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S1210 12% (s1210-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S1210 12% (s1210-il)
Reynolds number: 500,000
Max Cl/Cd: 115.01 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1210-il-500000-n5.txt
Download as CSV file: xf-s1210-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1210 12%                                       
  
 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  -0.0743   0.10232   0.09989  -0.0749   0.9643   0.0123
  -9.000  -0.0634   0.09876   0.09633  -0.0773   0.9608   0.0119
  -8.750  -0.0654   0.09323   0.09082  -0.0793   0.9540   0.0106
  -8.500  -0.0530   0.09076   0.08836  -0.0809   0.9486   0.0109
  -8.250  -0.0460   0.08845   0.08607  -0.0816   0.9390   0.0128
  -8.000  -0.0357   0.08536   0.08298  -0.0834   0.9315   0.0126
  -7.500  -0.0138   0.07693   0.07454  -0.0900   0.9118   0.0114
  -7.000   0.0235   0.02364   0.02008  -0.1777   0.8745   0.0106
  -6.750   0.1059   0.02001   0.01600  -0.1952   0.8599   0.0110
  -6.500   0.1774   0.01789   0.01348  -0.2073   0.8389   0.0116
  -6.250   0.2436   0.01596   0.01105  -0.2176   0.8111   0.0120
  -6.000   0.2918   0.01483   0.00951  -0.2230   0.7802   0.0122
  -5.750   0.3290   0.01410   0.00847  -0.2256   0.7508   0.0125
  -5.500   0.3630   0.01358   0.00768  -0.2273   0.7240   0.0128
  -5.250   0.3957   0.01319   0.00705  -0.2287   0.6990   0.0131
  -5.000   0.4279   0.01290   0.00655  -0.2298   0.6767   0.0133
  -4.750   0.4648   0.01235   0.00585  -0.2322   0.6565   0.0138
  -4.500   0.4993   0.01204   0.00540  -0.2339   0.6389   0.0142
  -4.250   0.5332   0.01181   0.00503  -0.2354   0.6239   0.0147
  -4.000   0.5661   0.01164   0.00475  -0.2366   0.6103   0.0155
  -3.750   0.5991   0.01149   0.00447  -0.2377   0.5977   0.0163
  -3.500   0.6322   0.01134   0.00420  -0.2389   0.5864   0.0168
  -3.250   0.6657   0.01119   0.00393  -0.2401   0.5762   0.0175
  -3.000   0.6979   0.01110   0.00374  -0.2410   0.5663   0.0187
  -2.750   0.7293   0.01105   0.00360  -0.2417   0.5575   0.0203
  -2.500   0.7606   0.01101   0.00349  -0.2424   0.5484   0.0242
  -2.250   0.7965   0.01077   0.00334  -0.2443   0.5401   0.0763
  -2.000   0.8345   0.01046   0.00334  -0.2469   0.5320   0.2138
  -1.750   0.8635   0.01053   0.00340  -0.2470   0.5256   0.2389
  -1.500   0.8920   0.01063   0.00346  -0.2469   0.5191   0.2538
  -1.000   0.9492   0.01082   0.00358  -0.2469   0.5076   0.2725
  -0.750   0.9779   0.01091   0.00363  -0.2470   0.5016   0.2775
  -0.500   1.0061   0.01102   0.00368  -0.2469   0.4962   0.2808
  -0.250   1.0348   0.01110   0.00373  -0.2469   0.4914   0.2845
   0.000   1.0635   0.01119   0.00380  -0.2469   0.4866   0.2883
   0.250   1.0918   0.01130   0.00388  -0.2469   0.4821   0.2922
   0.500   1.1202   0.01140   0.00397  -0.2469   0.4778   0.2965
   0.750   1.1486   0.01150   0.00406  -0.2469   0.4734   0.3009
   1.000   1.1769   0.01161   0.00416  -0.2468   0.4692   0.3056
   1.250   1.2048   0.01175   0.00429  -0.2468   0.4652   0.3112
   1.500   1.2329   0.01186   0.00440  -0.2467   0.4614   0.3173
   1.750   1.2611   0.01196   0.00453  -0.2467   0.4565   0.3240
   2.000   1.2885   0.01212   0.00467  -0.2465   0.4502   0.3324
   2.250   1.3161   0.01225   0.00481  -0.2463   0.4444   0.3408
   2.500   1.3438   0.01238   0.00496  -0.2462   0.4393   0.3503
   2.750   1.3713   0.01253   0.00513  -0.2461   0.4351   0.3603
   3.000   1.3984   0.01270   0.00531  -0.2459   0.4309   0.3713
   3.250   1.4261   0.01281   0.00548  -0.2458   0.4256   0.3839
   3.500   1.4530   0.01298   0.00566  -0.2455   0.4190   0.3974
   3.750   1.4799   0.01316   0.00587  -0.2453   0.4133   0.4121
   4.000   1.5071   0.01330   0.00606  -0.2451   0.4064   0.4296
   4.250   1.5331   0.01353   0.00629  -0.2447   0.3989   0.4493
   4.500   1.5602   0.01367   0.00650  -0.2445   0.3915   0.4703
   4.750   1.5863   0.01388   0.00676  -0.2441   0.3843   0.4921
   5.000   1.6131   0.01405   0.00699  -0.2439   0.3769   0.5162
   5.250   1.6390   0.01428   0.00726  -0.2435   0.3689   0.5423
   5.500   1.6653   0.01448   0.00754  -0.2432   0.3599   0.5712
   5.750   1.6906   0.01475   0.00785  -0.2427   0.3469   0.6051
   6.000   1.7152   0.01509   0.00821  -0.2421   0.3288   0.6457
   6.250   1.7385   0.01557   0.00867  -0.2413   0.3069   0.6939
   6.500   1.7609   0.01610   0.00919  -0.2404   0.2847   0.7493
   6.750   1.7810   0.01668   0.00978  -0.2389   0.2631   0.8253
   7.000   1.7906   0.01707   0.01020  -0.2352   0.2467   1.0000
   7.250   1.8095   0.01776   0.01081  -0.2336   0.2300   1.0000
   7.750   1.8452   0.01910   0.01204  -0.2299   0.2024   1.0000
   8.000   1.8623   0.01976   0.01268  -0.2280   0.1906   1.0000
   8.250   1.8785   0.02047   0.01336  -0.2259   0.1791   1.0000
   8.500   1.8940   0.02124   0.01410  -0.2237   0.1679   1.0000
   8.750   1.9083   0.02209   0.01490  -0.2214   0.1563   1.0000
   9.000   1.9231   0.02287   0.01569  -0.2192   0.1472   1.0000
   9.250   1.9371   0.02372   0.01654  -0.2169   0.1400   1.0000
   9.500   1.9512   0.02456   0.01740  -0.2146   0.1332   1.0000
   9.750   1.9634   0.02553   0.01838  -0.2121   0.1273   1.0000
  10.000   1.9760   0.02647   0.01935  -0.2097   0.1211   1.0000
  10.250   1.9862   0.02760   0.02050  -0.2070   0.1156   1.0000
  10.500   1.9978   0.02864   0.02160  -0.2046   0.1114   1.0000
  10.750   2.0073   0.02986   0.02285  -0.2020   0.1062   1.0000
  11.000   2.0144   0.03129   0.02430  -0.1992   0.1016   1.0000
  11.250   2.0243   0.03251   0.02561  -0.1969   0.0984   1.0000
  11.500   2.0317   0.03399   0.02713  -0.1944   0.0946   1.0000
  11.750   2.0369   0.03570   0.02890  -0.1918   0.0912   1.0000
  12.000   2.0423   0.03747   0.03074  -0.1894   0.0884   1.0000
  12.250   2.0486   0.03921   0.03257  -0.1873   0.0855   1.0000
  12.500   2.0522   0.04128   0.03470  -0.1851   0.0821   1.0000
  12.750   2.0524   0.04382   0.03729  -0.1829   0.0784   1.0000
  13.000   2.0551   0.04620   0.03975  -0.1811   0.0751   1.0000
  13.250   2.0559   0.04894   0.04255  -0.1795   0.0707   1.0000
  13.500   2.0542   0.05207   0.04574  -0.1781   0.0674   1.0000
  13.750   2.0541   0.05519   0.04896  -0.1769   0.0643   1.0000
  14.000   2.0537   0.05846   0.05232  -0.1760   0.0614   1.0000
  14.250   2.0521   0.06199   0.05596  -0.1752   0.0594   1.0000
  14.500   2.0479   0.06603   0.06007  -0.1747   0.0569   1.0000
  14.750   2.0446   0.07002   0.06417  -0.1743   0.0543   1.0000
  15.000   2.0381   0.07460   0.06882  -0.1741   0.0494   1.0000
  15.250   2.0307   0.07943   0.07373  -0.1742   0.0460   1.0000
  15.500   2.0187   0.08507   0.07940  -0.1745   0.0397   1.0000
  15.750   2.0093   0.09035   0.08477  -0.1750   0.0357   1.0000
  16.000   1.9931   0.09685   0.09130  -0.1758   0.0296   1.0000
  16.250   1.9812   0.10274   0.09726  -0.1768   0.0259   1.0000
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