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NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il)
Reynolds number: 50,000
Max Cl/Cd: 28.42 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ms317-il-50000.txt
Download as CSV file: xf-ms317-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5831   0.08341   0.07579  -0.0577   1.0000   0.1672
 -10.500  -0.6039   0.07822   0.07065  -0.0577   1.0000   0.1655
 -10.250  -0.6405   0.07384   0.06632  -0.0558   1.0000   0.1633
 -10.000  -0.6899   0.07037   0.06287  -0.0516   1.0000   0.1604
  -9.750  -0.7433   0.06662   0.05897  -0.0468   1.0000   0.1572
  -9.500  -0.7911   0.06257   0.05451  -0.0423   1.0000   0.1543
  -9.250  -0.8027   0.05947   0.05119  -0.0395   1.0000   0.1546
  -9.000  -0.8012   0.05705   0.04869  -0.0373   1.0000   0.1569
  -8.750  -0.8016   0.05447   0.04591  -0.0352   1.0000   0.1593
  -8.500  -0.8004   0.05169   0.04283  -0.0334   1.0000   0.1619
  -8.250  -0.7958   0.04882   0.03954  -0.0320   1.0000   0.1647
  -8.000  -0.7878   0.04609   0.03624  -0.0309   1.0000   0.1682
  -7.750  -0.7712   0.04420   0.03453  -0.0297   1.0000   0.1742
  -7.500  -0.7557   0.04225   0.03229  -0.0289   1.0000   0.1809
  -7.250  -0.7383   0.04028   0.03016  -0.0281   1.0000   0.1885
  -7.000  -0.7194   0.03878   0.02853  -0.0273   1.0000   0.1987
  -6.750  -0.6998   0.03729   0.02707  -0.0264   1.0000   0.2099
  -6.500  -0.6795   0.03591   0.02564  -0.0256   1.0000   0.2240
  -6.250  -0.6593   0.03472   0.02449  -0.0246   1.0000   0.2412
  -6.000  -0.6395   0.03364   0.02357  -0.0235   1.0000   0.2618
  -5.750  -0.6198   0.03259   0.02269  -0.0223   1.0000   0.2881
  -5.500  -0.6008   0.03148   0.02191  -0.0209   1.0000   0.3225
  -5.250  -0.5824   0.03019   0.02122  -0.0196   1.0000   0.3759
  -5.000  -0.5698   0.02956   0.02176  -0.0157   1.0000   0.4703
  -4.750  -0.5665   0.03173   0.02457  -0.0067   1.0000   0.5618
  -4.500  -0.5588   0.03436   0.02715   0.0006   1.0000   0.6267
  -4.250  -0.5516   0.03672   0.02942   0.0081   1.0000   0.6650
  -4.000  -0.5442   0.03875   0.03135   0.0155   1.0000   0.6943
  -3.750  -0.5353   0.04012   0.03259   0.0216   1.0000   0.7247
  -3.500  -0.5249   0.04133   0.03369   0.0278   1.0000   0.7513
  -3.250  -0.5148   0.04191   0.03414   0.0325   1.0000   0.7809
  -3.000  -0.4979   0.04259   0.03469   0.0372   1.0000   0.8075
  -2.750  -0.4820   0.04279   0.03475   0.0406   1.0000   0.8366
  -2.500  -0.4525   0.04307   0.03486   0.0418   1.0000   0.8664
  -2.250  -0.3965   0.04351   0.03509   0.0379   1.0000   0.8975
  -2.000  -0.3080   0.04414   0.03544   0.0270   1.0000   0.9290
  -1.750  -0.2210   0.04442   0.03548   0.0151   1.0000   0.9560
  -1.500  -0.1480   0.04446   0.03536   0.0046   1.0000   0.9757
  -1.250  -0.0929   0.04454   0.03531  -0.0031   1.0000   0.9906
  -1.000  -0.0525   0.04467   0.03535  -0.0083   1.0000   1.0000
  -0.750  -0.0507   0.04459   0.03524  -0.0063   1.0000   1.0000
  -0.500  -0.0488   0.04453   0.03515  -0.0043   1.0000   1.0000
  -0.250  -0.0469   0.04449   0.03509  -0.0023   1.0000   1.0000
   0.000  -0.0450   0.04447   0.03506  -0.0003   1.0000   1.0000
   0.250  -0.0432   0.04448   0.03505   0.0017   1.0000   1.0000
   0.500  -0.0415   0.04450   0.03506   0.0037   1.0000   1.0000
   0.750  -0.0399   0.04454   0.03510   0.0057   1.0000   1.0000
   1.000   0.0036   0.04533   0.03587  -0.0001   0.9869   1.0000
   1.250   0.0442   0.04614   0.03667  -0.0052   0.9717   1.0000
   1.500   0.0831   0.04693   0.03746  -0.0097   0.9549   1.0000
   1.750   0.1228   0.04773   0.03827  -0.0140   0.9365   1.0000
   2.000   0.1669   0.04859   0.03913  -0.0186   0.9166   1.0000
   2.250   0.1971   0.04907   0.03964  -0.0207   0.8958   1.0000
   2.500   0.2252   0.04946   0.04006  -0.0221   0.8736   1.0000
   2.750   0.2567   0.04977   0.04041  -0.0236   0.8500   1.0000
   3.000   0.2999   0.04991   0.04060  -0.0264   0.8250   1.0000
   3.250   0.3649   0.04964   0.04038  -0.0316   0.7999   1.0000
   3.500   0.3788   0.04950   0.04031  -0.0296   0.7749   1.0000
   3.750   0.4153   0.04894   0.03982  -0.0301   0.7500   1.0000
   4.000   0.4727   0.04762   0.03859  -0.0327   0.7262   1.0000
   4.250   0.5612   0.04478   0.03591  -0.0382   0.7038   1.0000
   4.500   0.5638   0.04424   0.03543  -0.0334   0.6774   1.0000
   4.750   0.6510   0.03999   0.03136  -0.0371   0.6525   1.0000
   5.000   0.7174   0.03584   0.02734  -0.0379   0.6226   1.0000
   5.250   0.7715   0.03199   0.02350  -0.0370   0.5790   1.0000
   5.500   0.8112   0.02944   0.02057  -0.0349   0.5154   1.0000
   5.750   0.8283   0.02915   0.01970  -0.0315   0.4574   1.0000
   6.000   0.8423   0.02973   0.01980  -0.0288   0.4154   1.0000
   6.250   0.8596   0.03060   0.02030  -0.0270   0.3844   1.0000
   6.500   0.8760   0.03155   0.02107  -0.0253   0.3613   1.0000
   6.750   0.8947   0.03256   0.02193  -0.0242   0.3430   1.0000
   7.000   0.9155   0.03364   0.02288  -0.0234   0.3278   1.0000
   7.250   0.9441   0.03485   0.02388  -0.0239   0.3143   1.0000
   7.500   0.9583   0.03617   0.02540  -0.0225   0.3043   1.0000
   7.750   0.9892   0.03770   0.02680  -0.0236   0.2948   1.0000
   8.000   1.0055   0.03931   0.02868  -0.0229   0.2867   1.0000
   8.250   1.0400   0.04100   0.03019  -0.0247   0.2785   1.0000
   8.500   1.0520   0.04309   0.03267  -0.0237   0.2732   1.0000
   8.750   1.0695   0.04527   0.03510  -0.0236   0.2680   1.0000
   9.000   1.0966   0.04731   0.03718  -0.0246   0.2626   1.0000
   9.250   1.1144   0.04993   0.03997  -0.0248   0.2583   1.0000
   9.500   1.1130   0.05300   0.04348  -0.0231   0.2554   1.0000
   9.750   1.1090   0.05645   0.04732  -0.0216   0.2530   1.0000
  10.000   1.0973   0.06048   0.05170  -0.0198   0.2517   1.0000
  10.250   1.0665   0.06542   0.05698  -0.0171   0.2515   1.0000
  10.500   0.9939   0.07427   0.06619  -0.0152   0.2540   1.0000
  10.750   0.9049   0.08901   0.08114  -0.0190   0.2586   1.0000
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