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LOCKHEED L-188 ROOT AIRFOIL (l188root-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED L-188 ROOT AIRFOIL (l188root-il)
Reynolds number: 50,000
Max Cl/Cd: 32.4 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-l188root-il-50000.txt
Download as CSV file: xf-l188root-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED L-188 ROOT 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3666   0.11010   0.10255  -0.0257   1.0000   0.3486
  -9.250  -0.3800   0.10847   0.10103  -0.0246   1.0000   0.3618
  -9.000  -0.3846   0.10676   0.09939  -0.0229   1.0000   0.3770
  -8.750  -0.3678   0.10320   0.09584  -0.0215   1.0000   0.3926
  -8.500  -0.3565   0.09998   0.09264  -0.0201   1.0000   0.4057
  -8.250  -0.3583   0.09758   0.09031  -0.0182   1.0000   0.4180
  -8.000  -0.3714   0.09600   0.08884  -0.0154   1.0000   0.4313
  -7.750  -0.6344   0.07385   0.06700  -0.0333   1.0000   0.1894
  -7.500  -0.6804   0.06663   0.05919  -0.0327   1.0000   0.1691
  -7.250  -0.6783   0.06284   0.05532  -0.0310   1.0000   0.1675
  -7.000  -0.6781   0.05903   0.05132  -0.0294   1.0000   0.1654
  -6.750  -0.6768   0.05510   0.04709  -0.0280   1.0000   0.1629
  -6.500  -0.6727   0.05129   0.04285  -0.0267   1.0000   0.1610
  -6.250  -0.6637   0.04820   0.03937  -0.0254   1.0000   0.1622
  -6.000  -0.6515   0.04540   0.03612  -0.0242   1.0000   0.1645
  -5.750  -0.6362   0.04275   0.03299  -0.0232   1.0000   0.1666
  -5.500  -0.6186   0.04048   0.03012  -0.0223   1.0000   0.1701
  -5.250  -0.5987   0.03853   0.02825  -0.0217   1.0000   0.1764
  -5.000  -0.5776   0.03683   0.02618  -0.0210   1.0000   0.1829
  -4.750  -0.5561   0.03518   0.02435  -0.0203   1.0000   0.1911
  -4.500  -0.5339   0.03390   0.02284  -0.0197   1.0000   0.2012
  -4.250  -0.5119   0.03262   0.02157  -0.0190   1.0000   0.2134
  -4.000  -0.4892   0.03147   0.02040  -0.0183   1.0000   0.2282
  -3.750  -0.4666   0.03044   0.01942  -0.0175   1.0000   0.2477
  -3.500  -0.4437   0.02945   0.01852  -0.0168   1.0000   0.2745
  -3.250  -0.4210   0.02832   0.01772  -0.0161   1.0000   0.3149
  -3.000  -0.3988   0.02660   0.01698  -0.0155   1.0000   0.4123
  -2.750  -0.3980   0.02622   0.01835  -0.0065   1.0000   0.6988
  -2.500  -0.3986   0.02686   0.01908   0.0025   1.0000   0.7993
  -2.250  -0.3930   0.02737   0.01957   0.0101   1.0000   0.8652
  -2.000  -0.3291   0.02915   0.02101   0.0076   1.0000   0.9429
  -1.750  -0.1457   0.03171   0.02276  -0.0207   1.0000   1.0000
  -1.500  -0.1503   0.03131   0.02228  -0.0176   1.0000   1.0000
  -1.250  -0.1552   0.03089   0.02178  -0.0145   1.0000   1.0000
  -1.000  -0.1601   0.03045   0.02127  -0.0113   1.0000   1.0000
  -0.750  -0.1648   0.02999   0.02074  -0.0080   1.0000   1.0000
  -0.500  -0.1676   0.02958   0.02024  -0.0050   1.0000   1.0000
  -0.250  -0.1648   0.02933   0.01988  -0.0028   1.0000   1.0000
   0.000  -0.1544   0.02936   0.01977  -0.0018   1.0000   1.0000
   0.250  -0.1393   0.02959   0.01985  -0.0016   1.0000   1.0000
   0.500  -0.1216   0.02997   0.02008  -0.0016   1.0000   1.0000
   0.750  -0.1027   0.03045   0.02043  -0.0018   1.0000   1.0000
   1.000  -0.0832   0.03101   0.02085  -0.0021   1.0000   1.0000
   1.250  -0.0634   0.03163   0.02137  -0.0024   1.0000   1.0000
   1.500  -0.0435   0.03231   0.02195  -0.0027   1.0000   1.0000
   1.750  -0.0237   0.03304   0.02259  -0.0030   1.0000   1.0000
   2.000  -0.0039   0.03382   0.02330  -0.0034   1.0000   1.0000
   2.250   0.0157   0.03466   0.02407  -0.0037   1.0000   1.0000
   2.500   0.0351   0.03554   0.02490  -0.0040   1.0000   1.0000
   2.750   0.0542   0.03647   0.02580  -0.0044   1.0000   1.0000
   3.000   0.0730   0.03746   0.02676  -0.0047   1.0000   1.0000
   3.250   0.0915   0.03850   0.02779  -0.0051   1.0000   1.0000
   3.500   0.1096   0.03961   0.02889  -0.0054   1.0000   1.0000
   3.750   0.2315   0.04372   0.03308  -0.0240   0.9327   1.0000
   4.000   0.2902   0.04565   0.03507  -0.0303   0.9073   1.0000
   4.250   0.3185   0.04652   0.03600  -0.0314   0.8844   1.0000
   4.500   0.3615   0.04760   0.03717  -0.0345   0.8600   1.0000
   4.750   0.4056   0.04850   0.03817  -0.0373   0.8350   1.0000
   5.000   0.4446   0.04904   0.03883  -0.0390   0.8094   1.0000
   5.250   0.4884   0.04931   0.03924  -0.0408   0.7836   1.0000
   5.500   0.5376   0.04903   0.03913  -0.0426   0.7572   1.0000
   5.750   0.5751   0.04864   0.03890  -0.0426   0.7298   1.0000
   6.000   0.6433   0.04645   0.03699  -0.0446   0.7045   1.0000
   6.250   0.6801   0.04498   0.03572  -0.0431   0.6751   1.0000
   6.500   0.7401   0.04133   0.03237  -0.0421   0.6475   1.0000
   6.750   0.8208   0.03503   0.02645  -0.0413   0.6159   1.0000
   7.000   0.8791   0.02998   0.02151  -0.0383   0.5554   1.0000
   7.250   0.9091   0.02806   0.01897  -0.0339   0.4564   1.0000
   7.500   0.9257   0.02906   0.01908  -0.0306   0.3803   1.0000
   7.750   0.9488   0.03082   0.02026  -0.0294   0.3284   1.0000
   8.000   0.9773   0.03264   0.02172  -0.0293   0.2912   1.0000
   8.250   1.0070   0.03452   0.02342  -0.0295   0.2638   1.0000
   8.500   1.0357   0.03643   0.02523  -0.0296   0.2427   1.0000
   8.750   1.0625   0.03843   0.02721  -0.0295   0.2259   1.0000
   9.000   1.0865   0.04059   0.02946  -0.0290   0.2128   1.0000
   9.250   1.1116   0.04291   0.03179  -0.0288   0.2016   1.0000
   9.500   1.1294   0.04511   0.03420  -0.0276   0.1923   1.0000
   9.750   1.1462   0.04779   0.03708  -0.0264   0.1850   1.0000
  10.000   1.1554   0.05040   0.04005  -0.0242   0.1790   1.0000
  10.250   1.1802   0.05331   0.04285  -0.0243   0.1721   1.0000
  10.500   1.1738   0.05633   0.04642  -0.0205   0.1693   1.0000
  10.750   1.1670   0.05966   0.05019  -0.0171   0.1669   1.0000
  11.000   1.1579   0.06310   0.05397  -0.0138   0.1648   1.0000
  11.250   1.1465   0.06661   0.05776  -0.0106   0.1629   1.0000
  11.500   1.1276   0.07026   0.06166  -0.0070   0.1619   1.0000
  11.750   1.0877   0.07504   0.06672  -0.0031   0.1634   1.0000
  12.000   1.0369   0.08152   0.07345  -0.0012   0.1664   1.0000
  12.250   0.9910   0.08930   0.08138  -0.0018   0.1693   1.0000
  12.500   0.9571   0.09761   0.08977  -0.0039   0.1713   1.0000
  12.750   0.9364   0.10565   0.09787  -0.0064   0.1725   1.0000
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