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NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il)
Reynolds number: 100,000
Max Cl/Cd: 39.46 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ms313-il-100000-n5.txt
Download as CSV file: xf-ms313-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.5512   0.08856   0.08310  -0.0462   1.0000   0.0332
 -11.250  -0.5908   0.07501   0.06947  -0.0563   1.0000   0.0325
 -11.000  -0.6254   0.06676   0.06105  -0.0617   1.0000   0.0321
 -10.750  -0.6540   0.06127   0.05540  -0.0636   1.0000   0.0319
 -10.500  -0.6806   0.05753   0.05151  -0.0626   1.0000   0.0318
 -10.250  -0.7025   0.05438   0.04820  -0.0603   1.0000   0.0318
 -10.000  -0.7194   0.05154   0.04515  -0.0574   1.0000   0.0319
  -9.750  -0.7321   0.04890   0.04228  -0.0542   1.0000   0.0320
  -9.500  -0.7402   0.04640   0.03951  -0.0511   1.0000   0.0325
  -9.250  -0.7440   0.04388   0.03665  -0.0484   1.0000   0.0332
  -9.000  -0.7412   0.04099   0.03327  -0.0466   0.9993   0.0342
  -8.750  -0.7172   0.03818   0.03007  -0.0483   0.9952   0.0353
  -8.500  -0.6904   0.03628   0.02800  -0.0497   0.9914   0.0363
  -8.250  -0.6628   0.03427   0.02575  -0.0510   0.9874   0.0374
  -8.000  -0.6332   0.03231   0.02349  -0.0524   0.9840   0.0388
  -7.750  -0.6040   0.03062   0.02137  -0.0534   0.9804   0.0410
  -7.500  -0.5762   0.02934   0.02011  -0.0544   0.9764   0.0429
  -7.250  -0.5458   0.02814   0.01881  -0.0555   0.9731   0.0449
  -7.000  -0.5136   0.02688   0.01738  -0.0568   0.9705   0.0472
  -6.750  -0.4856   0.02583   0.01627  -0.0574   0.9663   0.0500
  -6.500  -0.4567   0.02498   0.01544  -0.0582   0.9621   0.0534
  -6.250  -0.4256   0.02410   0.01445  -0.0592   0.9590   0.0571
  -6.000  -0.3934   0.02320   0.01360  -0.0608   0.9565   0.0617
  -5.750  -0.3635   0.02253   0.01286  -0.0617   0.9528   0.0677
  -5.500  -0.3359   0.02179   0.01218  -0.0623   0.9481   0.0742
  -5.250  -0.3042   0.02109   0.01149  -0.0637   0.9447   0.0841
  -5.000  -0.2713   0.02041   0.01087  -0.0653   0.9420   0.0988
  -4.750  -0.2373   0.01968   0.01027  -0.0672   0.9397   0.1254
  -4.500  -0.2123   0.01892   0.00984  -0.0676   0.9342   0.1798
  -4.250  -0.1821   0.01765   0.00934  -0.0696   0.9305   0.3264
  -4.000  -0.1540   0.01691   0.00960  -0.0699   0.9274   0.5203
  -3.750  -0.1241   0.01713   0.00999  -0.0696   0.9246   0.5995
  -3.500  -0.0976   0.01743   0.01024  -0.0690   0.9198   0.6394
  -3.250  -0.0722   0.01778   0.01056  -0.0680   0.9147   0.6673
  -3.000  -0.0442   0.01820   0.01093  -0.0673   0.9110   0.6948
  -2.750  -0.0173   0.01867   0.01138  -0.0660   0.9079   0.7162
  -2.500   0.0052   0.01898   0.01164  -0.0645   0.9024   0.7304
  -2.250   0.0324   0.01914   0.01170  -0.0644   0.8976   0.7422
  -2.000   0.0586   0.01932   0.01186  -0.0634   0.8938   0.7509
  -1.750   0.0906   0.01938   0.01184  -0.0640   0.8910   0.7615
  -1.500   0.1117   0.01955   0.01199  -0.0626   0.8849   0.7678
  -1.250   0.1418   0.01955   0.01193  -0.0634   0.8801   0.7747
  -1.000   0.1724   0.01953   0.01187  -0.0639   0.8764   0.7792
  -0.750   0.2047   0.01947   0.01178  -0.0646   0.8735   0.7838
  -0.500   0.2277   0.01960   0.01189  -0.0641   0.8657   0.7895
  -0.250   0.2591   0.01954   0.01181  -0.0648   0.8608   0.7943
   0.000   0.2918   0.01939   0.01165  -0.0653   0.8569   0.7981
   0.250   0.3154   0.01939   0.01166  -0.0645   0.8466   0.8030
   0.500   0.3523   0.01900   0.01123  -0.0657   0.8389   0.8080
   0.750   0.3801   0.01858   0.01081  -0.0647   0.8250   0.8117
   1.000   0.4070   0.01818   0.01040  -0.0636   0.8095   0.8157
   1.250   0.4347   0.01786   0.01006  -0.0629   0.7944   0.8205
   1.500   0.4633   0.01762   0.00983  -0.0627   0.7802   0.8254
   1.750   0.4885   0.01740   0.00963  -0.0616   0.7655   0.8291
   2.000   0.5148   0.01719   0.00945  -0.0608   0.7493   0.8336
   2.250   0.5426   0.01701   0.00928  -0.0605   0.7303   0.8386
   2.500   0.5696   0.01681   0.00907  -0.0598   0.7087   0.8428
   2.750   0.5932   0.01669   0.00898  -0.0586   0.6804   0.8472
   3.000   0.6192   0.01657   0.00880  -0.0578   0.6399   0.8522
   3.250   0.6467   0.01651   0.00846  -0.0571   0.5703   0.8570
   3.500   0.6661   0.01688   0.00826  -0.0549   0.4756   0.8612
   3.750   0.6835   0.01763   0.00851  -0.0531   0.3936   0.8665
   4.250   0.7219   0.01900   0.00927  -0.0506   0.2871   0.8769
   4.500   0.7423   0.01960   0.00967  -0.0496   0.2533   0.8826
   4.750   0.7645   0.02015   0.01010  -0.0490   0.2280   0.8885
   5.000   0.7846   0.02064   0.01049  -0.0478   0.2101   0.8943
   5.250   0.8068   0.02115   0.01095  -0.0471   0.1965   0.9006
   5.500   0.8273   0.02165   0.01140  -0.0460   0.1862   0.9071
   5.750   0.8485   0.02214   0.01189  -0.0451   0.1768   0.9147
   6.000   0.8691   0.02263   0.01237  -0.0440   0.1691   0.9225
   6.250   0.8906   0.02313   0.01288  -0.0432   0.1619   0.9313
   6.500   0.9106   0.02367   0.01341  -0.0421   0.1564   0.9419
   6.750   0.9336   0.02417   0.01398  -0.0416   0.1512   0.9555
   7.000   0.9578   0.02474   0.01458  -0.0414   0.1466   0.9808
   7.250   0.9838   0.02555   0.01533  -0.0419   0.1425   1.0000
   7.500   1.0114   0.02629   0.01617  -0.0425   0.1381   1.0000
   7.750   1.0381   0.02707   0.01700  -0.0429   0.1339   1.0000
   8.000   1.0642   0.02792   0.01785  -0.0433   0.1304   1.0000
   8.250   1.0913   0.02894   0.01882  -0.0439   0.1277   1.0000
   8.500   1.1180   0.02984   0.01989  -0.0442   0.1248   1.0000
   8.750   1.1436   0.03078   0.02095  -0.0445   0.1216   1.0000
   9.000   1.1683   0.03172   0.02196  -0.0446   0.1186   1.0000
   9.250   1.1927   0.03270   0.02294  -0.0447   0.1160   1.0000
   9.500   1.2187   0.03393   0.02416  -0.0451   0.1137   1.0000
   9.750   1.2407   0.03506   0.02557  -0.0447   0.1113   1.0000
  10.000   1.2616   0.03622   0.02694  -0.0442   0.1085   1.0000
  10.250   1.2814   0.03733   0.02818  -0.0437   0.1057   1.0000
  10.500   1.3012   0.03841   0.02932  -0.0432   0.1034   1.0000
  10.750   1.3227   0.03958   0.03047  -0.0430   0.1011   1.0000
  11.000   1.3366   0.04103   0.03219  -0.0417   0.0987   1.0000
  11.250   1.3479   0.04251   0.03397  -0.0401   0.0962   1.0000
  11.500   1.3573   0.04387   0.03554  -0.0382   0.0939   1.0000
  11.750   1.3673   0.04511   0.03690  -0.0366   0.0917   1.0000
  12.000   1.3795   0.04629   0.03814  -0.0353   0.0898   1.0000
  12.250   1.3943   0.04769   0.03952  -0.0344   0.0880   1.0000
  12.500   1.3900   0.04990   0.04214  -0.0316   0.0862   1.0000
  12.750   1.3859   0.05226   0.04483  -0.0293   0.0842   1.0000
  13.000   1.3829   0.05460   0.04744  -0.0275   0.0824   1.0000
  13.250   1.3811   0.05687   0.04990  -0.0259   0.0807   1.0000
  13.500   1.3820   0.05892   0.05207  -0.0248   0.0791   1.0000
  13.750   1.3885   0.06055   0.05374  -0.0239   0.0776   1.0000
  14.000   1.3896   0.06289   0.05615  -0.0231   0.0762   1.0000
  14.250   1.3656   0.06774   0.06141  -0.0223   0.0752   1.0000
  14.500   1.3383   0.07343   0.06747  -0.0225   0.0742   1.0000
  14.750   1.3059   0.08036   0.07474  -0.0240   0.0734   1.0000
  15.000   1.2620   0.08981   0.08452  -0.0278   0.0731   1.0000
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