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NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il)
Reynolds number: 200,000
Max Cl/Cd: 55.55 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ms313-il-200000.txt
Download as CSV file: xf-ms313-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3624   0.09786   0.09436  -0.0427   1.0000   0.0737
 -10.750  -0.5235   0.08941   0.08577  -0.0493   1.0000   0.0696
 -10.500  -0.5066   0.08917   0.08554  -0.0459   1.0000   0.0706
 -10.250  -0.5009   0.08635   0.08275  -0.0462   1.0000   0.0721
 -10.000  -0.5099   0.08019   0.07663  -0.0506   1.0000   0.0736
  -9.750  -0.5424   0.07206   0.06849  -0.0570   1.0000   0.0739
  -9.500  -0.5850   0.06849   0.06494  -0.0554   1.0000   0.0734
  -9.250  -0.6290   0.06692   0.06338  -0.0500   1.0000   0.0728
  -9.000  -0.6562   0.06498   0.06139  -0.0459   1.0000   0.0731
  -8.750  -0.7239   0.04782   0.04292  -0.0451   0.9974   0.0471
  -8.500  -0.7044   0.04205   0.03669  -0.0479   0.9941   0.0454
  -8.250  -0.6857   0.03503   0.02872  -0.0496   0.9904   0.0428
  -8.000  -0.6578   0.03143   0.02455  -0.0511   0.9874   0.0426
  -7.750  -0.6258   0.02941   0.02233  -0.0529   0.9850   0.0434
  -7.500  -0.5915   0.02771   0.02045  -0.0549   0.9831   0.0448
  -7.250  -0.5615   0.02642   0.01892  -0.0558   0.9793   0.0470
  -7.000  -0.5289   0.02528   0.01746  -0.0570   0.9759   0.0486
  -6.750  -0.4974   0.02331   0.01547  -0.0582   0.9737   0.0505
  -6.500  -0.4628   0.02237   0.01452  -0.0600   0.9717   0.0533
  -6.250  -0.4261   0.02165   0.01368  -0.0620   0.9700   0.0570
  -6.000  -0.4005   0.02050   0.01256  -0.0619   0.9655   0.0600
  -5.750  -0.3688   0.01977   0.01188  -0.0631   0.9620   0.0643
  -5.500  -0.3346   0.01895   0.01106  -0.0648   0.9595   0.0704
  -5.250  -0.2985   0.01827   0.01041  -0.0669   0.9575   0.0781
  -5.000  -0.2608   0.01747   0.00969  -0.0695   0.9559   0.0900
  -4.750  -0.2324   0.01687   0.00915  -0.0703   0.9514   0.1068
  -4.500  -0.1986   0.01574   0.00844  -0.0727   0.9480   0.1650
  -4.250  -0.1582   0.01350   0.00795  -0.0777   0.9470   0.5140
  -4.000  -0.1245   0.01358   0.00832  -0.0785   0.9442   0.6134
  -3.750  -0.0883   0.01385   0.00859  -0.0797   0.9420   0.6531
  -3.500  -0.0522   0.01417   0.00887  -0.0808   0.9400   0.6789
  -3.250  -0.0325   0.01461   0.00930  -0.0789   0.9335   0.6955
  -3.000  -0.0031   0.01496   0.00962  -0.0787   0.9296   0.7113
  -2.750   0.0291   0.01527   0.00990  -0.0790   0.9267   0.7264
  -2.500   0.0588   0.01572   0.01036  -0.0783   0.9242   0.7417
  -2.250   0.0725   0.01632   0.01101  -0.0746   0.9173   0.7533
  -2.000   0.0995   0.01655   0.01122  -0.0739   0.9131   0.7635
  -1.750   0.1305   0.01664   0.01129  -0.0741   0.9100   0.7711
  -1.500   0.1635   0.01668   0.01129  -0.0747   0.9075   0.7792
  -1.250   0.1802   0.01700   0.01163  -0.0723   0.8999   0.7873
  -1.000   0.2109   0.01697   0.01158  -0.0727   0.8955   0.7950
  -0.750   0.2434   0.01680   0.01139  -0.0729   0.8917   0.7994
  -0.500   0.2702   0.01670   0.01128  -0.0725   0.8830   0.8049
  -0.250   0.3079   0.01606   0.01057  -0.0734   0.8750   0.8098
   0.000   0.3319   0.01565   0.01015  -0.0715   0.8623   0.8134
   0.250   0.3595   0.01525   0.00972  -0.0704   0.8521   0.8178
   0.500   0.3899   0.01493   0.00936  -0.0705   0.8431   0.8228
   0.750   0.4170   0.01470   0.00913  -0.0700   0.8336   0.8269
   1.000   0.4436   0.01440   0.00882  -0.0690   0.8251   0.8307
   1.250   0.4702   0.01421   0.00865  -0.0684   0.8142   0.8351
   1.500   0.5012   0.01394   0.00834  -0.0687   0.8041   0.8399
   1.750   0.5271   0.01366   0.00806  -0.0677   0.7923   0.8436
   2.000   0.5526   0.01344   0.00788  -0.0668   0.7788   0.8476
   2.250   0.5803   0.01323   0.00767  -0.0664   0.7641   0.8520
   2.500   0.6101   0.01304   0.00747  -0.0666   0.7469   0.8568
   2.750   0.6344   0.01281   0.00722  -0.0653   0.7265   0.8605
   3.000   0.6597   0.01265   0.00705  -0.0644   0.6975   0.8647
   3.250   0.6862   0.01257   0.00686  -0.0638   0.6526   0.8695
   3.500   0.7082   0.01275   0.00663  -0.0622   0.5621   0.8739
   3.750   0.7206   0.01364   0.00680  -0.0592   0.4371   0.8783
   4.000   0.7353   0.01470   0.00727  -0.0573   0.3370   0.8835
   4.250   0.7538   0.01559   0.00774  -0.0562   0.2714   0.8886
   4.500   0.7712   0.01623   0.00814  -0.0545   0.2361   0.8933
   4.750   0.7928   0.01679   0.00857  -0.0537   0.2128   0.8986
   5.000   0.8153   0.01733   0.00901  -0.0530   0.1972   0.9039
   5.250   0.8342   0.01783   0.00942  -0.0515   0.1865   0.9095
   5.500   0.8575   0.01830   0.00986  -0.0510   0.1773   0.9154
   5.750   0.8782   0.01881   0.01033  -0.0499   0.1701   0.9212
   6.000   0.9000   0.01918   0.01072  -0.0489   0.1636   0.9282
   6.250   0.9209   0.01987   0.01130  -0.0479   0.1578   0.9351
   6.500   0.9435   0.02019   0.01172  -0.0471   0.1534   0.9430
   6.750   0.9652   0.02058   0.01215  -0.0461   0.1492   0.9519
   7.000   0.9875   0.02109   0.01263  -0.0453   0.1456   0.9632
   7.250   1.0146   0.02192   0.01343  -0.0456   0.1420   0.9779
   7.500   1.0441   0.02244   0.01408  -0.0464   0.1385   1.0000
   7.750   1.0744   0.02314   0.01482  -0.0476   0.1348   1.0000
   8.000   1.1051   0.02395   0.01562  -0.0488   0.1316   1.0000
   8.250   1.1384   0.02539   0.01699  -0.0505   0.1284   1.0000
   8.500   1.1671   0.02615   0.01791  -0.0513   0.1261   1.0000
   8.750   1.1953   0.02695   0.01885  -0.0519   0.1232   1.0000
   9.000   1.2230   0.02780   0.01979  -0.0526   0.1203   1.0000
   9.250   1.2504   0.02864   0.02064  -0.0532   0.1174   1.0000
   9.500   1.2810   0.03050   0.02244  -0.0546   0.1140   1.0000
   9.750   1.3034   0.03117   0.02334  -0.0542   0.1119   1.0000
  10.000   1.3260   0.03207   0.02443  -0.0539   0.1092   1.0000
  10.250   1.3481   0.03296   0.02545  -0.0536   0.1064   1.0000
  10.500   1.3708   0.03380   0.02630  -0.0534   0.1038   1.0000
  10.750   1.3977   0.03588   0.02832  -0.0542   0.1007   1.0000
  11.000   1.4120   0.03674   0.02947  -0.0526   0.0987   1.0000
  11.250   1.4267   0.03777   0.03074  -0.0512   0.0961   1.0000
  11.500   1.4418   0.03872   0.03183  -0.0499   0.0935   1.0000
  11.750   1.4585   0.03950   0.03263  -0.0488   0.0911   1.0000
  12.000   1.4816   0.04171   0.03476  -0.0492   0.0881   1.0000
  12.250   1.4836   0.04270   0.03607  -0.0460   0.0864   1.0000
  12.500   1.4844   0.04400   0.03763  -0.0428   0.0843   1.0000
  12.750   1.4873   0.04524   0.03904  -0.0401   0.0822   1.0000
  13.000   1.4921   0.04629   0.04018  -0.0378   0.0802   1.0000
  13.250   1.5049   0.04709   0.04093  -0.0365   0.0783   1.0000
  13.500   1.5105   0.04959   0.04352  -0.0351   0.0762   1.0000
  13.750   1.4980   0.05182   0.04606  -0.0318   0.0749   1.0000
  14.000   1.4866   0.05445   0.04898  -0.0292   0.0734   1.0000
  14.250   1.4788   0.05700   0.05174  -0.0274   0.0718   1.0000
  14.500   1.4733   0.05944   0.05433  -0.0260   0.0703   1.0000
  14.750   1.4748   0.06123   0.05619  -0.0252   0.0688   1.0000
  15.000   1.4891   0.06212   0.05698  -0.0247   0.0671   1.0000
  15.250   1.4774   0.06617   0.06118  -0.0239   0.0659   1.0000
  15.500   1.4509   0.07129   0.06663  -0.0236   0.0653   1.0000
  15.750   1.4200   0.07759   0.07325  -0.0245   0.0648   1.0000
  16.000   1.3829   0.08544   0.08141  -0.0269   0.0645   1.0000
  16.250   1.3344   0.09630   0.09257  -0.0321   0.0646   1.0000
  16.500   1.2567   0.11486   0.11147  -0.0436   0.0655   1.0000
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