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NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il)
Reynolds number: 100,000
Max Cl/Cd: 46.41 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ms313-il-100000.txt
Download as CSV file: xf-ms313-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY MS(1)-0313 AIRFOIL                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5181   0.09764   0.09269  -0.0451   1.0000   0.1528
  -9.750  -0.4548   0.09688   0.09182  -0.0351   1.0000   0.1586
  -9.500  -0.4787   0.09248   0.08755  -0.0396   1.0000   0.1673
  -9.250  -0.4714   0.08884   0.08395  -0.0384   1.0000   0.1724
  -9.000  -0.4656   0.08625   0.08140  -0.0374   1.0000   0.1790
  -8.750  -0.5326   0.08201   0.07740  -0.0395   1.0000   0.1832
  -8.500  -0.5056   0.07970   0.07510  -0.0360   1.0000   0.1901
  -8.250  -0.5322   0.07770   0.07322  -0.0326   1.0000   0.1933
  -8.000  -0.6871   0.05484   0.04882  -0.0410   1.0000   0.0947
  -7.750  -0.6839   0.04898   0.04200  -0.0397   1.0000   0.0800
  -7.500  -0.6717   0.04497   0.03783  -0.0389   1.0000   0.0791
  -7.250  -0.6572   0.04147   0.03407  -0.0383   1.0000   0.0779
  -7.000  -0.6397   0.03830   0.03054  -0.0378   1.0000   0.0769
  -6.750  -0.6196   0.03559   0.02742  -0.0374   1.0000   0.0767
  -6.500  -0.5978   0.03364   0.02502  -0.0369   1.0000   0.0786
  -6.250  -0.5743   0.03193   0.02288  -0.0366   1.0000   0.0805
  -6.000  -0.5502   0.02970   0.02058  -0.0365   1.0000   0.0827
  -5.750  -0.5263   0.02838   0.01919  -0.0362   1.0000   0.0857
  -5.500  -0.5021   0.02741   0.01805  -0.0358   1.0000   0.0907
  -5.250  -0.4774   0.02613   0.01668  -0.0354   1.0000   0.0952
  -5.000  -0.4534   0.02515   0.01578  -0.0351   1.0000   0.1012
  -4.750  -0.4287   0.02427   0.01488  -0.0348   1.0000   0.1095
  -4.500  -0.4038   0.02349   0.01419  -0.0347   1.0000   0.1201
  -4.250  -0.3777   0.02267   0.01350  -0.0349   1.0000   0.1363
  -4.000  -0.3488   0.02168   0.01282  -0.0359   1.0000   0.1669
  -3.750  -0.3101   0.01912   0.01299  -0.0389   1.0000   0.5984
  -3.500  -0.2948   0.02005   0.01392  -0.0355   1.0000   0.6759
  -3.250  -0.2819   0.02093   0.01477  -0.0316   1.0000   0.7101
  -3.000  -0.2721   0.02173   0.01556  -0.0269   1.0000   0.7338
  -2.750  -0.2591   0.02241   0.01617  -0.0233   1.0000   0.7575
  -2.500  -0.2426   0.02308   0.01680  -0.0201   0.9975   0.7787
  -2.250  -0.2217   0.02378   0.01745  -0.0174   0.9931   0.8000
  -2.000  -0.2026   0.02430   0.01790  -0.0147   0.9879   0.8249
  -1.750  -0.1889   0.02473   0.01832  -0.0101   0.9830   0.8488
  -1.500  -0.1733   0.02487   0.01840  -0.0071   0.9770   0.8718
  -1.250  -0.1490   0.02495   0.01842  -0.0061   0.9716   0.8883
  -1.000  -0.1278   0.02492   0.01832  -0.0049   0.9654   0.9035
  -0.750  -0.1018   0.02490   0.01823  -0.0047   0.9590   0.9178
  -0.500  -0.0701   0.02495   0.01820  -0.0059   0.9527   0.9274
  -0.250  -0.0398   0.02494   0.01814  -0.0072   0.9449   0.9355
   0.000   0.0013   0.02514   0.01827  -0.0104   0.9382   0.9428
   0.250   0.0323   0.02513   0.01822  -0.0119   0.9286   0.9501
   0.500   0.0740   0.02529   0.01833  -0.0151   0.9201   0.9568
   0.750   0.1165   0.02534   0.01836  -0.0185   0.9100   0.9629
   1.000   0.1561   0.02541   0.01842  -0.0213   0.8990   0.9693
   1.250   0.2130   0.02532   0.01832  -0.0265   0.8876   0.9734
   1.500   0.2827   0.02475   0.01775  -0.0332   0.8736   0.9751
   1.750   0.3390   0.02413   0.01716  -0.0376   0.8585   0.9780
   2.000   0.3940   0.02346   0.01653  -0.0418   0.8445   0.9811
   2.250   0.4490   0.02261   0.01573  -0.0457   0.8315   0.9838
   2.500   0.5096   0.02142   0.01461  -0.0500   0.8198   0.9851
   2.750   0.5676   0.02008   0.01332  -0.0537   0.8071   0.9869
   3.000   0.6111   0.01909   0.01242  -0.0553   0.7889   0.9912
   3.250   0.6501   0.01820   0.01161  -0.0563   0.7663   0.9960
   3.500   0.6886   0.01714   0.01058  -0.0568   0.7405   1.0000
   3.750   0.7036   0.01657   0.01004  -0.0537   0.7084   1.0000
   4.000   0.7159   0.01609   0.00954  -0.0501   0.6603   1.0000
   4.250   0.7301   0.01573   0.00869  -0.0463   0.5480   1.0000
   4.500   0.7315   0.01673   0.00867  -0.0413   0.4132   1.0000
   4.750   0.7396   0.01800   0.00926  -0.0386   0.3370   1.0000
   5.000   0.7582   0.01908   0.00995  -0.0377   0.2936   1.0000
   5.250   0.7821   0.02011   0.01066  -0.0378   0.2674   1.0000
   5.500   0.8095   0.02105   0.01144  -0.0384   0.2479   1.0000
   5.750   0.8385   0.02201   0.01225  -0.0393   0.2331   1.0000
   6.000   0.8691   0.02305   0.01309  -0.0405   0.2212   1.0000
   6.250   0.8997   0.02392   0.01404  -0.0415   0.2114   1.0000
   6.500   0.9328   0.02513   0.01510  -0.0431   0.2039   1.0000
   6.750   0.9632   0.02607   0.01618  -0.0440   0.1966   1.0000
   7.000   0.9959   0.02729   0.01724  -0.0455   0.1901   1.0000
   7.250   1.0261   0.02847   0.01861  -0.0465   0.1848   1.0000
   7.500   1.0560   0.02967   0.01995  -0.0474   0.1800   1.0000
   7.750   1.0868   0.03100   0.02126  -0.0485   0.1758   1.0000
   8.000   1.1160   0.03267   0.02304  -0.0494   0.1718   1.0000
   8.250   1.1412   0.03403   0.02470  -0.0495   0.1676   1.0000
   8.500   1.1678   0.03556   0.02640  -0.0499   0.1641   1.0000
   8.750   1.1944   0.03712   0.02806  -0.0504   0.1607   1.0000
   9.000   1.2199   0.03940   0.03041  -0.0509   0.1573   1.0000
   9.250   1.2362   0.04122   0.03270  -0.0498   0.1543   1.0000
   9.500   1.2533   0.04328   0.03511  -0.0489   0.1510   1.0000
   9.750   1.2737   0.04503   0.03701  -0.0486   0.1475   1.0000
  10.000   1.2996   0.04694   0.03882  -0.0492   0.1438   1.0000
  10.250   1.3068   0.04990   0.04221  -0.0473   0.1413   1.0000
  10.500   1.3064   0.05283   0.04565  -0.0446   0.1388   1.0000
  10.750   1.3057   0.05586   0.04907  -0.0421   0.1361   1.0000
  11.000   1.3082   0.05862   0.05209  -0.0401   0.1336   1.0000
  11.250   1.3441   0.05959   0.05282  -0.0415   0.1294   1.0000
  11.500   1.3371   0.06373   0.05723  -0.0391   0.1275   1.0000
  11.750   1.3098   0.06782   0.06177  -0.0347   0.1267   1.0000
  12.000   1.2766   0.07209   0.06634  -0.0304   0.1264   1.0000
  12.250   1.2396   0.07729   0.07182  -0.0276   0.1264   1.0000
  12.500   1.1997   0.08374   0.07849  -0.0266   0.1268   1.0000
  12.750   1.1589   0.09159   0.08651  -0.0277   0.1274   1.0000
  13.000   1.1219   0.10071   0.09575  -0.0304   0.1280   1.0000
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