  -0.2453   0.3112   0.4098
   2.000   1.3283   0.01668   0.00872  -0.2449   0.3093   0.4238
   2.250   1.3550   0.01697   0.00898  -0.2446   0.3072   0.4390
   2.500   1.3839   0.01739   0.00935  -0.2448   0.3045   0.4542
   2.750   1.4106   0.01760   0.00961  -0.2444   0.3032   0.4683
   3.000   1.4363   0.01778   0.00983  -0.2439   0.3020   0.4824
   3.250   1.4618   0.01798   0.01006  -0.2433   0.3005   0.4975
   3.500   1.4871   0.01819   0.01029  -0.2427   0.2988   0.5130
   3.750   1.5123   0.01841   0.01054  -0.2421   0.2970   0.5280
   4.000   1.5374   0.01864   0.01080  -0.2415   0.2952   0.5431
   4.250   1.5626   0.01888   0.01107  -0.2410   0.2936   0.5598
   4.500   1.5878   0.01915   0.01135  -0.2404   0.2920   0.5782
   4.750   1.6136   0.01947   0.01168  -0.2400   0.2903   0.5979
   5.000   1.6417   0.01989   0.01211  -0.2402   0.2882   0.6210
   5.250   1.6708   0.02029   0.01257  -0.2405   0.2864   0.6509
   5.500   1.6960   0.02049   0.01292  -0.2400   0.2854   0.6949
   5.750   1.7119   0.02037   0.01316  -0.2375   0.2842   1.0000
   6.000   1.7352   0.02066   0.01347  -0.2366   0.2828   1.0000
   6.250   1.7583   0.02096   0.01378  -0.2357   0.2812   1.0000
   6.500   1.7815   0.02129   0.01411  -0.2349   0.2797   1.0000
   6.750   1.8046   0.02162   0.01445  -0.2340   0.2782   1.0000
   7.000   1.8274   0.02197   0.01480  -0.2331   0.2768   1.0000
   7.250   1.8499   0.02234   0.01517  -0.2322   0.2754   1.0000
   7.500   1.8728   0.02275   0.01557  -0.2313   0.2740   1.0000
   7.750   1.8976   0.02325   0.01605  -0.2309   0.2723   1.0000
   8.000   1.9257   0.02385   0.01663  -0.2312   0.2702   1.0000
   8.250   1.9447   0.02419   0.01705  -0.2296   0.2693   1.0000
   8.500   1.9646   0.02457   0.01750  -0.2282   0.2681   1.0000
   8.750   1.9852   0.02498   0.01798  -0.2270   0.2669   1.0000
   9.000   2.0056   0.02541   0.01846  -0.2258   0.2655   1.0000
   9.250   2.0260   0.02586   0.01896  -0.2246   0.2642   1.0000
   9.500   2.0460   0.02631   0.01946  -0.2233   0.2628   1.0000
   9.750   2.0658   0.02679   0.01998  -0.2221   0.2615   1.0000
  10.000   2.0854   0.02727   0.02050  -0.2208   0.2602   1.0000
  10.250   2.1046   0.02777   0.02103  -0.2195   0.2589   1.0000
  10.500   2.1246   0.02833   0.02161  -0.2183   0.2574   1.0000
  10.750   2.1501   0.02904   0.02231  -0.2183   0.2553   1.0000
  11.000   2.1689   0.02965   0.02301  -0.2170   0.2542   1.0000
  11.250   2.1848   0.03025   0.02372  -0.2152   0.2533   1.0000
  11.500   2.2008   0.03088   0.02446  -0.2134   0.2521   1.0000
  11.750   2.2170   0.03153   0.02521  -0.2117   0.2509   1.0000
  12.000   2.2329   0.03220   0.02598  -0.2100   0.2497   1.0000
  12.250   2.2483   0.03289   0.02675  -0.2083   0.2483   1.0000
  12.500   2.2634   0.03358   0.02752  -0.2065   0.2469   1.0000
  12.750   2.2781   0.03429   0.02829  -0.2048   0.2455   1.0000
  13.000   2.2934   0.03503   0.02909  -0.2032   0.2443   1.0000
  13.250   2.3087   0.03582   0.02994  -0.2016   0.2431   1.0000
  13.500   2.3261   0.03665   0.03081  -0.2004   0.2415   1.0000
  13.750   2.3452   0.03760   0.03182  -0.1996   0.2396   1.0000
  14.000   2.3510   0.03867   0.03305  -0.1967   0.2384   1.0000
  14.250   2.3559   0.03979   0.03432  -0.1939   0.2366   1.0000
  14.500   2.3633   0.04091   0.03557  -0.1915   0.2348   1.0000
  14.750   2.3710   0.04203   0.03679  -0.1893   0.2329   1.0000
  15.000   2.3798   0.04315   0.03800  -0.1873   0.2311   1.0000
  15.250   2.3881   0.04437   0.03929  -0.1854   0.2294   1.0000
  15.500   2.3976   0.04561   0.04056  -0.1836   0.2274   1.0000
  15.750   2.4032   0.04719   0.04223  -0.1816   0.2247   1.0000
  16.000   2.4006   0.04915   0.04438  -0.1790   0.2216   1.0000
  16.250   2.4023   0.05095   0.04629  -0.1770   0.2180   1.0000
  16.500   2.4036   0.05293   0.04831  -0.1752   0.2142   1.0000
  16.750   2.4037   0.05526   0.05072  -0.1735   0.2103   1.0000
  17.000   2.4061   0.05746   0.05310  -0.1721   0.2067   1.0000
  17.250   2.4072   0.05989   0.05562  -0.1708   0.2031   1.0000
  17.500   2.4041   0.06289   0.05868  -0.1695   0.1998   1.0000
  17.750   2.4022   0.06591   0.06183  -0.1685   0.1969   1.0000
  18.000   2.4012   0.06894   0.06504  -0.1677   0.1934   1.0000
  18.250   2.3940   0.07284   0.06904  -0.1670   0.1894   1.0000
  18.500   2.3802   0.07780   0.07408  -0.1667   0.1859   1.0000
  18.750   2.3705   0.08244   0.07890  -0.1668   0.1818   1.0000
  19.000   2.3531   0.08841   0.08503  -0.1675   0.1777   1.0000
  19.250   2.3258   0.09621   0.09296  -0.1691   0.1740   1.0000
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