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NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il)
Reynolds number: 100,000
Max Cl/Cd: 36.16 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ms317-il-100000.txt
Download as CSV file: xf-ms317-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY MS(1)-0317 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.6573   0.08404   0.07815  -0.0662   1.0000   0.0889
 -12.500  -0.6703   0.07843   0.07250  -0.0678   1.0000   0.0883
 -12.250  -0.6941   0.07265   0.06663  -0.0693   1.0000   0.0875
 -12.000  -0.7240   0.06736   0.06120  -0.0699   1.0000   0.0867
 -11.750  -0.7560   0.06304   0.05673  -0.0687   1.0000   0.0860
 -11.500  -0.7901   0.06006   0.05364  -0.0649   1.0000   0.0853
 -11.250  -0.8200   0.05755   0.05099  -0.0604   1.0000   0.0849
 -11.000  -0.8458   0.05534   0.04862  -0.0554   1.0000   0.0846
 -10.750  -0.8672   0.05319   0.04628  -0.0506   1.0000   0.0845
 -10.500  -0.8825   0.05095   0.04382  -0.0464   1.0000   0.0846
 -10.250  -0.8918   0.04868   0.04129  -0.0428   1.0000   0.0850
 -10.000  -0.8956   0.04646   0.03879  -0.0398   1.0000   0.0858
  -9.750  -0.8957   0.04433   0.03631  -0.0372   1.0000   0.0872
  -9.500  -0.8928   0.04230   0.03382  -0.0350   1.0000   0.0888
  -9.250  -0.8810   0.04032   0.03176  -0.0336   1.0000   0.0907
  -9.000  -0.8665   0.03904   0.03049  -0.0323   1.0000   0.0928
  -8.750  -0.8519   0.03764   0.02894  -0.0310   1.0000   0.0951
  -8.500  -0.8368   0.03626   0.02725  -0.0298   1.0000   0.0982
  -8.250  -0.8196   0.03482   0.02571  -0.0289   1.0000   0.1015
  -8.000  -0.8016   0.03386   0.02478  -0.0280   1.0000   0.1052
  -7.750  -0.7794   0.03281   0.02351  -0.0277   0.9992   0.1099
  -7.500  -0.7457   0.03158   0.02238  -0.0295   0.9957   0.1162
  -7.250  -0.7094   0.03059   0.02122  -0.0317   0.9921   0.1246
  -7.000  -0.6777   0.02967   0.02045  -0.0331   0.9877   0.1338
  -6.750  -0.6442   0.02876   0.01964  -0.0348   0.9837   0.1452
  -6.500  -0.6086   0.02797   0.01895  -0.0370   0.9806   0.1599
  -6.250  -0.5807   0.02722   0.01832  -0.0378   0.9759   0.1759
  -6.000  -0.5483   0.02650   0.01772  -0.0395   0.9714   0.1981
  -5.750  -0.5121   0.02565   0.01719  -0.0420   0.9678   0.2296
  -5.500  -0.4820   0.02471   0.01666  -0.0437   0.9637   0.2775
  -5.250  -0.4525   0.02317   0.01614  -0.0458   0.9597   0.3921
  -5.000  -0.4283   0.02368   0.01766  -0.0438   0.9549   0.5553
  -4.750  -0.3960   0.02514   0.01911  -0.0430   0.9503   0.6129
  -4.500  -0.3793   0.02625   0.02014  -0.0401   0.9436   0.6398
  -4.250  -0.3526   0.02743   0.02121  -0.0389   0.9388   0.6633
  -4.000  -0.3254   0.02895   0.02268  -0.0366   0.9348   0.6780
  -3.750  -0.3154   0.02996   0.02366  -0.0321   0.9279   0.6899
  -3.500  -0.2931   0.03084   0.02447  -0.0301   0.9225   0.7052
  -3.250  -0.2631   0.03170   0.02523  -0.0297   0.9184   0.7217
  -3.000  -0.2512   0.03273   0.02626  -0.0247   0.9128   0.7302
  -2.750  -0.2362   0.03330   0.02678  -0.0219   0.9067   0.7446
  -2.500  -0.2106   0.03392   0.02733  -0.0210   0.9020   0.7609
  -2.250  -0.1833   0.03471   0.02810  -0.0183   0.8983   0.7720
  -2.000  -0.1790   0.03496   0.02832  -0.0145   0.8912   0.7841
  -1.750  -0.1576   0.03524   0.02853  -0.0137   0.8855   0.7981
  -1.500  -0.1312   0.03554   0.02881  -0.0117   0.8811   0.8088
  -1.250  -0.1123   0.03574   0.02897  -0.0100   0.8753   0.8215
  -1.000  -0.0999   0.03588   0.02907  -0.0080   0.8676   0.8349
  -0.750  -0.0705   0.03588   0.02904  -0.0071   0.8625   0.8449
  -0.500  -0.0404   0.03588   0.02899  -0.0080   0.8571   0.8543
  -0.250  -0.0335   0.03588   0.02898  -0.0051   0.8482   0.8616
   0.000   0.0048   0.03578   0.02883  -0.0078   0.8425   0.8680
   0.250   0.0253   0.03571   0.02874  -0.0070   0.8346   0.8728
   0.500   0.0499   0.03561   0.02862  -0.0071   0.8260   0.8782
   0.750   0.0996   0.03534   0.02831  -0.0110   0.8210   0.8825
   1.000   0.1059   0.03541   0.02839  -0.0085   0.8087   0.8876
   1.250   0.1567   0.03486   0.02781  -0.0118   0.8024   0.8912
   1.500   0.1720   0.03485   0.02782  -0.0105   0.7896   0.8958
   1.750   0.2377   0.03371   0.02665  -0.0155   0.7826   0.8989
   2.000   0.2582   0.03331   0.02627  -0.0143   0.7682   0.9028
   2.250   0.3384   0.03133   0.02427  -0.0204   0.7631   0.9043
   2.500   0.3553   0.03106   0.02403  -0.0187   0.7490   0.9088
   2.750   0.4180   0.02927   0.02224  -0.0224   0.7439   0.9116
   3.000   0.4383   0.02885   0.02185  -0.0211   0.7302   0.9154
   3.250   0.4973   0.02693   0.01993  -0.0241   0.7239   0.9174
   3.500   0.5213   0.02625   0.01929  -0.0229   0.7093   0.9214
   3.750   0.5571   0.02514   0.01821  -0.0231   0.6970   0.9251
   4.000   0.6013   0.02370   0.01674  -0.0244   0.6850   0.9281
   4.250   0.6286   0.02284   0.01591  -0.0236   0.6671   0.9315
   4.500   0.6604   0.02185   0.01493  -0.0233   0.6469   0.9353
   4.750   0.6772   0.02134   0.01449  -0.0211   0.6196   0.9399
   5.000   0.6995   0.02069   0.01380  -0.0196   0.5846   0.9436
   5.250   0.7203   0.02017   0.01309  -0.0177   0.5269   0.9474
   5.500   0.7329   0.02027   0.01259  -0.0146   0.4383   0.9524
   5.750   0.7382   0.02113   0.01281  -0.0113   0.3696   0.9576
   6.000   0.7506   0.02204   0.01332  -0.0094   0.3234   0.9623
   6.250   0.7680   0.02291   0.01384  -0.0085   0.2941   0.9669
   6.500   0.7919   0.02371   0.01444  -0.0086   0.2719   0.9713
   6.750   0.8210   0.02454   0.01509  -0.0096   0.2549   0.9761
   7.000   0.8529   0.02544   0.01576  -0.0111   0.2414   0.9811
   7.250   0.8862   0.02621   0.01655  -0.0129   0.2297   0.9858
   7.500   0.9230   0.02721   0.01746  -0.0153   0.2208   0.9905
   7.750   0.9577   0.02808   0.01834  -0.0173   0.2131   0.9961
   8.000   0.9929   0.02922   0.01927  -0.0193   0.2068   1.0000
   8.250   1.0129   0.02998   0.02022  -0.0188   0.2020   1.0000
   8.500   1.0399   0.03092   0.02122  -0.0196   0.1969   1.0000
   8.750   1.0731   0.03209   0.02230  -0.0214   0.1924   1.0000
   9.000   1.1063   0.03363   0.02387  -0.0232   0.1888   1.0000
   9.250   1.1308   0.03483   0.02531  -0.0237   0.1854   1.0000
   9.500   1.1573   0.03612   0.02676  -0.0246   0.1817   1.0000
   9.750   1.1855   0.03746   0.02817  -0.0258   0.1783   1.0000
  10.000   1.2186   0.03915   0.02982  -0.0277   0.1753   1.0000
  10.250   1.2442   0.04123   0.03208  -0.0287   0.1728   1.0000
  10.500   1.2604   0.04295   0.03416  -0.0283   0.1704   1.0000
  10.750   1.2772   0.04487   0.03636  -0.0282   0.1679   1.0000
  11.000   1.2952   0.04685   0.03858  -0.0282   0.1655   1.0000
  11.250   1.3177   0.04869   0.04052  -0.0288   0.1629   1.0000
  11.500   1.3427   0.05064   0.04249  -0.0299   0.1603   1.0000
  11.750   1.3622   0.05376   0.04571  -0.0306   0.1581   1.0000
  12.000   1.3552   0.05643   0.04882  -0.0280   0.1568   1.0000
  12.250   1.3409   0.05943   0.05220  -0.0249   0.1557   1.0000
  12.500   1.3195   0.06291   0.05604  -0.0217   0.1547   1.0000
  12.750   1.2910   0.06720   0.06066  -0.0191   0.1540   1.0000
  13.000   1.2513   0.07282   0.06661  -0.0173   0.1538   1.0000
  13.250   1.1932   0.08103   0.07517  -0.0170   0.1544   1.0000
  13.500   1.1068   0.09462   0.08911  -0.0205   0.1563   1.0000
  13.750   1.0321   0.11124   0.10592  -0.0276   0.1580   1.0000
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