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S2050 8.93% (s2050-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S2050 8.93% (s2050-il)
Reynolds number: 50,000
Max Cl/Cd: 33.24 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2050-il-50000.txt
Download as CSV file: xf-s2050-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2050 8.93%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5112   0.10907   0.10200  -0.0052   1.0000   0.2603
  -8.750  -0.5038   0.10537   0.09833  -0.0045   1.0000   0.2746
  -8.500  -0.5018   0.10220   0.09522  -0.0040   1.0000   0.2893
  -8.250  -0.4984   0.09894   0.09202  -0.0033   1.0000   0.3039
  -8.000  -0.4974   0.09583   0.08898  -0.0026   1.0000   0.3187
  -7.750  -0.4933   0.09239   0.08556  -0.0017   1.0000   0.3332
  -7.500  -0.4718   0.08767   0.08082   0.0000   1.0000   0.3529
  -7.250  -0.5623   0.07063   0.06398  -0.0317   1.0000   0.1606
  -7.000  -0.5690   0.06133   0.05429  -0.0376   1.0000   0.1290
  -6.750  -0.5616   0.05646   0.04928  -0.0380   1.0000   0.1260
  -6.500  -0.5544   0.05132   0.04382  -0.0390   1.0000   0.1241
  -6.250  -0.5432   0.04647   0.03853  -0.0396   1.0000   0.1237
  -6.000  -0.5279   0.04185   0.03338  -0.0399   1.0000   0.1242
  -5.750  -0.5092   0.03782   0.02858  -0.0400   1.0000   0.1292
  -5.500  -0.4888   0.03485   0.02545  -0.0393   1.0000   0.1401
  -5.250  -0.4669   0.03209   0.02234  -0.0386   1.0000   0.1552
  -5.000  -0.4431   0.02955   0.01927  -0.0380   1.0000   0.1734
  -4.750  -0.4201   0.02734   0.01709  -0.0371   1.0000   0.1934
  -4.500  -0.3965   0.02552   0.01517  -0.0362   1.0000   0.2202
  -4.250  -0.3729   0.02385   0.01352  -0.0351   1.0000   0.2502
  -4.000  -0.3494   0.02233   0.01207  -0.0339   1.0000   0.2881
  -3.750  -0.3276   0.02086   0.01088  -0.0325   1.0000   0.3395
  -3.500  -0.3065   0.01926   0.00985  -0.0309   1.0000   0.4238
  -3.250  -0.2955   0.01804   0.00988  -0.0258   1.0000   0.5819
  -3.000  -0.2951   0.01824   0.01051  -0.0168   1.0000   0.7275
  -2.750  -0.2970   0.01839   0.01074  -0.0074   1.0000   0.8088
  -2.500  -0.2904   0.01834   0.01062   0.0002   1.0000   0.8813
  -2.250  -0.0736   0.01843   0.00925  -0.0308   1.0000   1.0000
  -2.000  -0.0699   0.01801   0.00876  -0.0284   1.0000   1.0000
  -1.750  -0.0675   0.01766   0.00835  -0.0255   1.0000   1.0000
  -1.500  -0.0669   0.01735   0.00801  -0.0223   1.0000   1.0000
  -1.250  -0.0681   0.01709   0.00771  -0.0187   1.0000   1.0000
  -1.000  -0.0693   0.01687   0.00745  -0.0152   1.0000   1.0000
  -0.750  -0.0632   0.01675   0.00725  -0.0129   1.0000   1.0000
  -0.500  -0.0491   0.01676   0.00713  -0.0120   1.0000   1.0000
  -0.250  -0.0310   0.01687   0.00711  -0.0117   1.0000   1.0000
   0.000  -0.0111   0.01705   0.00718  -0.0117   1.0000   1.0000
   0.250   0.0095   0.01731   0.00734  -0.0118   1.0000   1.0000
   0.500   0.0301   0.01763   0.00758  -0.0120   1.0000   1.0000
   0.750   0.0505   0.01803   0.00790  -0.0122   1.0000   1.0000
   1.000   0.0705   0.01849   0.00831  -0.0125   1.0000   1.0000
   1.250   0.0899   0.01902   0.00881  -0.0128   1.0000   1.0000
   1.500   0.1088   0.01964   0.00941  -0.0131   1.0000   1.0000
   1.750   0.1270   0.02034   0.01010  -0.0135   1.0000   1.0000
   2.000   0.1567   0.02133   0.01112  -0.0162   0.9945   1.0000
   2.250   0.2233   0.02264   0.01253  -0.0253   0.9685   1.0000
   2.500   0.2871   0.02356   0.01360  -0.0330   0.9417   1.0000
   2.750   0.3491   0.02412   0.01434  -0.0398   0.9138   1.0000
   3.000   0.4104   0.02434   0.01481  -0.0456   0.8847   1.0000
   3.250   0.4734   0.02415   0.01490  -0.0508   0.8549   1.0000
   3.500   0.5315   0.02370   0.01475  -0.0543   0.8235   1.0000
   3.750   0.5832   0.02311   0.01441  -0.0559   0.7901   1.0000
   4.000   0.6283   0.02253   0.01400  -0.0559   0.7545   1.0000
   4.250   0.6613   0.02231   0.01392  -0.0542   0.7144   1.0000
   4.500   0.6898   0.02226   0.01391  -0.0520   0.6715   1.0000
   4.750   0.7161   0.02232   0.01393  -0.0494   0.6263   1.0000
   5.000   0.7398   0.02255   0.01412  -0.0468   0.5781   1.0000
   5.250   0.7618   0.02296   0.01440  -0.0441   0.5265   1.0000
   5.500   0.7827   0.02355   0.01480  -0.0415   0.4726   1.0000
   5.750   0.8027   0.02432   0.01533  -0.0390   0.4170   1.0000
   6.000   0.8218   0.02534   0.01608  -0.0367   0.3609   1.0000
   6.250   0.8402   0.02663   0.01707  -0.0345   0.3062   1.0000
   6.500   0.8587   0.02829   0.01855  -0.0325   0.2562   1.0000
   6.750   0.8779   0.03017   0.02023  -0.0308   0.2135   1.0000
   7.000   0.8978   0.03219   0.02207  -0.0293   0.1790   1.0000
   7.250   0.9179   0.03456   0.02451  -0.0280   0.1534   1.0000
   7.500   0.9400   0.03714   0.02709  -0.0270   0.1359   1.0000
   7.750   0.9591   0.04016   0.03053  -0.0256   0.1248   1.0000
   8.000   0.9772   0.04388   0.03460  -0.0244   0.1188   1.0000
   8.250   0.9886   0.04755   0.03888  -0.0227   0.1137   1.0000
   8.500   1.0081   0.05095   0.04217  -0.0222   0.1073   1.0000
   8.750   1.0122   0.05539   0.04726  -0.0204   0.1064   1.0000
   9.000   1.0147   0.06023   0.05257  -0.0190   0.1065   1.0000
   9.250   1.0146   0.06537   0.05807  -0.0179   0.1070   1.0000
   9.500   0.9841   0.07123   0.06462  -0.0168   0.1104   1.0000
   9.750   0.9445   0.07784   0.07153  -0.0172   0.1142   1.0000
  10.000   0.9172   0.08401   0.07777  -0.0188   0.1169   1.0000
  10.250   0.9017   0.09047   0.08424  -0.0215   0.1192   1.0000
  10.500   0.8415   0.10741   0.10104  -0.0371   0.1381   1.0000
  10.750   0.8561   0.11087   0.10459  -0.0355   0.1352   1.0000
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