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 LS(1)-0421 AIRFOIL (ls421-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il)
Reynolds number: 200,000
Max Cl/Cd: 56.43 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ls421-il-200000-n5.txt
Download as CSV file: xf-ls421-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY LS(1)-0421 AIRFOIL                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -0.7893   0.12202   0.11656  -0.0611   1.0000   0.0321
 -19.500  -0.8040   0.11525   0.10966  -0.0652   1.0000   0.0323
 -19.250  -0.8156   0.10921   0.10351  -0.0688   1.0000   0.0325
 -19.000  -0.8252   0.10367   0.09784  -0.0720   1.0000   0.0327
 -18.750  -0.8335   0.09845   0.09251  -0.0749   1.0000   0.0329
 -18.500  -0.8409   0.09349   0.08743  -0.0777   1.0000   0.0331
 -18.250  -0.8469   0.08884   0.08267  -0.0802   1.0000   0.0334
 -18.000  -0.8518   0.08447   0.07818  -0.0825   1.0000   0.0337
 -17.750  -0.8556   0.08036   0.07395  -0.0846   1.0000   0.0340
 -17.500  -0.8585   0.07647   0.06993  -0.0865   1.0000   0.0344
 -17.250  -0.8603   0.07281   0.06615  -0.0882   1.0000   0.0348
 -17.000  -0.8614   0.06935   0.06255  -0.0897   1.0000   0.0353
 -16.750  -0.8616   0.06611   0.05915  -0.0910   1.0000   0.0358
 -16.500  -0.8590   0.06334   0.05626  -0.0920   1.0000   0.0362
 -16.250  -0.8526   0.06118   0.05412  -0.0927   1.0000   0.0366
 -16.000  -0.8447   0.05900   0.05190  -0.0940   0.9879   0.0371
 -15.750  -0.8339   0.05670   0.04954  -0.0958   0.9753   0.0376
 -15.500  -0.8228   0.05449   0.04724  -0.0973   0.9644   0.0382
 -15.250  -0.8127   0.05243   0.04508  -0.0983   0.9538   0.0388
 -15.000  -0.8027   0.05054   0.04307  -0.0989   0.9446   0.0395
 -14.750  -0.7936   0.04877   0.04117  -0.0990   0.9354   0.0401
 -14.500  -0.7840   0.04715   0.03945  -0.0989   0.9279   0.0407
 -14.250  -0.7748   0.04559   0.03786  -0.0987   0.9202   0.0413
 -14.000  -0.7654   0.04410   0.03633  -0.0985   0.9133   0.0419
 -13.750  -0.7556   0.04268   0.03484  -0.0981   0.9074   0.0427
 -13.500  -0.7450   0.04131   0.03340  -0.0979   0.9009   0.0436
 -13.250  -0.7339   0.04006   0.03204  -0.0974   0.8948   0.0446
 -13.000  -0.7233   0.03882   0.03072  -0.0967   0.8896   0.0455
 -12.750  -0.7123   0.03754   0.02942  -0.0964   0.8843   0.0464
 -12.500  -0.6999   0.03637   0.02822  -0.0961   0.8791   0.0474
 -12.250  -0.6874   0.03526   0.02704  -0.0956   0.8744   0.0486
 -12.000  -0.6743   0.03422   0.02591  -0.0950   0.8703   0.0498
 -11.750  -0.6617   0.03314   0.02479  -0.0945   0.8664   0.0510
 -11.500  -0.6481   0.03208   0.02373  -0.0942   0.8620   0.0523
 -11.250  -0.6336   0.03113   0.02273  -0.0938   0.8575   0.0539
 -11.000  -0.6185   0.03025   0.02177  -0.0932   0.8532   0.0557
 -10.750  -0.6054   0.02926   0.02077  -0.0926   0.8494   0.0573
 -10.500  -0.5908   0.02839   0.01985  -0.0919   0.8461   0.0592
 -10.250  -0.5739   0.02761   0.01903  -0.0916   0.8423   0.0616
 -10.000  -0.5591   0.02672   0.01817  -0.0911   0.8385   0.0639
  -9.750  -0.5425   0.02597   0.01738  -0.0906   0.8348   0.0669
  -9.500  -0.5268   0.02518   0.01659  -0.0900   0.8315   0.0700
  -9.250  -0.5103   0.02445   0.01583  -0.0894   0.8284   0.0739
  -9.000  -0.4943   0.02371   0.01508  -0.0887   0.8256   0.0783
  -8.750  -0.4778   0.02305   0.01442  -0.0880   0.8222   0.0838
  -8.500  -0.4627   0.02243   0.01383  -0.0871   0.8183   0.0903
  -8.250  -0.4493   0.02184   0.01327  -0.0858   0.8147   0.0976
  -8.000  -0.4333   0.02125   0.01270  -0.0850   0.8116   0.1066
  -7.750  -0.4150   0.02066   0.01214  -0.0846   0.8088   0.1178
  -7.500  -0.3952   0.02008   0.01159  -0.0844   0.8064   0.1311
  -7.250  -0.3744   0.01948   0.01105  -0.0844   0.8042   0.1468
  -7.000  -0.3529   0.01893   0.01059  -0.0845   0.8015   0.1658
  -6.500  -0.3082   0.01787   0.00978  -0.0850   0.7950   0.2151
  -6.250  -0.2842   0.01730   0.00937  -0.0855   0.7922   0.2487
  -6.000  -0.2587   0.01674   0.00898  -0.0862   0.7898   0.2877
  -5.750  -0.2317   0.01622   0.00862  -0.0871   0.7876   0.3274
  -5.500  -0.2036   0.01568   0.00828  -0.0881   0.7856   0.3730
  -5.250  -0.1746   0.01515   0.00803  -0.0892   0.7838   0.4299
  -5.000  -0.1454   0.01485   0.00803  -0.0899   0.7820   0.4885
  -4.750  -0.1178   0.01494   0.00835  -0.0899   0.7791   0.5311
  -4.500  -0.0886   0.01507   0.00853  -0.0903   0.7763   0.5589
  -4.250  -0.0589   0.01521   0.00869  -0.0907   0.7738   0.5791
  -4.000  -0.0291   0.01538   0.00885  -0.0911   0.7714   0.5951
  -3.750   0.0002   0.01559   0.00905  -0.0913   0.7691   0.6071
  -3.500   0.0318   0.01565   0.00903  -0.0922   0.7668   0.6195
  -3.250   0.0608   0.01587   0.00926  -0.0921   0.7647   0.6277
  -3.000   0.0935   0.01593   0.00922  -0.0932   0.7629   0.6389
  -2.750   0.1214   0.01625   0.00954  -0.0927   0.7613   0.6447
  -2.500   0.1496   0.01647   0.00978  -0.0928   0.7587   0.6508
  -2.250   0.1806   0.01650   0.00975  -0.0941   0.7555   0.6577
  -2.000   0.2082   0.01667   0.00993  -0.0940   0.7525   0.6611
  -1.750   0.2357   0.01684   0.01011  -0.0939   0.7497   0.6641
  -1.500   0.2646   0.01695   0.01022  -0.0940   0.7472   0.6677
  -1.250   0.2952   0.01700   0.01023  -0.0946   0.7449   0.6719
  -1.000   0.3284   0.01695   0.01011  -0.0959   0.7429   0.6776
  -0.750   0.3595   0.01698   0.01010  -0.0965   0.7409   0.6816
  -0.500   0.3845   0.01724   0.01042  -0.0959   0.7375   0.6845
  -0.250   0.4096   0.01746   0.01070  -0.0954   0.7332   0.6876
   0.000   0.4377   0.01753   0.01078  -0.0955   0.7294   0.6908
   0.250   0.4687   0.01747   0.01070  -0.0962   0.7258   0.6943
   0.500   0.5026   0.01731   0.01048  -0.0976   0.7227   0.6981
   0.750   0.5381   0.01711   0.01020  -0.0993   0.7198   0.7016
   1.000   0.5599   0.01728   0.01047  -0.0983   0.7130   0.7033
   1.250   0.5873   0.01723   0.01044  -0.0980   0.7071   0.7051
   1.500   0.6183   0.01707   0.01026  -0.0984   0.7024   0.7070
   1.750   0.6470   0.01702   0.01022  -0.0986   0.6972   0.7089
   2.000   0.6723   0.01708   0.01033  -0.0983   0.6900   0.7111
   2.250   0.7030   0.01689   0.01012  -0.0988   0.6831   0.7136
   2.500   0.7309   0.01681   0.01005  -0.0989   0.6742   0.7162
   2.750   0.7600   0.01668   0.00991  -0.0993   0.6647   0.7187
   3.000   0.7896   0.01660   0.00981  -0.0999   0.6558   0.7211
   3.250   0.8174   0.01656   0.00977  -0.1001   0.6456   0.7235
   3.500   0.8416   0.01658   0.00984  -0.0994   0.6349   0.7251
   3.750   0.8674   0.01655   0.00979  -0.0989   0.6228   0.7266
   4.000   0.8898   0.01663   0.00990  -0.0980   0.6076   0.7283
   4.250   0.9132   0.01668   0.00994  -0.0971   0.5896   0.7300
   4.500   0.9360   0.01676   0.00993  -0.0962   0.5669   0.7319
   4.750   0.9559   0.01694   0.00999  -0.0948   0.5379   0.7339
   5.000   0.9710   0.01730   0.01015  -0.0926   0.5045   0.7364
   5.250   0.9785   0.01784   0.01049  -0.0892   0.4715   0.7393
   5.500   0.9841   0.01853   0.01100  -0.0858   0.4404   0.7421
   6.000   1.0001   0.02038   0.01254  -0.0805   0.3821   0.7461
   6.250   1.0077   0.02139   0.01345  -0.0779   0.3565   0.7478
   6.500   1.0156   0.02246   0.01441  -0.0756   0.3329   0.7496
   7.000   1.0348   0.02461   0.01637  -0.0717   0.2916   0.7536
   7.250   1.0456   0.02570   0.01739  -0.0701   0.2733   0.7559
   7.500   1.0576   0.02676   0.01839  -0.0687   0.2564   0.7585
   7.750   1.0704   0.02783   0.01939  -0.0675   0.2409   0.7612
   8.000   1.0840   0.02889   0.02039  -0.0665   0.2270   0.7637
   8.250   1.0975   0.03001   0.02145  -0.0655   0.2145   0.7659
   8.750   1.1218   0.03216   0.02357  -0.0629   0.1933   0.7693
   9.000   1.1338   0.03329   0.02468  -0.0617   0.1847   0.7712
   9.250   1.1468   0.03437   0.02577  -0.0606   0.1765   0.7733
   9.500   1.1591   0.03554   0.02692  -0.0595   0.1694   0.7755
   9.750   1.1726   0.03665   0.02805  -0.0586   0.1627   0.7778
  10.000   1.1848   0.03790   0.02928  -0.0577   0.1569   0.7803
  10.250   1.1992   0.03903   0.03044  -0.0570   0.1512   0.7830
  10.500   1.2114   0.04037   0.03175  -0.0563   0.1461   0.7858
  10.750   1.2246   0.04153   0.03295  -0.0554   0.1417   0.7880
  11.000   1.2368   0.04276   0.03424  -0.0545   0.1371   0.7901
  11.250   1.2471   0.04419   0.03567  -0.0535   0.1333   0.7924
  11.500   1.2605   0.04541   0.03696  -0.0528   0.1296   0.7948
  11.750   1.2729   0.04675   0.03834  -0.0521   0.1259   0.7973
  12.000   1.2836   0.04827   0.03987  -0.0514   0.1227   0.7999
  12.250   1.2954   0.04973   0.04136  -0.0508   0.1198   0.8027
  12.500   1.3085   0.05114   0.04283  -0.0503   0.1167   0.8054
  12.750   1.3191   0.05269   0.04443  -0.0497   0.1138   0.8077
  13.000   1.3277   0.05439   0.04615  -0.0489   0.1113   0.8099
  13.250   1.3385   0.05593   0.04777  -0.0483   0.1089   0.8126
  13.500   1.3493   0.05750   0.04943  -0.0477   0.1064   0.8156
  13.750   1.3590   0.05922   0.05121  -0.0472   0.1040   0.8189
  14.000   1.3671   0.06117   0.05318  -0.0468   0.1020   0.8221
  14.250   1.3764   0.06304   0.05509  -0.0465   0.1000   0.8253
  14.500   1.3860   0.06476   0.05692  -0.0460   0.0978   0.8278
  14.750   1.3940   0.06668   0.05893  -0.0456   0.0957   0.8305
  15.000   1.4008   0.06875   0.06106  -0.0452   0.0939   0.8335
  15.250   1.4066   0.07098   0.06331  -0.0449   0.0924   0.8366
  15.500   1.4148   0.07303   0.06546  -0.0447   0.0906   0.8400
  15.750   1.4228   0.07515   0.06768  -0.0446   0.0888   0.8433
  16.000   1.4285   0.07742   0.07005  -0.0444   0.0871   0.8462
  16.250   1.4331   0.07982   0.07251  -0.0443   0.0856   0.8494
  16.500   1.4370   0.08234   0.07506  -0.0442   0.0843   0.8530
  16.750   1.4423   0.08476   0.07758  -0.0443   0.0828   0.8570
  17.000   1.4477   0.08727   0.08021  -0.0445   0.0813   0.8611
  17.250   1.4511   0.08986   0.08292  -0.0445   0.0799   0.8648
  17.500   1.4542   0.09256   0.08571  -0.0447   0.0786   0.8690
  17.750   1.4567   0.09541   0.08862  -0.0451   0.0774   0.8734
  18.000   1.4596   0.09819   0.09141  -0.0456   0.0763   0.8778
  18.250   1.4614   0.10111   0.09449  -0.0460   0.0751   0.8820
  18.500   1.4629   0.10409   0.09762  -0.0466   0.0738   0.8869
  18.750   1.4642   0.10721   0.10085  -0.0474   0.0726   0.8922
  19.000   1.4648   0.11033   0.10407  -0.0481   0.0716   0.8977
  19.250   1.4652   0.11347   0.10729  -0.0490   0.0706   0.9044
<< Back to NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il)

Polar data table (+)

Polar graphs


<< Back to NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il)