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NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY MS(1)-0313 AIRFOIL (ms313-il)
Reynolds number: 50,000
Max Cl/Cd: 29.82 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ms313-il-50000-n5.txt
Download as CSV file: xf-ms313-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.5134   0.10527   0.09757  -0.0421   1.0000   0.0576
 -11.250  -0.5186   0.09912   0.09145  -0.0453   1.0000   0.0574
 -11.000  -0.5289   0.09224   0.08458  -0.0494   1.0000   0.0571
 -10.750  -0.5446   0.08550   0.07786  -0.0536   1.0000   0.0568
 -10.500  -0.5645   0.07941   0.07175  -0.0570   1.0000   0.0564
 -10.250  -0.5874   0.07435   0.06665  -0.0589   1.0000   0.0561
 -10.000  -0.6121   0.07047   0.06273  -0.0586   1.0000   0.0558
  -9.750  -0.6341   0.06692   0.05909  -0.0575   1.0000   0.0557
  -9.500  -0.6528   0.06360   0.05561  -0.0557   1.0000   0.0558
  -9.250  -0.6673   0.06040   0.05218  -0.0535   1.0000   0.0561
  -9.000  -0.6776   0.05727   0.04876  -0.0512   1.0000   0.0567
  -8.750  -0.6836   0.05416   0.04526  -0.0490   1.0000   0.0573
  -8.500  -0.6836   0.05119   0.04193  -0.0471   1.0000   0.0580
  -8.250  -0.6760   0.04879   0.03940  -0.0455   1.0000   0.0589
  -8.000  -0.6664   0.04650   0.03691  -0.0441   1.0000   0.0598
  -7.750  -0.6547   0.04433   0.03451  -0.0427   1.0000   0.0610
  -7.500  -0.6414   0.04238   0.03232  -0.0415   1.0000   0.0631
  -7.250  -0.6262   0.04040   0.02998  -0.0403   1.0000   0.0658
  -7.000  -0.6088   0.03845   0.02754  -0.0392   1.0000   0.0682
  -6.750  -0.5906   0.03677   0.02585  -0.0381   1.0000   0.0703
  -6.500  -0.5717   0.03545   0.02445  -0.0371   1.0000   0.0734
  -6.250  -0.5519   0.03424   0.02303  -0.0360   1.0000   0.0778
  -6.000  -0.5316   0.03304   0.02172  -0.0347   1.0000   0.0818
  -5.750  -0.5118   0.03207   0.02077  -0.0335   1.0000   0.0864
  -5.500  -0.4910   0.03127   0.01976  -0.0322   1.0000   0.0930
  -5.250  -0.4713   0.03037   0.01897  -0.0310   1.0000   0.0995
  -5.000  -0.4508   0.02961   0.01812  -0.0300   1.0000   0.1087
  -4.750  -0.4301   0.02879   0.01732  -0.0293   1.0000   0.1203
  -4.500  -0.4025   0.02781   0.01645  -0.0302   0.9977   0.1394
  -4.250  -0.3709   0.02656   0.01553  -0.0323   0.9947   0.1782
  -4.000  -0.3385   0.02449   0.01456  -0.0356   0.9924   0.3241
  -3.750  -0.3223   0.02430   0.01574  -0.0317   0.9882   0.5562
  -3.500  -0.2959   0.02508   0.01645  -0.0304   0.9837   0.6457
  -3.250  -0.2728   0.02582   0.01706  -0.0284   0.9787   0.6939
  -3.000  -0.2545   0.02669   0.01784  -0.0248   0.9736   0.7319
  -2.750  -0.2369   0.02749   0.01857  -0.0207   0.9689   0.7677
  -2.500  -0.2213   0.02789   0.01887  -0.0171   0.9633   0.7958
  -2.250  -0.1993   0.02810   0.01895  -0.0151   0.9586   0.8164
  -2.000  -0.1729   0.02820   0.01889  -0.0146   0.9542   0.8335
  -1.750  -0.1516   0.02817   0.01874  -0.0134   0.9485   0.8481
  -1.500  -0.1232   0.02815   0.01858  -0.0139   0.9435   0.8603
  -1.250  -0.0900   0.02818   0.01846  -0.0155   0.9393   0.8699
  -1.000  -0.0668   0.02811   0.01830  -0.0152   0.9327   0.8782
  -0.750  -0.0352   0.02814   0.01822  -0.0167   0.9273   0.8865
  -0.500  -0.0018   0.02817   0.01817  -0.0183   0.9224   0.8937
  -0.250   0.0232   0.02819   0.01812  -0.0186   0.9149   0.9018
   0.000   0.0579   0.02824   0.01811  -0.0205   0.9092   0.9086
   0.250   0.0864   0.02832   0.01815  -0.0214   0.9018   0.9163
   0.500   0.1193   0.02837   0.01818  -0.0229   0.8945   0.9233
   0.750   0.1534   0.02846   0.01825  -0.0247   0.8872   0.9306
   1.000   0.1862   0.02851   0.01830  -0.0261   0.8780   0.9377
   1.250   0.2214   0.02856   0.01836  -0.0280   0.8688   0.9451
   1.500   0.2625   0.02852   0.01836  -0.0306   0.8590   0.9514
   1.750   0.2966   0.02849   0.01838  -0.0321   0.8464   0.9593
   2.000   0.3397   0.02826   0.01821  -0.0347   0.8329   0.9652
   2.250   0.3844   0.02779   0.01780  -0.0371   0.8166   0.9714
   2.500   0.4290   0.02712   0.01721  -0.0391   0.7979   0.9772
   2.750   0.4716   0.02638   0.01654  -0.0407   0.7788   0.9841
   3.000   0.5130   0.02555   0.01581  -0.0419   0.7591   0.9924
   3.250   0.5345   0.02509   0.01543  -0.0403   0.7359   1.0000
   3.750   0.5801   0.02421   0.01472  -0.0375   0.6816   1.0000
   4.000   0.6048   0.02380   0.01436  -0.0364   0.6447   1.0000
   4.250   0.6303   0.02343   0.01398  -0.0353   0.5925   1.0000
   4.500   0.6687   0.02278   0.01292  -0.0351   0.5077   1.0000
   4.750   0.6936   0.02326   0.01270  -0.0340   0.4195   1.0000
   5.000   0.7110   0.02431   0.01326  -0.0328   0.3578   1.0000
   5.250   0.7294   0.02542   0.01403  -0.0321   0.3152   1.0000
   5.500   0.7498   0.02649   0.01483  -0.0317   0.2843   1.0000
   5.750   0.7726   0.02749   0.01568  -0.0317   0.2610   1.0000
   6.000   0.7973   0.02847   0.01656  -0.0318   0.2436   1.0000
   6.250   0.8236   0.02943   0.01743  -0.0322   0.2289   1.0000
   6.500   0.8512   0.03038   0.01830  -0.0327   0.2165   1.0000
   6.750   0.8808   0.03133   0.01920  -0.0335   0.2062   1.0000
   7.000   0.9132   0.03230   0.02025  -0.0345   0.1975   1.0000
   7.250   0.9446   0.03332   0.02119  -0.0355   0.1901   1.0000
   7.500   0.9747   0.03441   0.02243  -0.0362   0.1825   1.0000
   7.750   1.0040   0.03552   0.02355  -0.0369   0.1761   1.0000
   8.000   1.0347   0.03681   0.02489  -0.0378   0.1713   1.0000
   8.250   1.0623   0.03820   0.02653  -0.0383   0.1664   1.0000
   8.500   1.0888   0.03955   0.02797  -0.0387   0.1617   1.0000
   8.750   1.1166   0.04098   0.02934  -0.0393   0.1575   1.0000
   9.000   1.1369   0.04270   0.03146  -0.0389   0.1532   1.0000
   9.250   1.1586   0.04451   0.03354  -0.0387   0.1498   1.0000
   9.500   1.1803   0.04622   0.03541  -0.0385   0.1464   1.0000
   9.750   1.2047   0.04787   0.03704  -0.0387   0.1432   1.0000
  10.000   1.2148   0.05020   0.03983  -0.0373   0.1400   1.0000
  10.250   1.2239   0.05264   0.04266  -0.0359   0.1369   1.0000
  10.500   1.2333   0.05505   0.04537  -0.0347   0.1342   1.0000
  10.750   1.2444   0.05721   0.04771  -0.0336   0.1315   1.0000
  11.000   1.2633   0.05901   0.04952  -0.0333   0.1287   1.0000
  11.250   1.2550   0.06224   0.05315  -0.0307   0.1267   1.0000
  11.500   1.2351   0.06580   0.05711  -0.0273   0.1251   1.0000
  11.750   1.2114   0.06986   0.06152  -0.0245   0.1238   1.0000
  12.000   1.1819   0.07479   0.06677  -0.0227   0.1229   1.0000
  12.250   1.1425   0.08133   0.07360  -0.0226   0.1224   1.0000
  12.500   1.0810   0.09191   0.08445  -0.0259   0.1227   1.0000
  12.750   0.9756   0.11519   0.10786  -0.0402   0.1235   1.0000
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