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LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED L-188 TIP AIRFOIL (l188tip-il)
Reynolds number: 50,000
Max Cl/Cd: 35.05 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-l188tip-il-50000.txt
Download as CSV file: xf-l188tip-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4013   0.10279   0.09587  -0.0218   1.0000   0.3196
  -8.000  -0.4336   0.10296   0.09620  -0.0186   1.0000   0.3309
  -7.750  -0.4333   0.10051   0.09381  -0.0158   1.0000   0.3472
  -7.500  -0.4377   0.09843   0.09181  -0.0127   1.0000   0.3638
  -7.250  -0.4447   0.09653   0.08999  -0.0092   1.0000   0.3805
  -7.000  -0.4554   0.09489   0.08844  -0.0054   1.0000   0.3972
  -6.750  -0.4166   0.08983   0.08330  -0.0046   1.0000   0.4196
  -6.500  -0.4224   0.08821   0.08176  -0.0007   1.0000   0.4426
  -6.250  -0.4548   0.08820   0.08191   0.0055   1.0000   0.4623
  -6.000  -0.4411   0.08551   0.07924   0.0088   1.0000   0.4946
  -5.500  -0.5470   0.05549   0.04760  -0.0341   1.0000   0.1667
  -5.250  -0.5308   0.05151   0.04357  -0.0336   1.0000   0.1615
  -5.000  -0.5105   0.04670   0.03761  -0.0350   1.0000   0.1510
  -4.750  -0.4906   0.04353   0.03427  -0.0349   1.0000   0.1530
  -4.500  -0.4685   0.04092   0.03135  -0.0348   1.0000   0.1550
  -4.250  -0.4446   0.03852   0.02855  -0.0347   1.0000   0.1568
  -4.000  -0.4204   0.03665   0.02628  -0.0345   1.0000   0.1628
  -3.750  -0.3946   0.03482   0.02389  -0.0344   1.0000   0.1679
  -3.500  -0.3711   0.03331   0.02237  -0.0340   1.0000   0.1772
  -3.250  -0.3460   0.03194   0.02077  -0.0336   1.0000   0.1877
  -3.000  -0.3213   0.03082   0.01953  -0.0332   1.0000   0.2022
  -2.750  -0.2966   0.02976   0.01850  -0.0326   1.0000   0.2209
  -2.500  -0.2717   0.02886   0.01759  -0.0321   1.0000   0.2488
  -2.250  -0.2451   0.02774   0.01679  -0.0320   1.0000   0.2959
  -2.000  -0.2207   0.02504   0.01659  -0.0300   1.0000   0.6246
  -1.750  -0.2034   0.02450   0.01668  -0.0229   1.0000   1.0000
  -1.500  -0.1844   0.02463   0.01634  -0.0228   1.0000   1.0000
  -1.250  -0.1642   0.02487   0.01621  -0.0227   1.0000   1.0000
  -1.000  -0.1434   0.02519   0.01619  -0.0228   1.0000   1.0000
  -0.750  -0.1223   0.02557   0.01628  -0.0228   1.0000   1.0000
  -0.500  -0.1010   0.02600   0.01646  -0.0229   1.0000   1.0000
  -0.250  -0.0798   0.02647   0.01670  -0.0230   1.0000   1.0000
   0.000  -0.0587   0.02699   0.01701  -0.0230   1.0000   1.0000
   0.250  -0.0376   0.02755   0.01739  -0.0231   1.0000   1.0000
   0.500  -0.0167   0.02815   0.01783  -0.0231   1.0000   1.0000
   0.750   0.0041   0.02878   0.01831  -0.0232   1.0000   1.0000
   1.000   0.0247   0.02945   0.01886  -0.0232   1.0000   1.0000
   1.250   0.0451   0.03017   0.01946  -0.0233   1.0000   1.0000
   1.500   0.0652   0.03092   0.02012  -0.0234   1.0000   1.0000
   1.750   0.0852   0.03171   0.02082  -0.0234   1.0000   1.0000
   2.000   0.1049   0.03254   0.02159  -0.0235   1.0000   1.0000
   2.250   0.1244   0.03341   0.02241  -0.0236   1.0000   1.0000
   2.500   0.1436   0.03433   0.02329  -0.0237   1.0000   1.0000
   2.750   0.1625   0.03530   0.02423  -0.0239   1.0000   1.0000
   3.000   0.1810   0.03632   0.02523  -0.0240   1.0000   1.0000
   3.250   0.1993   0.03739   0.02630  -0.0242   1.0000   1.0000
   3.500   0.2487   0.03951   0.02844  -0.0303   0.9857   1.0000
   3.750   0.3044   0.04159   0.03058  -0.0373   0.9608   1.0000
   4.000   0.3510   0.04326   0.03233  -0.0421   0.9378   1.0000
   4.250   0.3926   0.04463   0.03378  -0.0458   0.9152   1.0000
   4.500   0.4391   0.04595   0.03521  -0.0498   0.8918   1.0000
   4.750   0.4760   0.04682   0.03620  -0.0519   0.8675   1.0000
   5.000   0.5205   0.04754   0.03709  -0.0547   0.8425   1.0000
   5.250   0.5717   0.04778   0.03751  -0.0578   0.8166   1.0000
   5.500   0.6090   0.04774   0.03763  -0.0585   0.7894   1.0000
   5.750   0.6545   0.04712   0.03725  -0.0595   0.7617   1.0000
   6.000   0.7088   0.04553   0.03594  -0.0606   0.7337   1.0000
   6.250   0.7834   0.04176   0.03257  -0.0619   0.7067   1.0000
   6.500   0.8416   0.03755   0.02874  -0.0603   0.6763   1.0000
   6.750   0.8976   0.03274   0.02429  -0.0574   0.6349   1.0000
   7.000   0.9515   0.02782   0.01938  -0.0533   0.5450   1.0000
   7.250   0.9702   0.02768   0.01810  -0.0481   0.4142   1.0000
   7.500   0.9851   0.02967   0.01917  -0.0453   0.3390   1.0000
   7.750   1.0117   0.03175   0.02077  -0.0448   0.2881   1.0000
   8.000   1.0443   0.03382   0.02254  -0.0453   0.2526   1.0000
   8.250   1.0757   0.03597   0.02459  -0.0457   0.2272   1.0000
   8.500   1.1043   0.03812   0.02672  -0.0457   0.2081   1.0000
   8.750   1.1307   0.04047   0.02918  -0.0455   0.1938   1.0000
   9.000   1.1537   0.04293   0.03178  -0.0449   0.1821   1.0000
   9.250   1.1825   0.04575   0.03450  -0.0452   0.1719   1.0000
   9.500   1.1897   0.04826   0.03761  -0.0423   0.1655   1.0000
   9.750   1.2126   0.05112   0.04052  -0.0418   0.1584   1.0000
  10.000   1.2177   0.05445   0.04430  -0.0391   0.1547   1.0000
  10.250   1.2156   0.05766   0.04802  -0.0356   0.1514   1.0000
  10.500   1.2150   0.06094   0.05166  -0.0326   0.1482   1.0000
  10.750   1.2142   0.06453   0.05555  -0.0298   0.1462   1.0000
  11.000   1.2367   0.06881   0.05974  -0.0301   0.1423   1.0000
  11.250   1.2204   0.07270   0.06403  -0.0262   0.1419   1.0000
  11.500   1.2002   0.07678   0.06844  -0.0224   0.1418   1.0000
  11.750   1.1781   0.08092   0.07280  -0.0189   0.1420   1.0000
  12.000   1.1563   0.08548   0.07755  -0.0162   0.1423   1.0000
  12.250   0.6011   0.14054   0.13311  -0.0395   0.3593   1.0000
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