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=9


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0421 AIRFOIL (ls421-il)
Reynolds number: 200,000
Max Cl/Cd: 52.38 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ls421-il-200000.txt
Download as CSV file: xf-ls421-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.250  -0.7825   0.08704   0.08170  -0.0911   1.0000   0.0503
 -17.000  -0.8116   0.08006   0.07451  -0.0945   1.0000   0.0502
 -16.750  -0.8384   0.07405   0.06827  -0.0970   1.0000   0.0501
 -16.500  -0.8628   0.06898   0.06297  -0.0985   1.0000   0.0501
 -16.250  -0.8852   0.06471   0.05849  -0.0991   1.0000   0.0502
 -16.000  -0.9098   0.06182   0.05544  -0.0976   1.0000   0.0502
 -15.750  -0.9449   0.06154   0.05514  -0.0912   1.0000   0.0502
 -15.500  -0.9511   0.05767   0.05100  -0.0929   0.9962   0.0505
 -15.250  -0.9280   0.05529   0.04860  -0.0950   0.9938   0.0511
 -15.000  -0.9084   0.05306   0.04631  -0.0972   0.9913   0.0518
 -14.750  -0.8902   0.05101   0.04418  -0.0991   0.9873   0.0525
 -14.500  -0.8749   0.04865   0.04166  -0.1012   0.9836   0.0535
 -14.250  -0.8612   0.04608   0.03886  -0.1034   0.9805   0.0545
 -14.000  -0.8505   0.04357   0.03603  -0.1053   0.9765   0.0554
 -13.750  -0.8275   0.04183   0.03421  -0.1064   0.9716   0.0565
 -13.500  -0.7987   0.04056   0.03296  -0.1080   0.9681   0.0577
 -13.250  -0.7729   0.03917   0.03151  -0.1096   0.9647   0.0590
 -13.000  -0.7525   0.03784   0.03003  -0.1103   0.9600   0.0603
 -12.750  -0.7379   0.03655   0.02852  -0.1102   0.9536   0.0615
 -12.500  -0.7058   0.03563   0.02772  -0.1110   0.9503   0.0632
 -12.250  -0.6829   0.03473   0.02680  -0.1114   0.9464   0.0650
 -12.000  -0.6676   0.03391   0.02589  -0.1107   0.9397   0.0668
 -11.750  -0.6473   0.03305   0.02496  -0.1103   0.9344   0.0687
 -11.500  -0.6243   0.03236   0.02435  -0.1100   0.9303   0.0708
 -11.250  -0.6054   0.03170   0.02364  -0.1095   0.9259   0.0730
 -11.000  -0.5878   0.03102   0.02287  -0.1088   0.9206   0.0753
 -10.750  -0.5676   0.03038   0.02236  -0.1082   0.9163   0.0779
 -10.500  -0.5497   0.02974   0.02167  -0.1075   0.9123   0.0809
 -10.250  -0.5314   0.02908   0.02101  -0.1065   0.9090   0.0840
 -10.000  -0.5148   0.02850   0.02049  -0.1060   0.9040   0.0873
  -9.750  -0.4985   0.02790   0.01986  -0.1050   0.8990   0.0914
  -9.500  -0.4838   0.02720   0.01923  -0.1040   0.8947   0.0957
  -9.250  -0.4689   0.02650   0.01854  -0.1028   0.8913   0.1012
  -9.000  -0.4549   0.02589   0.01795  -0.1016   0.8880   0.1078
  -8.750  -0.4454   0.02528   0.01744  -0.1002   0.8829   0.1151
  -8.500  -0.4384   0.02469   0.01692  -0.0982   0.8780   0.1245
  -8.250  -0.4333   0.02406   0.01636  -0.0956   0.8735   0.1361
  -8.000  -0.4237   0.02331   0.01569  -0.0939   0.8700   0.1526
  -7.750  -0.4125   0.02267   0.01516  -0.0927   0.8668   0.1738
  -7.500  -0.4064   0.02226   0.01493  -0.0912   0.8612   0.1972
  -7.250  -0.3942   0.02168   0.01455  -0.0903   0.8568   0.2303
  -7.000  -0.3757   0.02096   0.01406  -0.0903   0.8535   0.2762
  -6.750  -0.3529   0.02018   0.01353  -0.0909   0.8508   0.3282
  -6.500  -0.3263   0.01950   0.01310  -0.0918   0.8487   0.3825
  -6.250  -0.2981   0.01902   0.01289  -0.0927   0.8469   0.4389
  -6.000  -0.2802   0.01924   0.01342  -0.0919   0.8426   0.4862
  -5.750  -0.2619   0.01973   0.01412  -0.0907   0.8378   0.5271
  -5.500  -0.2359   0.02009   0.01454  -0.0904   0.8344   0.5607
  -5.250  -0.2072   0.02052   0.01500  -0.0901   0.8318   0.5854
  -5.000  -0.1772   0.02101   0.01547  -0.0900   0.8299   0.6055
  -4.750  -0.1468   0.02152   0.01594  -0.0901   0.8281   0.6215
  -4.500  -0.1177   0.02214   0.01653  -0.0895   0.8265   0.6323
  -4.250  -0.0876   0.02265   0.01699  -0.0892   0.8250   0.6419
  -4.000  -0.0953   0.02434   0.01877  -0.0838   0.8150   0.6473
  -3.750  -0.0684   0.02477   0.01911  -0.0841   0.8118   0.6596
  -3.500  -0.0450   0.02553   0.01991  -0.0818   0.8093   0.6635
  -3.250  -0.0171   0.02615   0.02052  -0.0804   0.8075   0.6689
  -3.000   0.0189   0.02621   0.02049  -0.0821   0.8062   0.6806
  -2.750   0.0439   0.02691   0.02121  -0.0798   0.8046   0.6837
  -2.500   0.0168   0.02899   0.02339  -0.0714   0.7919   0.6880
  -2.250   0.0416   0.02951   0.02389  -0.0702   0.7889   0.6954
  -2.000   0.0766   0.02945   0.02377  -0.0715   0.7871   0.7036
  -1.750   0.1062   0.02965   0.02397  -0.0705   0.7856   0.7064
  -1.500   0.1385   0.02974   0.02404  -0.0702   0.7844   0.7098
  -1.250   0.1091   0.03148   0.02582  -0.0626   0.7703   0.7171
  -1.000   0.1488   0.03116   0.02544  -0.0657   0.7679   0.7244
  -0.750   0.1804   0.03112   0.02540  -0.0651   0.7661   0.7269
  -0.500   0.2141   0.03099   0.02526  -0.0650   0.7648   0.7300
  -0.250   0.2513   0.03071   0.02496  -0.0658   0.7637   0.7342
   0.000   0.2353   0.03216   0.02641  -0.0615   0.7493   0.7429
   0.250   0.2685   0.03186   0.02611  -0.0619   0.7468   0.7470
   0.500   0.3026   0.03152   0.02579  -0.0616   0.7453   0.7498
   0.750   0.3422   0.03100   0.02526  -0.0625   0.7442   0.7532
   1.000   0.3862   0.03025   0.02448  -0.0646   0.7433   0.7570
   1.250   0.4348   0.02935   0.02354  -0.0681   0.7423   0.7616
   1.500   0.4907   0.02828   0.02241  -0.0735   0.7413   0.7663
   1.750   0.4712   0.02952   0.02375  -0.0661   0.7267   0.7688
   2.000   0.5119   0.02861   0.02284  -0.0672   0.7252   0.7710
   2.250   0.5544   0.02768   0.02190  -0.0689   0.7236   0.7734
   2.500   0.6015   0.02656   0.02076  -0.0714   0.7221   0.7762
   2.750   0.6393   0.02580   0.01999  -0.0729   0.7171   0.7792
   3.000   0.6648   0.02549   0.01970  -0.0731   0.7077   0.7828
   3.250   0.7197   0.02431   0.01846  -0.0781   0.7044   0.7861
   3.500   0.7636   0.02323   0.01735  -0.0802   0.7012   0.7877
   3.750   0.7747   0.02327   0.01747  -0.0773   0.6912   0.7896
   4.000   0.8078   0.02255   0.01676  -0.0776   0.6852   0.7916
   4.250   0.8507   0.02164   0.01580  -0.0795   0.6806   0.7939
   4.500   0.8637   0.02166   0.01593  -0.0773   0.6687   0.7965
   4.750   0.9062   0.02083   0.01504  -0.0796   0.6616   0.7986
   5.000   0.9249   0.02073   0.01502  -0.0785   0.6484   0.8012
   5.250   0.9571   0.02033   0.01462  -0.0796   0.6362   0.8041
   5.500   0.9899   0.01992   0.01416  -0.0807   0.6218   0.8068
   5.750   1.0046   0.01976   0.01402  -0.0782   0.6041   0.8087
   6.000   1.0184   0.01967   0.01393  -0.0756   0.5836   0.8106
   6.250   1.0267   0.01975   0.01397  -0.0721   0.5586   0.8129
   6.500   1.0413   0.01988   0.01392  -0.0699   0.5277   0.8152
   6.750   1.0527   0.02040   0.01425  -0.0676   0.4917   0.8178
   7.000   1.0620   0.02126   0.01488  -0.0654   0.4544   0.8211
   7.250   1.0706   0.02238   0.01577  -0.0636   0.4184   0.8241
   7.500   1.0757   0.02359   0.01678  -0.0612   0.3861   0.8263
   7.750   1.0782   0.02479   0.01784  -0.0583   0.3570   0.8283
   8.000   1.0808   0.02614   0.01902  -0.0556   0.3311   0.8305
   8.250   1.0867   0.02743   0.02021  -0.0535   0.3068   0.8328
   8.500   1.0939   0.02877   0.02142  -0.0518   0.2849   0.8353
   8.750   1.1028   0.03011   0.02266  -0.0505   0.2658   0.8378
   9.000   1.1136   0.03145   0.02389  -0.0495   0.2491   0.8407
   9.250   1.1258   0.03285   0.02517  -0.0489   0.2347   0.8436
   9.500   1.1350   0.03397   0.02625  -0.0473   0.2226   0.8459
   9.750   1.1466   0.03504   0.02731  -0.0460   0.2120   0.8482
  10.000   1.1564   0.03631   0.02845  -0.0447   0.2030   0.8506
  10.250   1.1712   0.03735   0.02956  -0.0441   0.1943   0.8533
  10.500   1.1842   0.03857   0.03065  -0.0433   0.1869   0.8560
  10.750   1.2006   0.03967   0.03182  -0.0431   0.1798   0.8589
  11.000   1.2155   0.04090   0.03295  -0.0427   0.1735   0.8614
  11.250   1.2288   0.04189   0.03400  -0.0416   0.1680   0.8639
  11.500   1.2417   0.04296   0.03510  -0.0407   0.1628   0.8667
  11.750   1.2570   0.04394   0.03595  -0.0398   0.1579   0.8700
  12.000   1.2712   0.04514   0.03729  -0.0393   0.1535   0.8736
  12.250   1.2865   0.04638   0.03854  -0.0391   0.1492   0.8771
  12.500   1.3038   0.04719   0.03922  -0.0384   0.1450   0.8800
  12.750   1.3144   0.04849   0.04068  -0.0375   0.1416   0.8832
  13.000   1.3275   0.04970   0.04195  -0.0368   0.1380   0.8867
  13.250   1.3426   0.05085   0.04308  -0.0364   0.1347   0.8903
  13.500   1.3613   0.05190   0.04410  -0.0363   0.1314   0.8938
  13.750   1.3703   0.05333   0.04568  -0.0353   0.1284   0.8973
  14.000   1.3815   0.05463   0.04704  -0.0346   0.1255   0.9013
  14.250   1.3967   0.05572   0.04809  -0.0341   0.1228   0.9058
  14.500   1.4134   0.05686   0.04924  -0.0337   0.1201   0.9104
  14.750   1.4196   0.05848   0.05104  -0.0327   0.1177   0.9153
  15.000   1.4293   0.06002   0.05266  -0.0320   0.1153   0.9207
  15.250   1.4424   0.06129   0.05391  -0.0316   0.1130   0.9259
  15.500   1.4619   0.06180   0.05432  -0.0308   0.1105   0.9318
  15.750   1.4637   0.06411   0.05687  -0.0302   0.1087   0.9381
  16.000   1.4674   0.06597   0.05889  -0.0292   0.1068   0.9456
  16.250   1.4742   0.06760   0.06060  -0.0284   0.1049   0.9553
  16.500   1.4830   0.06871   0.06171  -0.0275   0.1031   0.9748
  16.750   1.5073   0.06915   0.06203  -0.0277   0.1010   1.0000
  17.000   1.5060   0.07243   0.06557  -0.0282   0.0995   1.0000
  17.250   1.5077   0.07551   0.06884  -0.0287   0.0978   1.0000
  17.500   1.5139   0.07812   0.07156  -0.0294   0.0962   1.0000
  17.750   1.5244   0.08023   0.07370  -0.0300   0.0946   1.0000
  18.000   1.5446   0.08125   0.07463  -0.0305   0.0929   1.0000
  18.250   1.5516   0.08376   0.07724  -0.0310   0.0915   1.0000
  18.500   1.5429   0.08799   0.08173  -0.0318   0.0903   1.0000
  18.750   1.5373   0.09198   0.08592  -0.0328   0.0891   1.0000
  19.000   1.5337   0.09578   0.08987  -0.0339   0.0878   1.0000
  19.250   1.5352   0.09893   0.09312  -0.0349   0.0866   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)