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LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il)
Reynolds number: 200,000
Max Cl/Cd: 64.91 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c5b-il-200000.txt
Download as CSV file: xf-c5b-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-5A BL488.2 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  -0.4460   0.09132   0.08781  -0.0379   1.0000   0.0774
  -9.750  -0.5882   0.08380   0.08015  -0.0479   1.0000   0.0741
  -9.500  -0.6084   0.07942   0.07578  -0.0486   1.0000   0.0746
  -9.250  -0.6472   0.07549   0.07186  -0.0471   1.0000   0.0745
  -9.000  -0.6775   0.07298   0.06933  -0.0430   1.0000   0.0747
  -8.750  -0.6912   0.07037   0.06670  -0.0401   1.0000   0.0755
  -8.500  -0.7037   0.06766   0.06394  -0.0373   1.0000   0.0766
  -8.250  -0.7155   0.06478   0.06098  -0.0346   1.0000   0.0782
  -8.000  -0.7290   0.06163   0.05764  -0.0317   1.0000   0.0809
  -7.250  -0.7658   0.03918   0.03309  -0.0201   1.0000   0.0484
  -7.000  -0.7547   0.03565   0.02929  -0.0183   1.0000   0.0468
  -6.750  -0.7406   0.03280   0.02608  -0.0164   1.0000   0.0460
  -6.500  -0.7234   0.03016   0.02303  -0.0149   1.0000   0.0450
  -6.250  -0.7032   0.02766   0.02009  -0.0135   1.0000   0.0438
  -6.000  -0.6815   0.02584   0.01794  -0.0124   1.0000   0.0434
  -5.750  -0.6591   0.02444   0.01635  -0.0115   1.0000   0.0436
  -5.500  -0.6366   0.02326   0.01503  -0.0106   1.0000   0.0442
  -5.250  -0.6139   0.02224   0.01391  -0.0098   1.0000   0.0452
  -5.000  -0.5912   0.02134   0.01293  -0.0089   1.0000   0.0466
  -4.750  -0.5685   0.02057   0.01207  -0.0080   1.0000   0.0484
  -4.500  -0.5459   0.01958   0.01105  -0.0073   1.0000   0.0507
  -4.250  -0.5237   0.01886   0.01039  -0.0067   1.0000   0.0548
  -4.000  -0.5010   0.01844   0.00993  -0.0060   1.0000   0.0595
  -3.750  -0.4749   0.01771   0.00927  -0.0062   0.9994   0.0669
  -3.500  -0.4389   0.01718   0.00878  -0.0083   0.9967   0.0796
  -3.250  -0.4027   0.01645   0.00838  -0.0105   0.9945   0.1309
  -3.000  -0.3705   0.01498   0.00801  -0.0128   0.9924   0.3399
  -2.750  -0.3396   0.01400   0.00812  -0.0141   0.9900   0.5747
  -2.500  -0.3064   0.01398   0.00847  -0.0151   0.9869   0.6807
  -2.250  -0.2730   0.01416   0.00875  -0.0160   0.9834   0.7385
  -2.000  -0.2445   0.01430   0.00898  -0.0158   0.9785   0.7822
  -1.750  -0.2125   0.01457   0.00933  -0.0161   0.9750   0.8216
  -1.500  -0.1876   0.01471   0.00948  -0.0151   0.9693   0.8488
  -1.250  -0.1559   0.01488   0.00963  -0.0157   0.9649   0.8671
  -1.000  -0.1252   0.01506   0.00980  -0.0160   0.9606   0.8847
  -0.750  -0.1003   0.01513   0.00987  -0.0151   0.9542   0.9022
  -0.500  -0.0661   0.01530   0.01002  -0.0161   0.9505   0.9196
  -0.250  -0.0397   0.01544   0.01016  -0.0153   0.9442   0.9419
   0.000   0.0010   0.01564   0.01034  -0.0177   0.9400   0.9608
   0.250   0.0524   0.01583   0.01050  -0.0226   0.9375   0.9710
   0.500   0.1084   0.01599   0.01064  -0.0286   0.9357   0.9772
   0.750   0.1570   0.01609   0.01073  -0.0331   0.9311   0.9843
   1.000   0.2073   0.01608   0.01073  -0.0381   0.9262   0.9880
   1.250   0.2657   0.01578   0.01045  -0.0442   0.9218   0.9893
   1.500   0.3194   0.01526   0.00995  -0.0490   0.9124   0.9910
   1.750   0.3802   0.01459   0.00932  -0.0551   0.9071   0.9905
   2.000   0.4330   0.01389   0.00868  -0.0595   0.8982   0.9920
   2.250   0.4895   0.01288   0.00771  -0.0642   0.8897   0.9920
   2.500   0.5340   0.01223   0.00713  -0.0670   0.8755   0.9955
   2.750   0.5784   0.01166   0.00663  -0.0699   0.8597   0.9992
   3.000   0.6009   0.01127   0.00627  -0.0686   0.8360   1.0000
   3.250   0.6275   0.01087   0.00587  -0.0679   0.8088   1.0000
   3.500   0.6543   0.01058   0.00551  -0.0672   0.7701   1.0000
   3.750   0.6803   0.01048   0.00519  -0.0663   0.7066   1.0000
   4.000   0.6962   0.01078   0.00506  -0.0635   0.6167   1.0000
   4.250   0.7003   0.01140   0.00515  -0.0588   0.5124   1.0000
   4.500   0.6972   0.01224   0.00539  -0.0529   0.4001   1.0000
   4.750   0.6954   0.01319   0.00575  -0.0474   0.2939   1.0000
   5.000   0.6995   0.01411   0.00617  -0.0432   0.2084   1.0000
   5.250   0.7082   0.01499   0.00669  -0.0397   0.1600   1.0000
   5.500   0.7203   0.01582   0.00730  -0.0369   0.1293   1.0000
   5.750   0.7353   0.01659   0.00796  -0.0346   0.1133   1.0000
   6.000   0.7528   0.01726   0.00857  -0.0327   0.1038   1.0000
   6.250   0.7718   0.01797   0.00928  -0.0312   0.0978   1.0000
   6.500   0.7924   0.01858   0.00990  -0.0299   0.0926   1.0000
   6.750   0.8126   0.01960   0.01081  -0.0287   0.0877   1.0000
   7.000   0.8352   0.02008   0.01140  -0.0278   0.0837   1.0000
   7.250   0.8570   0.02065   0.01197  -0.0268   0.0792   1.0000
   7.500   0.8806   0.02184   0.01309  -0.0264   0.0750   1.0000
   7.750   0.9036   0.02246   0.01385  -0.0256   0.0719   1.0000
   8.000   0.9271   0.02328   0.01473  -0.0249   0.0687   1.0000
   8.250   0.9508   0.02425   0.01569  -0.0245   0.0656   1.0000
   8.500   0.9772   0.02587   0.01741  -0.0245   0.0625   1.0000
   8.750   0.9995   0.02686   0.01858  -0.0236   0.0596   1.0000
   9.000   1.0221   0.02803   0.01985  -0.0229   0.0571   1.0000
   9.250   1.0456   0.02950   0.02137  -0.0225   0.0549   1.0000
   9.500   1.0697   0.03274   0.02483  -0.0225   0.0530   1.0000
   9.750   1.0855   0.03438   0.02682  -0.0205   0.0520   1.0000
  10.000   1.0989   0.03610   0.02889  -0.0182   0.0502   1.0000
  10.250   1.1125   0.03746   0.03045  -0.0163   0.0479   1.0000
  10.500   1.1288   0.03843   0.03144  -0.0150   0.0458   1.0000
  10.750   1.1417   0.04147   0.03455  -0.0139   0.0440   1.0000
  11.000   1.1394   0.04398   0.03750  -0.0099   0.0428   1.0000
  11.250   1.1363   0.04604   0.03997  -0.0058   0.0416   1.0000
  11.500   1.1284   0.04873   0.04301  -0.0015   0.0407   1.0000
  11.750   1.1154   0.05157   0.04616   0.0032   0.0400   1.0000
  12.000   1.0997   0.05462   0.04949   0.0074   0.0394   1.0000
  12.250   1.0816   0.05791   0.05304   0.0110   0.0389   1.0000
  12.500   1.0591   0.06183   0.05720   0.0139   0.0387   1.0000
  12.750   1.0261   0.06727   0.06293   0.0157   0.0390   1.0000
  13.000   0.9841   0.07469   0.07063   0.0152   0.0399   1.0000
  13.250   0.9446   0.08319   0.07934   0.0117   0.0408   1.0000
  13.500   0.9078   0.09317   0.08947   0.0057   0.0419   1.0000
  13.750   0.8759   0.10431   0.10066  -0.0014   0.0428   1.0000
  14.000   0.8585   0.11297   0.10931  -0.0051   0.0435   1.0000
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