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S1223 RTL (s1223rtl-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S1223 RTL (s1223rtl-il)
Reynolds number: 500,000
Max Cl/Cd: 85.43 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1223rtl-il-500000-n5.txt
Download as CSV file: xf-s1223rtl-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250   0.1985   0.09508   0.09021  -0.1287   0.4952   0.0147
  -9.000   0.2041   0.09287   0.08785  -0.1291   0.4640   0.0147
  -8.750   0.2134   0.09098   0.08584  -0.1288   0.4380   0.0149
  -8.500   0.2228   0.08945   0.08424  -0.1284   0.4216   0.0152
  -8.250   0.2292   0.08753   0.08230  -0.1282   0.4124   0.0153
  -8.000   0.2363   0.08587   0.08062  -0.1279   0.4037   0.0156
  -7.750   0.2426   0.08419   0.07892  -0.1274   0.3968   0.0161
  -7.500   0.2471   0.08224   0.07697  -0.1269   0.3911   0.0164
  -7.250   0.2508   0.08028   0.07501  -0.1263   0.3861   0.0168
  -6.750   0.2502   0.07537   0.07012  -0.1247   0.3789   0.0144
  -6.500   0.2539   0.07380   0.06857  -0.1235   0.3748   0.0139
  -6.250   0.2540   0.07194   0.06673  -0.1221   0.3716   0.0135
  -6.000   0.2476   0.06959   0.06441  -0.1202   0.3690   0.0126
  -5.750   0.2389   0.06767   0.06253  -0.1176   0.3663   0.0125
  -4.750   0.4778   0.01755   0.01038  -0.2249   0.3546   0.0145
  -4.500   0.5219   0.01665   0.00918  -0.2290   0.3496   0.0149
  -4.250   0.5582   0.01624   0.00864  -0.2311   0.3452   0.0153
  -3.750   0.6278   0.01566   0.00782  -0.2342   0.3382   0.0164
  -3.500   0.6630   0.01537   0.00741  -0.2357   0.3352   0.0171
  -3.250   0.6972   0.01516   0.00707  -0.2370   0.3317   0.0178
  -3.000   0.7307   0.01501   0.00685  -0.2383   0.3281   0.0186
  -2.750   0.7619   0.01497   0.00674  -0.2389   0.3247   0.0198
  -2.500   0.7936   0.01492   0.00658  -0.2397   0.3218   0.0210
  -2.250   0.8272   0.01479   0.00642  -0.2408   0.3199   0.0221
  -2.000   0.8589   0.01474   0.00632  -0.2415   0.3177   0.0235
  -1.750   0.8904   0.01470   0.00623  -0.2422   0.3154   0.0251
  -1.500   0.9210   0.01471   0.00619  -0.2426   0.3131   0.0275
  -1.250   0.9513   0.01473   0.00617  -0.2430   0.3108   0.0306
  -1.000   0.9811   0.01478   0.00616  -0.2433   0.3084   0.0344
  -0.750   1.0106   0.01486   0.00619  -0.2436   0.3058   0.0409
  -0.500   1.0405   0.01492   0.00625  -0.2439   0.3036   0.0558
  -0.250   1.0725   0.01489   0.00631  -0.2447   0.3019   0.0972
   0.000   1.1057   0.01483   0.00645  -0.2460   0.3002   0.1881
   0.250   1.1343   0.01492   0.00660  -0.2460   0.2984   0.2273
   0.500   1.1617   0.01505   0.00674  -0.2458   0.2966   0.2537
   0.750   1.1891   0.01519   0.00691  -0.2456   0.2947   0.2823
   1.000   1.2160   0.01535   0.00710  -0.2453   0.2929   0.3137
   1.250   1.2423   0.01554   0.00727  -0.2449   0.2910   0.3281
   1.500   1.2681   0.01575   0.00745  -0.2443   0.2890   0.3398
   1.750   1.2937   0.01599   0.00766  -0.2437   0.2868   0.3512
   2.000   1.3200   0.01615   0.00784  -0.2433   0.2856   0.3628
   2.250   1.3460   0.01633   0.00803  -0.2428   0.2843   0.3762
   2.500   1.3720   0.01651   0.00824  -0.2423   0.2829   0.3884
   2.750   1.3975   0.01672   0.00845  -0.2417   0.2813   0.3999
   3.000   1.4230   0.01693   0.00868  -0.2412   0.2798   0.4124
   3.250   1.4482   0.01715   0.00891  -0.2406   0.2782   0.4253
   3.500   1.4731   0.01738   0.00915  -0.2399   0.2767   0.4385
   3.750   1.4979   0.01763   0.00940  -0.2392   0.2751   0.4509
   4.000   1.5222   0.01790   0.00967  -0.2385   0.2733   0.4625
   4.250   1.5462   0.01820   0.00997  -0.2377   0.2715   0.4755
   4.500   1.5704   0.01849   0.01028  -0.2370   0.2700   0.4899
   4.750   1.5950   0.01872   0.01057  -0.2363   0.2689   0.5032
   5.000   1.6193   0.01898   0.01087  -0.2356   0.2677   0.5166
   5.250   1.6435   0.01924   0.01119  -0.2349   0.2664   0.5320
   5.500   1.6675   0.01952   0.01151  -0.2342   0.2651   0.5484
   5.750   1.6914   0.01981   0.01185  -0.2334   0.2636   0.5659
   6.250   1.7389   0.02042   0.01258  -0.2320   0.2607   0.6098
   6.500   1.7626   0.02075   0.01296  -0.2313   0.2591   0.6396
   6.750   1.7867   0.02110   0.01340  -0.2307   0.2574   0.6858
   7.250   1.8233   0.02159   0.01420  -0.2271   0.2546   1.0000
   7.500   1.8456   0.02195   0.01460  -0.2262   0.2537   1.0000
   7.750   1.8677   0.02232   0.01502  -0.2252   0.2526   1.0000
   8.000   1.8895   0.02271   0.01544  -0.2242   0.2515   1.0000
   8.250   1.9110   0.02311   0.01588  -0.2231   0.2502   1.0000
   8.500   1.9319   0.02353   0.01635  -0.2220   0.2488   1.0000
   8.750   1.9523   0.02398   0.01683  -0.2208   0.2473   1.0000
   9.000   1.9724   0.02444   0.01732  -0.2196   0.2458   1.0000
   9.250   1.9921   0.02493   0.01784  -0.2183   0.2444   1.0000
   9.500   2.0112   0.02546   0.01840  -0.2170   0.2431   1.0000
   9.750   2.0297   0.02604   0.01900  -0.2155   0.2418   1.0000
  10.000   2.0477   0.02667   0.01966  -0.2141   0.2404   1.0000
  10.250   2.0667   0.02723   0.02028  -0.2128   0.2393   1.0000
  10.500   2.0858   0.02777   0.02090  -0.2116   0.2384   1.0000
  10.750   2.1045   0.02833   0.02154  -0.2103   0.2372   1.0000
  11.000   2.1228   0.02892   0.02221  -0.2089   0.2359   1.0000
  11.250   2.1406   0.02952   0.02289  -0.2076   0.2345   1.0000
  11.500   2.1575   0.03019   0.02362  -0.2061   0.2330   1.0000
  11.750   2.1740   0.03089   0.02439  -0.2046   0.2317   1.0000
  12.000   2.1901   0.03163   0.02519  -0.2031   0.2305   1.0000
  12.250   2.2052   0.03243   0.02606  -0.2015   0.2292   1.0000
  12.500   2.2197   0.03329   0.02698  -0.1998   0.2280   1.0000
  12.750   2.2333   0.03423   0.02797  -0.1981   0.2267   1.0000
  13.000   2.2467   0.03521   0.02902  -0.1964   0.2252   1.0000
  13.250   2.2619   0.03604   0.02996  -0.1950   0.2242   1.0000
  13.500   2.2762   0.03694   0.03098  -0.1935   0.2230   1.0000
  13.750   2.2899   0.03791   0.03206  -0.1919   0.2218   1.0000
  14.000   2.3031   0.03891   0.03316  -0.1904   0.2201   1.0000
  14.250   2.3145   0.04002   0.03437  -0.1887   0.2178   1.0000
  14.500   2.3249   0.04125   0.03566  -0.1870   0.2156   1.0000
  14.750   2.3328   0.04270   0.03717  -0.1852   0.2133   1.0000
  15.000   2.3409   0.04420   0.03875  -0.1834   0.2114   1.0000
  15.250   2.3521   0.04545   0.04014  -0.1820   0.2093   1.0000
  15.500   2.3619   0.04684   0.04166  -0.1805   0.2070   1.0000
  15.750   2.3695   0.04846   0.04338  -0.1790   0.2044   1.0000
  16.000   2.3720   0.05057   0.04553  -0.1772   0.2001   1.0000
  16.250   2.3764   0.05260   0.04766  -0.1757   0.1958   1.0000
  16.500   2.3779   0.05498   0.05011  -0.1742   0.1891   1.0000
  16.750   2.3745   0.05800   0.05320  -0.1726   0.1822   1.0000
  17.000   2.3683   0.06149   0.05675  -0.1712   0.1751   1.0000
  17.250   2.3606   0.06531   0.06066  -0.1700   0.1691   1.0000
  17.500   2.3458   0.07024   0.06567  -0.1690   0.1622   1.0000
  17.750   2.3300   0.07558   0.07113  -0.1686   0.1563   1.0000
  18.000   2.3048   0.08264   0.07831  -0.1689   0.1504   1.0000
  18.250   2.2759   0.09075   0.08659  -0.1702   0.1458   1.0000
  18.500   2.2414   0.10028   0.09631  -0.1727   0.1416   1.0000
  18.750   2.2059   0.11026   0.10648  -0.1760   0.1395   1.0000
  19.000   2.1624   0.12160   0.11801  -0.1802   0.1374   1.0000
  19.250   2.1282   0.13121   0.12779  -0.1841   0.1345   1.0000
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