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LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED L-188 TIP AIRFOIL (l188tip-il)
Reynolds number: 200,000
Max Cl/Cd: 79.26 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-l188tip-il-200000.txt
Download as CSV file: xf-l188tip-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4239   0.10388   0.10024  -0.0418   1.0000   0.0617
  -9.750  -0.4361   0.10128   0.09769  -0.0410   1.0000   0.0634
  -9.500  -0.4613   0.09788   0.09438  -0.0417   1.0000   0.0653
  -9.250  -0.4155   0.09142   0.08828  -0.0361   1.0000   0.0678
  -9.000  -0.4141   0.08949   0.08637  -0.0338   1.0000   0.0687
  -8.750  -0.4069   0.08590   0.08278  -0.0349   0.9984   0.0703
  -8.500  -0.4041   0.08096   0.07784  -0.0380   0.9960   0.0723
  -8.250  -0.4106   0.07462   0.07150  -0.0429   0.9933   0.0745
  -8.000  -0.5630   0.07384   0.07049  -0.0465   0.9947   0.0686
  -7.750  -0.5460   0.07084   0.06747  -0.0484   0.9911   0.0704
  -7.500  -0.5335   0.06570   0.06218  -0.0533   0.9861   0.0733
  -7.250  -0.5676   0.04163   0.03633  -0.0600   0.9762   0.0485
  -7.000  -0.5430   0.03726   0.03146  -0.0613   0.9732   0.0466
  -6.750  -0.5177   0.03408   0.02761  -0.0621   0.9698   0.0474
  -6.500  -0.4979   0.03078   0.02389  -0.0618   0.9650   0.0479
  -6.250  -0.4692   0.02824   0.02110  -0.0629   0.9619   0.0488
  -6.000  -0.4356   0.02674   0.01944  -0.0646   0.9595   0.0504
  -5.750  -0.3990   0.02565   0.01816  -0.0667   0.9576   0.0533
  -5.500  -0.3770   0.02470   0.01692  -0.0656   0.9517   0.0554
  -5.250  -0.3461   0.02311   0.01516  -0.0665   0.9484   0.0577
  -5.000  -0.3114   0.02229   0.01434  -0.0682   0.9456   0.0612
  -4.750  -0.2734   0.02173   0.01361  -0.0702   0.9435   0.0659
  -4.500  -0.2421   0.02066   0.01259  -0.0712   0.9404   0.0705
  -4.250  -0.2190   0.02028   0.01218  -0.0704   0.9340   0.0760
  -4.000  -0.1853   0.01949   0.01144  -0.0718   0.9308   0.0831
  -3.750  -0.1482   0.01891   0.01085  -0.0738   0.9286   0.0932
  -3.500  -0.1092   0.01833   0.01033  -0.0763   0.9269   0.1072
  -3.250  -0.0928   0.01807   0.01011  -0.0742   0.9186   0.1206
  -3.000  -0.0592   0.01747   0.00967  -0.0756   0.9152   0.1499
  -2.750  -0.0229   0.01660   0.00925  -0.0779   0.9130   0.2296
  -2.500   0.0093   0.01506   0.00913  -0.0795   0.9114   0.5547
  -2.250   0.0236   0.01501   0.00939  -0.0766   0.9030   0.6556
  -2.000   0.0544   0.01493   0.00944  -0.0767   0.8992   0.7180
  -1.750   0.0886   0.01483   0.00938  -0.0774   0.8968   0.7611
  -1.500   0.1222   0.01470   0.00927  -0.0779   0.8947   0.7946
  -1.250   0.1362   0.01482   0.00946  -0.0750   0.8854   0.8200
  -1.000   0.1665   0.01466   0.00934  -0.0748   0.8821   0.8479
  -0.750   0.1982   0.01448   0.00920  -0.0748   0.8797   0.8763
  -0.500   0.2194   0.01461   0.00938  -0.0730   0.8727   0.9067
  -0.250   0.2602   0.01463   0.00942  -0.0748   0.8695   0.9450
   0.000   0.3180   0.01464   0.00940  -0.0804   0.8685   0.9725
   0.250   0.3690   0.01452   0.00924  -0.0852   0.8666   0.9823
   0.500   0.4204   0.01433   0.00901  -0.0901   0.8648   0.9888
   0.750   0.4706   0.01411   0.00876  -0.0948   0.8631   0.9960
   1.000   0.4878   0.01421   0.00886  -0.0937   0.8533   1.0000
   1.250   0.5127   0.01398   0.00859  -0.0932   0.8488   1.0000
   1.500   0.5275   0.01409   0.00868  -0.0910   0.8404   1.0000
   1.750   0.5547   0.01392   0.00848  -0.0907   0.8348   1.0000
   2.000   0.5876   0.01346   0.00799  -0.0911   0.8293   1.0000
   2.250   0.6144   0.01292   0.00743  -0.0900   0.8180   1.0000
   2.500   0.6402   0.01249   0.00696  -0.0889   0.8062   1.0000
   2.750   0.6700   0.01209   0.00654  -0.0886   0.7974   1.0000
   3.000   0.6968   0.01185   0.00629  -0.0879   0.7871   1.0000
   3.250   0.7215   0.01172   0.00617  -0.0869   0.7755   1.0000
   3.500   0.7485   0.01156   0.00599  -0.0863   0.7641   1.0000
   3.750   0.7761   0.01140   0.00582  -0.0858   0.7518   1.0000
   4.000   0.8025   0.01131   0.00571  -0.0851   0.7375   1.0000
   4.250   0.8269   0.01129   0.00568  -0.0840   0.7208   1.0000
   4.500   0.8505   0.01131   0.00570  -0.0829   0.7015   1.0000
   4.750   0.8744   0.01135   0.00572  -0.0817   0.6797   1.0000
   5.000   0.8972   0.01144   0.00576  -0.0804   0.6539   1.0000
   5.250   0.9186   0.01159   0.00583  -0.0788   0.6217   1.0000
   5.500   0.9377   0.01185   0.00594  -0.0768   0.5781   1.0000
   5.750   0.9525   0.01232   0.00613  -0.0740   0.5134   1.0000
   6.000   0.9580   0.01325   0.00652  -0.0698   0.4153   1.0000
   6.250   0.9597   0.01451   0.00721  -0.0652   0.3250   1.0000
   6.500   0.9656   0.01567   0.00796  -0.0616   0.2585   1.0000
   6.750   0.9747   0.01671   0.00869  -0.0587   0.2124   1.0000
   7.000   0.9851   0.01762   0.00940  -0.0559   0.1814   1.0000
   7.250   0.9961   0.01851   0.01013  -0.0532   0.1592   1.0000
   7.500   1.0079   0.01944   0.01092  -0.0508   0.1422   1.0000
   7.750   1.0216   0.02030   0.01172  -0.0487   0.1285   1.0000
   8.000   1.0371   0.02108   0.01249  -0.0469   0.1172   1.0000
   8.250   1.0518   0.02197   0.01337  -0.0450   0.1080   1.0000
   8.500   1.0649   0.02307   0.01435  -0.0430   0.1002   1.0000
   8.750   1.0824   0.02377   0.01516  -0.0416   0.0934   1.0000
   9.000   1.0969   0.02497   0.01625  -0.0399   0.0874   1.0000
   9.250   1.1145   0.02572   0.01712  -0.0386   0.0823   1.0000
   9.500   1.1305   0.02667   0.01804  -0.0371   0.0777   1.0000
   9.750   1.1490   0.02784   0.01925  -0.0360   0.0735   1.0000
  10.000   1.1664   0.02876   0.02025  -0.0347   0.0697   1.0000
  10.250   1.1840   0.02983   0.02127  -0.0336   0.0663   1.0000
  10.500   1.2048   0.03116   0.02268  -0.0328   0.0630   1.0000
  10.750   1.2223   0.03224   0.02390  -0.0316   0.0603   1.0000
  11.000   1.2394   0.03332   0.02502  -0.0305   0.0578   1.0000
  11.250   1.2666   0.03523   0.02687  -0.0308   0.0549   1.0000
  11.500   1.2779   0.03636   0.02825  -0.0288   0.0532   1.0000
  11.750   1.2925   0.03776   0.02984  -0.0274   0.0513   1.0000
  12.000   1.3064   0.03919   0.03139  -0.0260   0.0497   1.0000
  12.250   1.3212   0.04058   0.03281  -0.0248   0.0481   1.0000
  12.500   1.3422   0.04325   0.03556  -0.0247   0.0463   1.0000
  12.750   1.3427   0.04494   0.03755  -0.0218   0.0454   1.0000
  13.000   1.3443   0.04704   0.03994  -0.0193   0.0444   1.0000
  13.250   1.3453   0.04939   0.04256  -0.0170   0.0435   1.0000
  13.500   1.3448   0.05184   0.04524  -0.0148   0.0427   1.0000
  13.750   1.3442   0.05424   0.04782  -0.0129   0.0420   1.0000
  14.000   1.3439   0.05657   0.05028  -0.0111   0.0412   1.0000
  14.250   1.3430   0.05893   0.05276  -0.0096   0.0405   1.0000
  14.500   1.3437   0.06171   0.05561  -0.0084   0.0398   1.0000
  15.000   1.3116   0.07049   0.06487  -0.0056   0.0391   1.0000
  15.250   1.2886   0.07513   0.06978  -0.0049   0.0390   1.0000
  15.500   1.2639   0.08044   0.07536  -0.0051   0.0389   1.0000
  15.750   1.2378   0.08642   0.08159  -0.0062   0.0389   1.0000
  16.000   1.2106   0.09320   0.08859  -0.0082   0.0389   1.0000
  16.250   1.1822   0.10084   0.09645  -0.0114   0.0390   1.0000
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