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S1223 (s1223-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S1223 (s1223-il)
Reynolds number: 100,000
Max Cl/Cd: 59.16 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1223-il-100000-n5.txt
Download as CSV file: xf-s1223-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1223                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -6.500   0.0289   0.10370   0.09907  -0.0665   0.9166   0.0463
  -6.250   0.0326   0.10179   0.09720  -0.0682   0.9041   0.0470
  -6.000   0.0331   0.10022   0.09568  -0.0696   0.8903   0.0473
  -5.750   0.0499   0.09631   0.09180  -0.0695   0.8800   0.0479
  -5.500   0.0667   0.09311   0.08861  -0.0701   0.8696   0.0489
  -5.000   0.0803   0.08867   0.08423  -0.0696   0.8373   0.0511
  -4.750   0.0858   0.08647   0.08203  -0.0701   0.8198   0.0527
  -4.500   0.0947   0.08399   0.07954  -0.0745   0.8008   0.0542
  -4.250   0.1153   0.08020   0.07572  -0.0813   0.7816   0.0547
  -4.000   0.1397   0.07650   0.07194  -0.0801   0.7637   0.0559
  -3.750   0.1708   0.07279   0.06811  -0.0842   0.7423   0.0582
  -3.500   0.2143   0.06795   0.06310  -0.1009   0.7163   0.0629
  -3.250   0.2376   0.06512   0.06012  -0.0978   0.6911   0.0658
  -3.000   0.2930   0.06000   0.05475  -0.1157   0.6651   0.0731
  -2.500   0.3707   0.04916   0.04342  -0.1303   0.6235   0.0401
  -2.000   0.7660   0.02393   0.01508  -0.2296   0.5690   0.0381
  -1.750   0.8233   0.02281   0.01340  -0.2360   0.5536   0.0399
  -1.500   0.8701   0.02226   0.01257  -0.2400   0.5408   0.0431
  -1.250   0.9132   0.02198   0.01199  -0.2431   0.5293   0.0475
  -1.000   0.9550   0.02173   0.01164  -0.2461   0.5186   0.0511
  -0.750   0.9981   0.02166   0.01135  -0.2493   0.5091   0.0586
  -0.500   1.0410   0.02155   0.01111  -0.2525   0.5003   0.0712
  -0.250   1.0910   0.02132   0.01116  -0.2575   0.4922   0.1945
   0.000   1.1230   0.02174   0.01149  -0.2582   0.4861   0.2726
   0.250   1.1513   0.02219   0.01198  -0.2582   0.4795   0.3256
   0.500   1.1821   0.02246   0.01211  -0.2586   0.4734   0.3424
   1.000   1.2440   0.02300   0.01240  -0.2596   0.4623   0.3694
   1.250   1.2738   0.02325   0.01260  -0.2599   0.4570   0.3821
   1.500   1.3040   0.02355   0.01281  -0.2603   0.4525   0.3980
   1.750   1.3349   0.02391   0.01303  -0.2608   0.4488   0.4159
   2.000   1.3632   0.02419   0.01335  -0.2608   0.4443   0.4348
   2.250   1.3914   0.02450   0.01368  -0.2608   0.4397   0.4574
   2.500   1.4199   0.02483   0.01401  -0.2608   0.4355   0.4861
   2.750   1.4488   0.02517   0.01435  -0.2610   0.4318   0.5195
   3.000   1.4786   0.02556   0.01472  -0.2613   0.4287   0.5606
   3.250   1.5053   0.02590   0.01522  -0.2610   0.4251   0.6108
   3.500   1.5307   0.02621   0.01569  -0.2604   0.4214   0.6777
   3.750   1.5513   0.02640   0.01605  -0.2587   0.4179   0.7765
   4.000   1.5672   0.02649   0.01620  -0.2561   0.4149   1.0000
   4.250   1.5962   0.02700   0.01660  -0.2563   0.4120   1.0000
   4.500   1.6249   0.02756   0.01707  -0.2566   0.4093   1.0000
   4.750   1.6501   0.02811   0.01767  -0.2561   0.4061   1.0000
   5.000   1.6753   0.02867   0.01826  -0.2556   0.4027   1.0000
   5.250   1.7006   0.02921   0.01883  -0.2552   0.3994   1.0000
   5.500   1.7264   0.02975   0.01934  -0.2549   0.3964   1.0000
   5.750   1.7532   0.03030   0.01985  -0.2547   0.3938   1.0000
   6.000   1.7814   0.03090   0.02038  -0.2549   0.3915   1.0000
   6.250   1.8022   0.03157   0.02123  -0.2536   0.3884   1.0000
   6.500   1.8235   0.03224   0.02201  -0.2525   0.3851   1.0000
   6.750   1.8455   0.03289   0.02273  -0.2515   0.3818   1.0000
   7.000   1.8687   0.03350   0.02341  -0.2507   0.3789   1.0000
   7.250   1.8931   0.03408   0.02400  -0.2502   0.3761   1.0000
   7.500   1.9194   0.03466   0.02454  -0.2500   0.3735   1.0000
   7.750   1.9355   0.03550   0.02557  -0.2480   0.3701   1.0000
   8.000   1.9514   0.03631   0.02659  -0.2459   0.3665   1.0000
   8.250   1.9695   0.03704   0.02743  -0.2442   0.3629   1.0000
   8.500   1.9897   0.03767   0.02811  -0.2430   0.3596   1.0000
   8.750   2.0130   0.03821   0.02866  -0.2422   0.3566   1.0000
   9.000   2.0287   0.03904   0.02962  -0.2402   0.3533   1.0000
   9.250   2.0350   0.04010   0.03094  -0.2366   0.3492   1.0000
   9.500   2.0453   0.04099   0.03197  -0.2336   0.3454   1.0000
   9.750   2.0603   0.04166   0.03274  -0.2315   0.3418   1.0000
  10.000   2.0812   0.04218   0.03326  -0.2303   0.3387   1.0000
  10.250   2.0861   0.04336   0.03465  -0.2267   0.3351   1.0000
  10.500   2.0845   0.04481   0.03636  -0.2221   0.3308   1.0000
  10.750   2.0906   0.04590   0.03762  -0.2187   0.3266   1.0000
  11.000   2.1046   0.04655   0.03831  -0.2166   0.3227   1.0000
  11.250   2.1132   0.04756   0.03942  -0.2138   0.3188   1.0000
  11.500   2.1022   0.04979   0.04198  -0.2085   0.3141   1.0000
  11.750   2.1014   0.05142   0.04380  -0.2048   0.3094   1.0000
  12.000   2.1115   0.05232   0.04476  -0.2025   0.3052   1.0000
  12.250   2.1066   0.05444   0.04708  -0.1987   0.3007   1.0000
  12.500   2.0908   0.05759   0.05053  -0.1943   0.2955   1.0000
  12.750   2.0889   0.05964   0.05272  -0.1914   0.2907   1.0000
  13.000   2.0889   0.06158   0.05476  -0.1889   0.2859   1.0000
  13.250   2.0589   0.06690   0.06044  -0.1852   0.2803   1.0000
  13.500   2.0482   0.07041   0.06412  -0.1831   0.2749   1.0000
  13.750   2.0375   0.07425   0.06810  -0.1815   0.2698   1.0000
  14.000   1.9866   0.08410   0.07829  -0.1808   0.2635   1.0000
  14.250   1.9828   0.08762   0.08190  -0.1804   0.2580   1.0000
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