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=100,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il)
Reynolds number: 100,000
Max Cl/Cd: 33.1 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ls421-il-100000.txt
Download as CSV file: xf-ls421-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.3481   0.15969   0.15417  -0.0472   1.0000   0.1499
 -14.500  -0.3627   0.15946   0.15400  -0.0442   1.0000   0.1531
 -14.250  -0.6067   0.10368   0.09807  -0.0722   1.0000   0.0909
 -14.000  -0.6124   0.10231   0.09676  -0.0699   1.0000   0.0915
 -13.750  -0.6145   0.10160   0.09610  -0.0675   1.0000   0.0925
 -13.500  -0.6053   0.10280   0.09739  -0.0642   1.0000   0.0941
 -13.250  -0.9528   0.07328   0.06646  -0.0641   1.0000   0.0825
 -13.000  -0.9758   0.07033   0.06332  -0.0618   0.9978   0.0824
 -12.750  -0.9962   0.06735   0.06009  -0.0600   0.9937   0.0824
 -12.500  -1.0109   0.06416   0.05657  -0.0586   0.9899   0.0824
 -12.250  -1.0100   0.06127   0.05351  -0.0576   0.9864   0.0830
 -12.000  -0.9797   0.05977   0.05216  -0.0590   0.9836   0.0847
 -11.750  -0.9693   0.05759   0.04980  -0.0593   0.9800   0.0861
 -11.500  -0.9647   0.05528   0.04720  -0.0586   0.9765   0.0874
 -11.250  -0.9673   0.05324   0.04488  -0.0562   0.9730   0.0885
 -11.000  -0.9651   0.05115   0.04241  -0.0543   0.9699   0.0897
 -10.750  -0.9550   0.04911   0.04002  -0.0534   0.9672   0.0910
 -10.500  -0.9261   0.04766   0.03864  -0.0546   0.9648   0.0931
 -10.250  -0.8997   0.04650   0.03739  -0.0556   0.9622   0.0959
 -10.000  -0.8936   0.04532   0.03598  -0.0531   0.9588   0.0982
  -9.750  -0.8793   0.04408   0.03461  -0.0518   0.9565   0.1006
  -9.500  -0.8597   0.04323   0.03383  -0.0512   0.9544   0.1034
  -9.250  -0.8403   0.04234   0.03284  -0.0506   0.9523   0.1067
  -9.000  -0.8157   0.04137   0.03180  -0.0508   0.9499   0.1108
  -8.750  -0.7847   0.04069   0.03118  -0.0520   0.9474   0.1160
  -8.500  -0.7631   0.03995   0.03035  -0.0516   0.9448   0.1209
  -8.250  -0.7515   0.03938   0.02993  -0.0494   0.9429   0.1254
  -8.000  -0.7386   0.03885   0.02927  -0.0477   0.9413   0.1315
  -7.750  -0.7232   0.03822   0.02887  -0.0463   0.9395   0.1382
  -7.500  -0.7051   0.03758   0.02830  -0.0453   0.9370   0.1471
  -7.250  -0.6848   0.03694   0.02778  -0.0450   0.9345   0.1597
  -7.000  -0.6663   0.03627   0.02730  -0.0445   0.9330   0.1758
  -6.750  -0.6471   0.03553   0.02680  -0.0443   0.9318   0.1994
  -6.500  -0.6200   0.03463   0.02630  -0.0459   0.9298   0.2410
  -6.250  -0.5935   0.03363   0.02588  -0.0478   0.9269   0.3064
  -6.000  -0.5781   0.03275   0.02553  -0.0474   0.9245   0.3795
  -5.750  -0.5605   0.03259   0.02595  -0.0464   0.9235   0.4564
  -5.500  -0.5476   0.03335   0.02711  -0.0433   0.9225   0.5129
  -5.250  -0.5320   0.03437   0.02824  -0.0406   0.9203   0.5541
  -5.000  -0.5156   0.03554   0.02940  -0.0382   0.9193   0.5839
  -4.750  -0.5020   0.03686   0.03070  -0.0353   0.9198   0.6055
  -4.500  -0.4874   0.03824   0.03204  -0.0323   0.9187   0.6236
  -4.250  -0.4737   0.03953   0.03327  -0.0295   0.9193   0.6405
  -4.000  -0.4667   0.04123   0.03498  -0.0247   0.9239   0.6499
  -3.750  -0.4490   0.04279   0.03648  -0.0226   0.9266   0.6634
  -3.500  -0.5317   0.04050   0.03439  -0.0066   0.9835   0.6659
  -3.250  -0.4964   0.04291   0.03668  -0.0073   0.9783   0.6824
  -3.000  -0.4867   0.04384   0.03762  -0.0026   0.9705   0.6903
  -2.750  -0.4550   0.04568   0.03936  -0.0029   0.9643   0.7052
  -2.500  -0.4432   0.04663   0.04030   0.0011   0.9562   0.7149
  -2.250  -0.4150   0.04807   0.04165   0.0016   0.9488   0.7281
  -2.000  -0.3924   0.04940   0.04292   0.0024   0.9445   0.7422
  -1.750  -0.3768   0.04994   0.04345   0.0059   0.9325   0.7517
  -1.500  -0.3405   0.05201   0.04542   0.0042   0.9278   0.7676
  -1.250  -0.2463   0.05265   0.04586  -0.0012   0.8678   0.7809
  -1.000  -0.2419   0.05279   0.04598   0.0013   0.8684   0.7904
  -0.750  -0.2089   0.05228   0.04538   0.0019   0.8437   0.7991
  -0.500  -0.2025   0.05207   0.04514   0.0036   0.8360   0.8084
  -0.250  -0.1556   0.05237   0.04536   0.0018   0.8265   0.8160
   0.000  -0.1463   0.05230   0.04525   0.0026   0.8148   0.8254
   0.250  -0.1154   0.05221   0.04512   0.0034   0.8069   0.8319
   0.500  -0.0977   0.05229   0.04517   0.0042   0.7961   0.8400
   0.750  -0.0715   0.05219   0.04504   0.0041   0.7875   0.8471
   1.000  -0.0168   0.05232   0.04509   0.0007   0.7823   0.8541
   1.250  -0.0215   0.05232   0.04509   0.0034   0.7684   0.8606
   1.500   0.0223   0.05201   0.04475   0.0017   0.7627   0.8656
   1.750   0.0258   0.05210   0.04485   0.0042   0.7498   0.8705
   2.000   0.0703   0.05192   0.04462   0.0012   0.7432   0.8753
   2.250   0.0852   0.05211   0.04481   0.0017   0.7313   0.8793
   2.500   0.1198   0.05171   0.04440   0.0008   0.7239   0.8831
   2.750   0.1720   0.05122   0.04388  -0.0023   0.7202   0.8869
   3.000   0.1754   0.05158   0.04426  -0.0006   0.7048   0.8905
   3.250   0.2290   0.05099   0.04365  -0.0044   0.7008   0.8937
   3.500   0.2336   0.05130   0.04399  -0.0023   0.6860   0.8968
   3.750   0.2820   0.05038   0.04306  -0.0047   0.6817   0.8992
   4.000   0.2928   0.05075   0.04347  -0.0036   0.6672   0.9025
   4.250   0.3423   0.04965   0.04237  -0.0061   0.6628   0.9056
   4.500   0.3599   0.04996   0.04272  -0.0060   0.6486   0.9081
   4.750   0.4122   0.04847   0.04124  -0.0087   0.6440   0.9101
   5.000   0.4659   0.04636   0.03915  -0.0105   0.6415   0.9126
   5.250   0.4763   0.04651   0.03935  -0.0090   0.6255   0.9160
   5.500   0.5311   0.04425   0.03712  -0.0111   0.6230   0.9189
   5.750   0.5482   0.04434   0.03727  -0.0105   0.6075   0.9214
   6.000   0.6034   0.04190   0.03487  -0.0127   0.6048   0.9237
   6.250   0.6218   0.04168   0.03471  -0.0119   0.5900   0.9262
   6.500   0.6709   0.03891   0.03198  -0.0127   0.5871   0.9295
   6.750   0.7270   0.03580   0.02891  -0.0143   0.5849   0.9330
   7.000   0.7495   0.03530   0.02847  -0.0137   0.5688   0.9363
   7.250   0.7833   0.03417   0.02738  -0.0142   0.5541   0.9390
   7.500   0.8253   0.03218   0.02539  -0.0148   0.5399   0.9420
   7.750   0.8642   0.03066   0.02384  -0.0153   0.5192   0.9452
   8.000   0.9049   0.02929   0.02232  -0.0161   0.4925   0.9485
   8.250   0.9326   0.02898   0.02182  -0.0159   0.4599   0.9524
   8.500   0.9559   0.02888   0.02143  -0.0151   0.4270   0.9568
   8.750   0.9700   0.02954   0.02187  -0.0139   0.3953   0.9615
   9.000   0.9862   0.03032   0.02239  -0.0131   0.3664   0.9657
   9.250   0.9991   0.03127   0.02318  -0.0121   0.3409   0.9702
   9.500   1.0145   0.03223   0.02396  -0.0115   0.3187   0.9753
   9.750   1.0320   0.03319   0.02478  -0.0113   0.2992   0.9807
  10.000   1.0511   0.03413   0.02559  -0.0113   0.2823   0.9873
  10.250   1.0686   0.03481   0.02616  -0.0110   0.2683   1.0000
  10.500   1.0964   0.03576   0.02689  -0.0121   0.2547   1.0000
  10.750   1.1132   0.03711   0.02833  -0.0124   0.2433   1.0000
  11.000   1.1394   0.03823   0.02936  -0.0135   0.2329   1.0000
  11.250   1.1630   0.03938   0.03046  -0.0143   0.2233   1.0000
  11.500   1.1882   0.04065   0.03174  -0.0154   0.2148   1.0000
  11.750   1.2121   0.04184   0.03290  -0.0163   0.2069   1.0000
  12.000   1.2397   0.04314   0.03418  -0.0176   0.1998   1.0000
  12.250   1.2585   0.04459   0.03573  -0.0181   0.1932   1.0000
  12.500   1.2979   0.04559   0.03652  -0.0204   0.1865   1.0000
  12.750   1.3055   0.04753   0.03874  -0.0199   0.1817   1.0000
  13.000   1.3278   0.04894   0.04017  -0.0208   0.1763   1.0000
  13.250   1.3633   0.05026   0.04136  -0.0227   0.1710   1.0000
  13.500   1.3670   0.05250   0.04390  -0.0220   0.1673   1.0000
  13.750   1.3803   0.05437   0.04588  -0.0222   0.1632   1.0000
  14.000   1.4297   0.05533   0.04656  -0.0252   0.1580   1.0000
  14.250   1.4200   0.05816   0.04978  -0.0235   0.1556   1.0000
  14.500   1.4189   0.06092   0.05281  -0.0227   0.1527   1.0000
  15.000   1.4581   0.06448   0.05639  -0.0241   0.1461   1.0000
  15.250   1.4590   0.06763   0.05974  -0.0236   0.1438   1.0000
  15.500   1.4354   0.07189   0.06439  -0.0220   0.1423   1.0000
  15.750   1.4123   0.07654   0.06937  -0.0210   0.1408   1.0000
  16.000   1.3886   0.08155   0.07468  -0.0205   0.1393   1.0000
  16.250   1.3652   0.08687   0.08028  -0.0206   0.1378   1.0000
  16.500   1.3627   0.09052   0.08404  -0.0212   0.1359   1.0000
  16.750   1.2966   0.10122   0.09519  -0.0231   0.1358   1.0000
  17.000   1.2763   0.10760   0.10174  -0.0252   0.1345   1.0000
  17.250   1.2536   0.11482   0.10910  -0.0280   0.1333   1.0000
<< 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)