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S1223 RTL (s1223rtl-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S1223 RTL (s1223rtl-il)
Reynolds number: 100,000
Max Cl/Cd: 49.79 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1223rtl-il-100000-n5.txt
Download as CSV file: xf-s1223rtl-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250   0.0250   0.10678   0.10224  -0.0674   0.9107   0.0490
  -7.000   0.0329   0.10428   0.09977  -0.0707   0.9028   0.0498
  -6.750   0.0301   0.10271   0.09825  -0.0713   0.8911   0.0500
  -6.500   0.0477   0.09875   0.09432  -0.0710   0.8811   0.0506
  -6.250   0.0653   0.09546   0.09104  -0.0717   0.8708   0.0518
  -6.000   0.0713   0.09322   0.08883  -0.0711   0.8556   0.0533
  -5.750   0.0719   0.09143   0.08708  -0.0712   0.8399   0.0561
  -5.500   0.0682   0.08982   0.08550  -0.0714   0.8222   0.0568
  -5.250   0.0827   0.08637   0.08205  -0.0716   0.8008   0.0586
  -5.000   0.0998   0.08341   0.07902  -0.0725   0.7670   0.0607
  -4.500   0.1914   0.07235   0.06661  -0.0955   0.5499   0.0665
  -4.250   0.1989   0.07067   0.06462  -0.0942   0.5088   0.0674
  -4.000   0.2074   0.06876   0.06255  -0.0943   0.4873   0.0682
  -3.500   0.2436   0.05725   0.05079  -0.1085   0.4685   0.0380
  -3.250   0.2671   0.05455   0.04796  -0.1120   0.4569   0.0372
  -3.000   0.3089   0.04954   0.04279  -0.1224   0.4470   0.0361
  -2.750   0.6024   0.02704   0.01744  -0.2044   0.4267   0.0382
  -2.500   0.6493   0.02611   0.01618  -0.2090   0.4192   0.0400
  -2.250   0.6981   0.02520   0.01482  -0.2136   0.4118   0.0439
  -2.000   0.7388   0.02466   0.01411  -0.2165   0.4053   0.0465
  -1.500   0.8200   0.02404   0.01311  -0.2217   0.3946   0.0558
  -1.250   0.8602   0.02384   0.01282  -0.2243   0.3897   0.0620
  -1.000   0.9015   0.02376   0.01258  -0.2271   0.3853   0.0741
  -0.750   0.9481   0.02362   0.01237  -0.2313   0.3810   0.1038
  -0.500   0.9921   0.02355   0.01261  -0.2350   0.3768   0.2395
  -0.250   1.0231   0.02386   0.01294  -0.2355   0.3727   0.3004
   0.000   1.0521   0.02428   0.01334  -0.2356   0.3689   0.3461
   0.250   1.0815   0.02470   0.01364  -0.2357   0.3656   0.3787
   0.500   1.1123   0.02506   0.01385  -0.2362   0.3627   0.3972
   0.750   1.1443   0.02548   0.01411  -0.2369   0.3601   0.4117
   1.000   1.1738   0.02577   0.01439  -0.2371   0.3573   0.4261
   1.250   1.2031   0.02609   0.01467  -0.2373   0.3543   0.4411
   1.500   1.2322   0.02644   0.01496  -0.2375   0.3511   0.4569
   1.750   1.2607   0.02679   0.01526  -0.2376   0.3481   0.4729
   2.000   1.2889   0.02716   0.01556  -0.2375   0.3454   0.4884
   2.250   1.3174   0.02756   0.01587  -0.2376   0.3431   0.5050
   2.500   1.3472   0.02805   0.01625  -0.2380   0.3410   0.5229
   2.750   1.3741   0.02846   0.01671  -0.2378   0.3388   0.5405
   3.000   1.4005   0.02888   0.01719  -0.2375   0.3364   0.5592
   3.250   1.4268   0.02931   0.01767  -0.2372   0.3339   0.5789
   3.500   1.4528   0.02975   0.01813  -0.2368   0.3313   0.6005
   3.750   1.4787   0.03017   0.01858  -0.2364   0.3289   0.6236
   4.000   1.5047   0.03058   0.01901  -0.2361   0.3267   0.6500
   4.250   1.5309   0.03100   0.01946  -0.2358   0.3247   0.6830
   4.500   1.5568   0.03143   0.01993  -0.2355   0.3230   0.7313
   4.750   1.5723   0.03158   0.02029  -0.2329   0.3215   1.0000
   5.000   1.5967   0.03226   0.02103  -0.2324   0.3194   1.0000
   5.250   1.6208   0.03295   0.02179  -0.2319   0.3173   1.0000
   5.500   1.6444   0.03363   0.02251  -0.2313   0.3150   1.0000
   5.750   1.6678   0.03430   0.02320  -0.2306   0.3128   1.0000
   6.000   1.6914   0.03495   0.02385  -0.2300   0.3106   1.0000
   6.250   1.7153   0.03559   0.02449  -0.2294   0.3087   1.0000
   6.500   1.7397   0.03624   0.02512  -0.2290   0.3070   1.0000
   6.750   1.7651   0.03694   0.02578  -0.2288   0.3056   1.0000
   7.000   1.7918   0.03772   0.02652  -0.2288   0.3042   1.0000
   7.250   1.8089   0.03868   0.02767  -0.2271   0.3024   1.0000
   7.500   1.8252   0.03969   0.02886  -0.2254   0.3004   1.0000
   7.750   1.8414   0.04067   0.03001  -0.2236   0.2983   1.0000
   8.000   1.8577   0.04162   0.03111  -0.2218   0.2961   1.0000
   8.250   1.8744   0.04253   0.03212  -0.2202   0.2942   1.0000
   8.500   1.8917   0.04343   0.03311  -0.2187   0.2925   1.0000
   8.750   1.9100   0.04433   0.03409  -0.2173   0.2910   1.0000
   9.000   1.9294   0.04520   0.03502  -0.2162   0.2896   1.0000
   9.250   1.9503   0.04607   0.03592  -0.2153   0.2884   1.0000
   9.500   1.9734   0.04695   0.03682  -0.2149   0.2872   1.0000
   9.750   1.9768   0.04848   0.03860  -0.2113   0.2856   1.0000
  10.000   1.9694   0.05036   0.04079  -0.2061   0.2835   1.0000
  10.250   1.9641   0.05230   0.04300  -0.2015   0.2815   1.0000
  10.500   1.9610   0.05425   0.04518  -0.1975   0.2796   1.0000
  10.750   1.9595   0.05620   0.04733  -0.1938   0.2778   1.0000
  11.000   1.9595   0.05817   0.04949  -0.1906   0.2763   1.0000
  11.250   1.9610   0.06011   0.05158  -0.1877   0.2749   1.0000
  11.500   1.9650   0.06192   0.05352  -0.1852   0.2736   1.0000
  11.750   1.9716   0.06362   0.05533  -0.1831   0.2725   1.0000
  12.000   1.9848   0.06491   0.05670  -0.1818   0.2714   1.0000
  12.250   1.9844   0.06726   0.05920  -0.1793   0.2700   1.0000
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