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NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il)
Reynolds number: 50,000
Max Cl/Cd: 24.19 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ms317-il-50000-n5.txt
Download as CSV file: xf-ms317-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.5564   0.10153   0.09323  -0.0528   1.0000   0.0778
 -12.750  -0.6152   0.08684   0.07840  -0.0619   1.0000   0.0770
 -12.500  -0.6641   0.07713   0.06850  -0.0669   1.0000   0.0763
 -12.250  -0.6998   0.07067   0.06182  -0.0689   1.0000   0.0763
 -12.000  -0.7270   0.06592   0.05686  -0.0691   1.0000   0.0766
 -11.750  -0.7498   0.06217   0.05291  -0.0680   1.0000   0.0771
 -11.500  -0.7710   0.05919   0.04973  -0.0656   1.0000   0.0778
 -11.250  -0.7912   0.05672   0.04707  -0.0623   1.0000   0.0785
 -11.000  -0.8068   0.05431   0.04440  -0.0589   1.0000   0.0793
 -10.750  -0.8088   0.05250   0.04251  -0.0562   1.0000   0.0805
 -10.500  -0.8063   0.05117   0.04119  -0.0537   1.0000   0.0821
 -10.250  -0.8071   0.04980   0.03973  -0.0507   1.0000   0.0839
 -10.000  -0.8084   0.04830   0.03807  -0.0477   1.0000   0.0860
  -9.750  -0.8091   0.04665   0.03614  -0.0447   1.0000   0.0883
  -9.500  -0.8024   0.04534   0.03478  -0.0423   1.0000   0.0905
  -9.250  -0.7941   0.04427   0.03371  -0.0401   1.0000   0.0931
  -9.000  -0.7861   0.04309   0.03240  -0.0378   1.0000   0.0964
  -8.750  -0.7765   0.04186   0.03096  -0.0357   1.0000   0.1002
  -8.500  -0.7645   0.04098   0.03016  -0.0338   1.0000   0.1037
  -8.250  -0.7493   0.03998   0.02905  -0.0324   0.9993   0.1087
  -8.000  -0.7189   0.03890   0.02798  -0.0336   0.9947   0.1155
  -7.750  -0.6884   0.03792   0.02684  -0.0345   0.9901   0.1243
  -7.500  -0.6594   0.03707   0.02606  -0.0354   0.9852   0.1334
  -7.250  -0.6289   0.03622   0.02524  -0.0366   0.9807   0.1448
  -7.000  -0.6031   0.03539   0.02443  -0.0370   0.9750   0.1574
  -6.750  -0.5756   0.03454   0.02364  -0.0379   0.9697   0.1729
  -6.250  -0.5268   0.03277   0.02208  -0.0389   0.9584   0.2131
  -6.000  -0.5008   0.03175   0.02128  -0.0401   0.9533   0.2430
  -5.750  -0.4789   0.03069   0.02053  -0.0406   0.9478   0.2824
  -5.500  -0.4593   0.02966   0.01996  -0.0405   0.9417   0.3391
  -5.250  -0.4355   0.02937   0.02041  -0.0395   0.9371   0.4272
  -5.000  -0.4103   0.03050   0.02197  -0.0364   0.9324   0.5051
  -4.750  -0.3891   0.03127   0.02271  -0.0343   0.9256   0.5556
  -4.500  -0.3602   0.03205   0.02333  -0.0339   0.9204   0.5945
  -4.000  -0.3123   0.03354   0.02452  -0.0314   0.9088   0.6482
  -3.750  -0.2869   0.03438   0.02524  -0.0299   0.9035   0.6685
  -3.500  -0.2567   0.03513   0.02585  -0.0292   0.8995   0.6877
  -3.250  -0.2377   0.03559   0.02621  -0.0273   0.8934   0.7044
  -3.000  -0.2182   0.03600   0.02652  -0.0255   0.8870   0.7203
  -2.750  -0.1907   0.03659   0.02703  -0.0240   0.8827   0.7328
  -2.500  -0.1596   0.03690   0.02724  -0.0240   0.8792   0.7472
  -2.250  -0.1508   0.03706   0.02733  -0.0212   0.8714   0.7613
  -2.000  -0.1269   0.03732   0.02753  -0.0197   0.8659   0.7713
  -1.750  -0.0975   0.03732   0.02742  -0.0202   0.8616   0.7826
  -1.500  -0.0737   0.03738   0.02742  -0.0196   0.8564   0.7911
  -1.250  -0.0614   0.03735   0.02734  -0.0179   0.8485   0.7999
  -1.000  -0.0321   0.03731   0.02723  -0.0183   0.8437   0.8056
  -0.750   0.0025   0.03720   0.02704  -0.0201   0.8400   0.8121
  -0.500   0.0085   0.03729   0.02710  -0.0175   0.8308   0.8188
  -0.250   0.0356   0.03726   0.02704  -0.0177   0.8251   0.8238
   0.000   0.0718   0.03715   0.02687  -0.0196   0.8209   0.8290
   0.250   0.0807   0.03729   0.02700  -0.0177   0.8110   0.8353
   0.500   0.1102   0.03722   0.02692  -0.0182   0.8048   0.8394
   0.750   0.1493   0.03707   0.02673  -0.0203   0.8006   0.8436
   1.000   0.1551   0.03732   0.02700  -0.0178   0.7890   0.8496
   1.250   0.1919   0.03715   0.02682  -0.0195   0.7832   0.8536
   1.500   0.2073   0.03728   0.02697  -0.0180   0.7726   0.8581
   1.750   0.2413   0.03708   0.02678  -0.0191   0.7650   0.8622
   2.000   0.2642   0.03709   0.02681  -0.0189   0.7544   0.8671
   2.250   0.2998   0.03669   0.02644  -0.0198   0.7453   0.8707
   2.500   0.3213   0.03652   0.02631  -0.0188   0.7323   0.8750
   2.750   0.3688   0.03550   0.02531  -0.0206   0.7235   0.8784
   3.000   0.3901   0.03521   0.02506  -0.0195   0.7076   0.8831
   3.250   0.4156   0.03468   0.02459  -0.0186   0.6923   0.8869
   3.500   0.4462   0.03391   0.02386  -0.0181   0.6779   0.8907
   3.750   0.4866   0.03272   0.02270  -0.0186   0.6653   0.8944
   4.000   0.5097   0.03225   0.02230  -0.0175   0.6477   0.8992
   4.250   0.5330   0.03168   0.02180  -0.0162   0.6290   0.9033
   4.500   0.5510   0.03133   0.02153  -0.0144   0.6074   0.9079
   4.750   0.5672   0.03113   0.02140  -0.0125   0.5825   0.9132
   5.000   0.5922   0.03050   0.02081  -0.0114   0.5555   0.9180
   5.250   0.6126   0.03017   0.02048  -0.0098   0.5215   0.9233
   5.500   0.6403   0.02961   0.01978  -0.0089   0.4790   0.9281
   5.750   0.6678   0.02921   0.01903  -0.0079   0.4282   0.9328
   6.000   0.6865   0.02953   0.01898  -0.0065   0.3817   0.9386
   6.250   0.7014   0.03027   0.01941  -0.0051   0.3443   0.9450
   6.500   0.7160   0.03115   0.02002  -0.0040   0.3151   0.9517
   6.750   0.7327   0.03207   0.02079  -0.0034   0.2915   0.9586
   7.000   0.7513   0.03299   0.02157  -0.0031   0.2727   0.9660
   7.250   0.7718   0.03389   0.02236  -0.0032   0.2572   0.9748
   7.500   0.7925   0.03468   0.02309  -0.0032   0.2441   0.9886
   7.750   0.8146   0.03544   0.02385  -0.0033   0.2330   1.0000
   8.000   0.8412   0.03636   0.02462  -0.0041   0.2237   1.0000
   8.250   0.8688   0.03729   0.02564  -0.0050   0.2142   1.0000
   8.500   0.9009   0.03814   0.02633  -0.0062   0.2069   1.0000
   8.750   0.9315   0.03915   0.02752  -0.0074   0.1999   1.0000
   9.000   0.9632   0.04013   0.02848  -0.0087   0.1937   1.0000
   9.250   0.9965   0.04119   0.02951  -0.0102   0.1883   1.0000
   9.500   1.0230   0.04250   0.03101  -0.0111   0.1830   1.0000
   9.750   1.0523   0.04375   0.03233  -0.0123   0.1785   1.0000
  10.000   1.0876   0.04497   0.03347  -0.0141   0.1747   1.0000
  10.250   1.1104   0.04664   0.03535  -0.0147   0.1712   1.0000
  10.500   1.1282   0.04844   0.03740  -0.0148   0.1676   1.0000
  10.750   1.1475   0.05017   0.03928  -0.0151   0.1642   1.0000
  11.000   1.1705   0.05181   0.04099  -0.0157   0.1613   1.0000
  11.250   1.2009   0.05341   0.04255  -0.0170   0.1587   1.0000
  11.500   1.2047   0.05592   0.04539  -0.0161   0.1566   1.0000
  11.750   1.2027   0.05874   0.04856  -0.0149   0.1544   1.0000
  12.000   1.1999   0.06172   0.05183  -0.0139   0.1523   1.0000
  12.250   1.1960   0.06486   0.05521  -0.0132   0.1503   1.0000
  12.500   1.1925   0.06809   0.05865  -0.0128   0.1484   1.0000
  12.750   1.1901   0.07137   0.06210  -0.0125   0.1468   1.0000
  13.000   1.1953   0.07417   0.06500  -0.0126   0.1451   1.0000
  13.250   1.1979   0.07734   0.06825  -0.0127   0.1435   1.0000
  13.500   1.1453   0.08544   0.07677  -0.0136   0.1430   1.0000
  13.750   1.0483   0.10112   0.09292  -0.0196   0.1429   1.0000
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