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LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: LOCKHEED L-188 TIP AIRFOIL (l188tip-il)
Reynolds number: 100,000
Max Cl/Cd: 53.19 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-l188tip-il-100000-n5.txt
Download as CSV file: xf-l188tip-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED L-188 TIP 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4530   0.09439   0.08913  -0.0490   1.0000   0.0373
  -9.750  -0.4679   0.09039   0.08520  -0.0490   1.0000   0.0372
  -9.500  -0.4868   0.08616   0.08105  -0.0490   1.0000   0.0371
  -9.250  -0.5111   0.08148   0.07647  -0.0492   1.0000   0.0368
  -9.000  -0.5572   0.07464   0.06971  -0.0507   1.0000   0.0356
  -8.750  -0.6076   0.06363   0.05843  -0.0549   0.9960   0.0346
  -8.500  -0.6032   0.05873   0.05330  -0.0581   0.9905   0.0352
  -8.250  -0.5981   0.05308   0.04727  -0.0611   0.9851   0.0357
  -8.000  -0.5917   0.04780   0.04153  -0.0625   0.9797   0.0361
  -7.750  -0.5789   0.04324   0.03645  -0.0637   0.9748   0.0367
  -7.500  -0.5589   0.03916   0.03177  -0.0651   0.9715   0.0377
  -7.250  -0.5434   0.03587   0.02780  -0.0646   0.9662   0.0395
  -7.000  -0.5194   0.03387   0.02550  -0.0652   0.9623   0.0411
  -6.750  -0.4908   0.03232   0.02374  -0.0663   0.9594   0.0426
  -6.500  -0.4603   0.03052   0.02162  -0.0676   0.9572   0.0443
  -6.250  -0.4394   0.02908   0.01982  -0.0667   0.9518   0.0465
  -6.000  -0.4118   0.02789   0.01848  -0.0672   0.9480   0.0490
  -5.750  -0.3810   0.02691   0.01740  -0.0683   0.9451   0.0518
  -5.500  -0.3478   0.02580   0.01605  -0.0695   0.9428   0.0551
  -5.250  -0.3245   0.02500   0.01522  -0.0690   0.9378   0.0584
  -5.000  -0.2974   0.02431   0.01448  -0.0692   0.9334   0.0623
  -4.750  -0.2662   0.02352   0.01358  -0.0701   0.9302   0.0672
  -4.500  -0.2330   0.02286   0.01295  -0.0715   0.9277   0.0734
  -4.250  -0.2077   0.02229   0.01233  -0.0712   0.9230   0.0796
  -4.000  -0.1824   0.02183   0.01188  -0.0710   0.9177   0.0878
  -3.750  -0.1513   0.02128   0.01135  -0.0719   0.9142   0.0986
  -3.500  -0.1176   0.02076   0.01087  -0.0733   0.9117   0.1140
  -3.250  -0.0937   0.02040   0.01055  -0.0728   0.9062   0.1328
  -3.000  -0.0678   0.01996   0.01025  -0.0728   0.9009   0.1619
  -2.750  -0.0366   0.01935   0.00992  -0.0738   0.8976   0.2204
  -2.500  -0.0058   0.01836   0.00962  -0.0750   0.8951   0.3690
  -2.250   0.0105   0.01780   0.00984  -0.0728   0.8882   0.5604
  -2.000   0.0355   0.01766   0.00994  -0.0717   0.8834   0.6567
  -1.750   0.0650   0.01756   0.00992  -0.0714   0.8802   0.7166
  -1.500   0.0882   0.01757   0.00996  -0.0701   0.8747   0.7587
  -1.250   0.1109   0.01757   0.00999  -0.0686   0.8686   0.7947
  -1.000   0.1395   0.01745   0.00993  -0.0680   0.8651   0.8348
  -0.750   0.1739   0.01735   0.00993  -0.0680   0.8629   0.8912
  -0.500   0.2148   0.01751   0.01011  -0.0702   0.8581   0.9377
  -0.250   0.2564   0.01756   0.01009  -0.0732   0.8536   0.9591
   0.000   0.3006   0.01752   0.00997  -0.0768   0.8504   0.9760
   0.250   0.3462   0.01744   0.00982  -0.0806   0.8480   0.9919
   0.500   0.3682   0.01756   0.00989  -0.0802   0.8397   1.0000
   0.750   0.3928   0.01753   0.00979  -0.0798   0.8342   1.0000
   1.250   0.4371   0.01769   0.00986  -0.0781   0.8207   1.0000
   1.500   0.4681   0.01762   0.00976  -0.0787   0.8168   1.0000
   1.750   0.4866   0.01785   0.00998  -0.0771   0.8082   1.0000
   2.000   0.5157   0.01784   0.00995  -0.0773   0.8032   1.0000
   2.250   0.5434   0.01786   0.00997  -0.0773   0.7978   1.0000
   2.500   0.5665   0.01798   0.01011  -0.0764   0.7896   1.0000
   2.750   0.6022   0.01766   0.00981  -0.0774   0.7850   1.0000
   3.000   0.6252   0.01754   0.00970  -0.0761   0.7724   1.0000
   3.250   0.6529   0.01718   0.00935  -0.0753   0.7585   1.0000
   3.500   0.6812   0.01682   0.00900  -0.0746   0.7435   1.0000
   3.750   0.7085   0.01660   0.00880  -0.0739   0.7286   1.0000
   4.000   0.7356   0.01646   0.00866  -0.0733   0.7130   1.0000
   4.250   0.7625   0.01634   0.00858  -0.0726   0.6958   1.0000
   4.500   0.7902   0.01622   0.00846  -0.0720   0.6765   1.0000
   4.750   0.8136   0.01626   0.00850  -0.0708   0.6534   1.0000
   5.000   0.8386   0.01627   0.00849  -0.0698   0.6263   1.0000
   5.250   0.8609   0.01639   0.00855  -0.0684   0.5917   1.0000
   5.500   0.8824   0.01659   0.00861  -0.0668   0.5453   1.0000
   5.750   0.9004   0.01700   0.00874  -0.0646   0.4784   1.0000
   6.000   0.9113   0.01784   0.00905  -0.0614   0.3932   1.0000
   6.250   0.9195   0.01891   0.00966  -0.0582   0.3227   1.0000
   6.500   0.9294   0.01995   0.01037  -0.0554   0.2691   1.0000
   6.750   0.9411   0.02091   0.01111  -0.0530   0.2293   1.0000
   7.000   0.9531   0.02181   0.01183  -0.0506   0.1988   1.0000
   7.250   0.9659   0.02268   0.01257  -0.0484   0.1752   1.0000
   7.500   0.9789   0.02357   0.01335  -0.0462   0.1567   1.0000
   7.750   0.9929   0.02444   0.01416  -0.0443   0.1414   1.0000
   8.000   1.0069   0.02534   0.01503  -0.0425   0.1288   1.0000
   8.250   1.0217   0.02621   0.01591  -0.0407   0.1179   1.0000
   8.500   1.0358   0.02716   0.01685  -0.0390   0.1091   1.0000
   8.750   1.0492   0.02817   0.01783  -0.0372   0.1015   1.0000
   9.000   1.0641   0.02912   0.01887  -0.0356   0.0944   1.0000
   9.250   1.0773   0.03020   0.01993  -0.0339   0.0888   1.0000
   9.500   1.0920   0.03125   0.02105  -0.0324   0.0834   1.0000
   9.750   1.1061   0.03232   0.02217  -0.0309   0.0785   1.0000
  10.000   1.1191   0.03357   0.02341  -0.0293   0.0748   1.0000
  10.250   1.1347   0.03468   0.02467  -0.0280   0.0705   1.0000
  10.500   1.1481   0.03587   0.02590  -0.0266   0.0671   1.0000
  10.750   1.1612   0.03724   0.02726  -0.0252   0.0643   1.0000
  11.000   1.1767   0.03852   0.02877  -0.0239   0.0612   1.0000
  11.250   1.1898   0.03985   0.03020  -0.0226   0.0583   1.0000
  11.500   1.2015   0.04124   0.03161  -0.0213   0.0561   1.0000
  11.750   1.2151   0.04285   0.03331  -0.0201   0.0541   1.0000
  12.000   1.2274   0.04451   0.03522  -0.0187   0.0519   1.0000
  12.250   1.2375   0.04617   0.03706  -0.0173   0.0499   1.0000
  12.500   1.2459   0.04782   0.03879  -0.0160   0.0483   1.0000
  12.750   1.2553   0.04954   0.04053  -0.0148   0.0469   1.0000
  13.000   1.2627   0.05179   0.04300  -0.0134   0.0457   1.0000
  13.250   1.2657   0.05429   0.04583  -0.0118   0.0444   1.0000
  13.500   1.2664   0.05688   0.04867  -0.0104   0.0432   1.0000
  13.750   1.2658   0.05947   0.05149  -0.0091   0.0421   1.0000
  14.000   1.2644   0.06209   0.05428  -0.0080   0.0411   1.0000
  14.250   1.2633   0.06470   0.05701  -0.0072   0.0403   1.0000
  14.500   1.2631   0.06736   0.05975  -0.0065   0.0396   1.0000
  14.750   1.2573   0.07086   0.06342  -0.0059   0.0390   1.0000
  15.000   1.2409   0.07561   0.06851  -0.0058   0.0387   1.0000
  15.250   1.2216   0.08095   0.07417  -0.0064   0.0384   1.0000
  15.500   1.1993   0.08705   0.08057  -0.0079   0.0382   1.0000
  15.750   1.1740   0.09414   0.08795  -0.0105   0.0381   1.0000
  16.000   1.1448   0.10257   0.09666  -0.0145   0.0381   1.0000
  16.250   1.1105   0.11306   0.10740  -0.0206   0.0382   1.0000
  16.500   1.0656   0.12762   0.12218  -0.0302   0.0386   1.0000
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