Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

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


Details Polar file
Airfoil: NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il)
Reynolds number: 1,000,000
Max Cl/Cd: 80.67 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ms317-il-1000000-n5.txt
Download as CSV file: xf-ms317-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.2481   0.07949   0.07540  -0.0493   1.0000   0.0149
 -19.500  -1.2623   0.07376   0.06955  -0.0521   1.0000   0.0150
 -19.250  -1.2722   0.06882   0.06450  -0.0544   1.0000   0.0151
 -19.000  -1.2794   0.06437   0.05996  -0.0564   1.0000   0.0152
 -18.750  -1.2838   0.06046   0.05595  -0.0579   1.0000   0.0153
 -18.500  -1.2860   0.05695   0.05236  -0.0592   1.0000   0.0154
 -18.250  -1.2862   0.05377   0.04910  -0.0603   1.0000   0.0156
 -18.000  -1.2849   0.05086   0.04612  -0.0612   1.0000   0.0157
 -17.750  -1.2824   0.04819   0.04337  -0.0618   1.0000   0.0159
 -17.500  -1.2784   0.04576   0.04087  -0.0624   1.0000   0.0160
 -17.250  -1.2730   0.04354   0.03859  -0.0627   1.0000   0.0162
 -17.000  -1.2669   0.04147   0.03646  -0.0629   1.0000   0.0163
 -16.750  -1.2603   0.03953   0.03445  -0.0631   1.0000   0.0165
 -16.500  -1.2523   0.03779   0.03265  -0.0630   1.0000   0.0167
 -16.250  -1.2439   0.03614   0.03094  -0.0629   1.0000   0.0168
 -16.000  -1.2344   0.03461   0.02935  -0.0628   1.0000   0.0170
 -15.750  -1.2238   0.03320   0.02788  -0.0626   1.0000   0.0171
 -15.500  -1.2150   0.03165   0.02629  -0.0623   1.0000   0.0174
 -15.250  -1.2044   0.03028   0.02488  -0.0619   1.0000   0.0176
 -15.000  -1.1927   0.02901   0.02358  -0.0616   1.0000   0.0179
 -14.750  -1.1796   0.02788   0.02242  -0.0612   1.0000   0.0182
 -14.500  -1.1661   0.02680   0.02131  -0.0608   1.0000   0.0185
 -14.250  -1.1515   0.02581   0.02030  -0.0604   1.0000   0.0188
 -14.000  -1.1367   0.02487   0.01932  -0.0599   1.0000   0.0191
 -13.750  -1.1213   0.02399   0.01841  -0.0594   1.0000   0.0195
 -13.500  -1.1028   0.02314   0.01753  -0.0595   0.9924   0.0198
 -13.250  -1.0788   0.02231   0.01665  -0.0605   0.9732   0.0201
 -12.750  -1.0432   0.02068   0.01489  -0.0598   0.9305   0.0209
 -12.500  -1.0267   0.01998   0.01412  -0.0590   0.9139   0.0213
 -12.250  -1.0091   0.01933   0.01340  -0.0583   0.9001   0.0217
 -12.000  -0.9914   0.01870   0.01271  -0.0577   0.8885   0.0222
 -11.750  -0.9742   0.01815   0.01209  -0.0568   0.8774   0.0226
 -11.500  -0.9525   0.01761   0.01149  -0.0568   0.8677   0.0231
 -11.250  -0.9297   0.01712   0.01093  -0.0568   0.8585   0.0235
 -11.000  -0.9065   0.01654   0.01032  -0.0570   0.8504   0.0243
 -10.750  -0.8822   0.01606   0.00980  -0.0572   0.8423   0.0250
 -10.500  -0.8572   0.01564   0.00933  -0.0574   0.8354   0.0257
 -10.250  -0.8316   0.01525   0.00891  -0.0576   0.8282   0.0264
 -10.000  -0.8056   0.01492   0.00852  -0.0578   0.8217   0.0270
  -9.750  -0.7795   0.01452   0.00810  -0.0580   0.8164   0.0279
  -9.500  -0.7528   0.01415   0.00772  -0.0583   0.8110   0.0289
  -9.250  -0.7257   0.01383   0.00738  -0.0586   0.8055   0.0299
  -8.750  -0.6705   0.01320   0.00671  -0.0594   0.7961   0.0327
  -8.500  -0.6424   0.01290   0.00641  -0.0598   0.7915   0.0344
  -8.250  -0.6141   0.01262   0.00611  -0.0602   0.7869   0.0362
  -8.000  -0.5857   0.01235   0.00583  -0.0606   0.7824   0.0385
  -7.750  -0.5569   0.01208   0.00557  -0.0611   0.7784   0.0412
  -7.500  -0.5278   0.01182   0.00532  -0.0617   0.7741   0.0448
  -7.250  -0.4986   0.01155   0.00507  -0.0622   0.7696   0.0492
  -7.000  -0.4693   0.01131   0.00484  -0.0628   0.7654   0.0537
  -6.750  -0.4398   0.01111   0.00463  -0.0633   0.7612   0.0583
  -6.250  -0.3798   0.01065   0.00423  -0.0647   0.7537   0.0697
  -6.000  -0.3497   0.01045   0.00405  -0.0653   0.7497   0.0755
  -5.750  -0.3195   0.01026   0.00388  -0.0660   0.7456   0.0815
  -5.500  -0.2892   0.01009   0.00371  -0.0666   0.7415   0.0889
  -5.250  -0.2585   0.00988   0.00355  -0.0674   0.7383   0.0973
  -5.000  -0.2277   0.00968   0.00339  -0.0682   0.7349   0.1068
  -4.750  -0.1969   0.00947   0.00324  -0.0690   0.7313   0.1200
  -4.500  -0.1659   0.00927   0.00310  -0.0698   0.7277   0.1365
  -4.250  -0.1348   0.00904   0.00295  -0.0707   0.7241   0.1572
  -4.000  -0.1031   0.00874   0.00279  -0.0718   0.7211   0.1913
  -3.750  -0.0712   0.00847   0.00265  -0.0729   0.7179   0.2238
  -3.500  -0.0391   0.00819   0.00252  -0.0741   0.7142   0.2607
  -3.250  -0.0068   0.00791   0.00238  -0.0753   0.7101   0.3015
  -3.000   0.0259   0.00760   0.00224  -0.0766   0.7060   0.3535
  -2.750   0.0596   0.00718   0.00207  -0.0783   0.7024   0.4270
  -2.500   0.0931   0.00687   0.00197  -0.0798   0.6992   0.4866
  -2.250   0.1257   0.00668   0.00192  -0.0809   0.6952   0.5292
  -2.000   0.1573   0.00661   0.00190  -0.0817   0.6892   0.5549
  -1.750   0.1885   0.00657   0.00189  -0.0824   0.6764   0.5780
  -1.500   0.2191   0.00660   0.00190  -0.0829   0.6562   0.5996
  -1.250   0.2494   0.00667   0.00190  -0.0834   0.6378   0.6100
  -1.000   0.2798   0.00673   0.00192  -0.0838   0.6235   0.6185
  -0.750   0.3100   0.00683   0.00194  -0.0843   0.6063   0.6265
  -0.500   0.3399   0.00694   0.00200  -0.0846   0.5842   0.6352
  -0.250   0.3697   0.00710   0.00205  -0.0850   0.5604   0.6427
   0.000   0.3992   0.00726   0.00213  -0.0853   0.5354   0.6485
   0.250   0.4278   0.00752   0.00223  -0.0855   0.4953   0.6520
   0.500   0.4548   0.00797   0.00240  -0.0855   0.4324   0.6546
   0.750   0.4820   0.00840   0.00258  -0.0855   0.3781   0.6570
   1.000   0.5096   0.00877   0.00274  -0.0856   0.3353   0.6591
   1.250   0.5373   0.00911   0.00290  -0.0858   0.2982   0.6611
   1.500   0.5652   0.00941   0.00305  -0.0859   0.2672   0.6628
   1.750   0.5931   0.00969   0.00320  -0.0860   0.2406   0.6648
   2.000   0.6210   0.00995   0.00336  -0.0861   0.2167   0.6668
   2.250   0.6488   0.01022   0.00353  -0.0862   0.1959   0.6689
   2.500   0.6767   0.01046   0.00369  -0.0863   0.1798   0.6709
   2.750   0.7048   0.01068   0.00384  -0.0864   0.1676   0.6729
   3.000   0.7327   0.01090   0.00400  -0.0865   0.1571   0.6747
   3.250   0.7608   0.01110   0.00415  -0.0866   0.1486   0.6765
   3.500   0.7887   0.01131   0.00431  -0.0867   0.1412   0.6785
   3.750   0.8165   0.01152   0.00448  -0.0868   0.1344   0.6805
   4.000   0.8441   0.01173   0.00465  -0.0868   0.1284   0.6819
   4.250   0.8718   0.01192   0.00482  -0.0868   0.1232   0.6838
   4.500   0.8988   0.01216   0.00502  -0.0868   0.1174   0.6856
   4.750   0.9263   0.01234   0.00520  -0.0868   0.1137   0.6873
   5.000   0.9532   0.01257   0.00541  -0.0867   0.1097   0.6891
   5.250   0.9798   0.01281   0.00563  -0.0866   0.1059   0.6910
   5.500   1.0068   0.01301   0.00583  -0.0865   0.1038   0.6931
   5.750   1.0334   0.01323   0.00604  -0.0864   0.1015   0.6949
   6.000   1.0595   0.01347   0.00628  -0.0861   0.0991   0.6966
   6.250   1.0852   0.01374   0.00652  -0.0859   0.0967   0.6982
   6.500   1.1108   0.01399   0.00677  -0.0856   0.0948   0.6997
   6.750   1.1366   0.01422   0.00701  -0.0853   0.0936   0.7010
   7.000   1.1619   0.01447   0.00727  -0.0849   0.0922   0.7026
   7.250   1.1866   0.01473   0.00754  -0.0845   0.0906   0.7046
   7.500   1.2108   0.01501   0.00783  -0.0840   0.0891   0.7067
   7.750   1.2344   0.01531   0.00814  -0.0834   0.0877   0.7088
   8.000   1.2573   0.01564   0.00848  -0.0826   0.0862   0.7110
   8.250   1.2798   0.01596   0.00882  -0.0818   0.0852   0.7130
   8.500   1.3023   0.01625   0.00914  -0.0810   0.0846   0.7151
   8.750   1.3240   0.01656   0.00948  -0.0801   0.0838   0.7172
   9.000   1.3439   0.01688   0.00983  -0.0788   0.0829   0.7192
   9.250   1.3605   0.01724   0.01021  -0.0769   0.0821   0.7209
   9.500   1.3791   0.01764   0.01064  -0.0756   0.0812   0.7229
   9.750   1.3980   0.01808   0.01111  -0.0743   0.0803   0.7252
  10.000   1.4165   0.01856   0.01161  -0.0730   0.0790   0.7274
  10.250   1.4339   0.01912   0.01218  -0.0717   0.0774   0.7297
  10.500   1.4522   0.01964   0.01274  -0.0705   0.0762   0.7321
  10.750   1.4712   0.02013   0.01328  -0.0695   0.0756   0.7347
  11.000   1.4894   0.02068   0.01387  -0.0684   0.0749   0.7373
  11.250   1.5073   0.02126   0.01449  -0.0673   0.0742   0.7396
  11.500   1.5248   0.02189   0.01515  -0.0663   0.0734   0.7419
  11.750   1.5420   0.02254   0.01585  -0.0652   0.0725   0.7447
  12.000   1.5584   0.02326   0.01660  -0.0641   0.0716   0.7475
  12.250   1.5745   0.02401   0.01740  -0.0630   0.0706   0.7504
  12.500   1.5897   0.02485   0.01827  -0.0619   0.0697   0.7534
  12.750   1.6038   0.02578   0.01923  -0.0607   0.0687   0.7563
  13.000   1.6197   0.02658   0.02009  -0.0598   0.0683   0.7591
  13.250   1.6353   0.02742   0.02099  -0.0589   0.0677   0.7619
  13.500   1.6505   0.02831   0.02194  -0.0579   0.0670   0.7653
  13.750   1.6652   0.02924   0.02294  -0.0570   0.0661   0.7689
  14.000   1.6792   0.03024   0.02398  -0.0561   0.0651   0.7728
  14.250   1.6923   0.03131   0.02509  -0.0551   0.0641   0.7766
  14.750   1.7161   0.03369   0.02756  -0.0532   0.0622   0.7841
  15.000   1.7274   0.03496   0.02889  -0.0522   0.0613   0.7882
  15.250   1.7393   0.03618   0.03018  -0.0514   0.0607   0.7924
  15.500   1.7506   0.03744   0.03152  -0.0506   0.0599   0.7964
  15.750   1.7610   0.03882   0.03296  -0.0497   0.0589   0.8002
  16.000   1.7711   0.04025   0.03445  -0.0489   0.0578   0.8047
  16.250   1.7798   0.04184   0.03610  -0.0482   0.0567   0.8094
  16.500   1.7878   0.04352   0.03781  -0.0474   0.0555   0.8140
  16.750   1.7955   0.04526   0.03962  -0.0467   0.0545   0.8184
  17.000   1.8039   0.04694   0.04139  -0.0461   0.0534   0.8235
  17.250   1.8106   0.04885   0.04336  -0.0456   0.0521   0.8288
  17.500   1.8165   0.05086   0.04543  -0.0450   0.0509   0.8339
  17.750   1.8206   0.05310   0.04773  -0.0446   0.0497   0.8391
  18.000   1.8246   0.05538   0.05009  -0.0442   0.0487   0.8454
  18.250   1.8289   0.05765   0.05244  -0.0439   0.0476   0.8516
  18.500   1.8310   0.06022   0.05510  -0.0436   0.0465   0.8584
  18.750   1.8317   0.06299   0.05795  -0.0435   0.0454   0.8657
  19.000   1.8307   0.06600   0.06103  -0.0434   0.0443   0.8730
<< Back to NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il)

Polar data table (+)

Polar graphs


<< Back to NASA/LANGLEY MS(1)-0317 AIRFOIL (ms317-il)