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LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il)
Reynolds number: 50,000
Max Cl/Cd: 29.4 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-c5b-il-50000-n5.txt
Download as CSV file: xf-c5b-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5609   0.09654   0.08871  -0.0463   1.0000   0.0576
 -10.250  -0.5746   0.09012   0.08234  -0.0494   1.0000   0.0571
 -10.000  -0.5951   0.08396   0.07621  -0.0521   1.0000   0.0564
  -9.750  -0.6211   0.07873   0.07100  -0.0532   1.0000   0.0556
  -9.500  -0.6506   0.07475   0.06700  -0.0518   1.0000   0.0550
  -9.250  -0.6776   0.07121   0.06341  -0.0489   1.0000   0.0546
  -9.000  -0.6978   0.06763   0.05970  -0.0462   1.0000   0.0544
  -8.750  -0.7131   0.06419   0.05607  -0.0434   1.0000   0.0545
  -8.500  -0.7237   0.06083   0.05249  -0.0405   1.0000   0.0547
  -8.250  -0.7300   0.05755   0.04893  -0.0378   1.0000   0.0551
  -8.000  -0.7324   0.05434   0.04541  -0.0352   1.0000   0.0556
  -7.750  -0.7310   0.05122   0.04192  -0.0327   1.0000   0.0562
  -7.500  -0.7259   0.04821   0.03851  -0.0303   1.0000   0.0566
  -7.250  -0.7173   0.04535   0.03524  -0.0282   1.0000   0.0571
  -7.000  -0.7055   0.04269   0.03213  -0.0262   1.0000   0.0578
  -6.750  -0.6910   0.04031   0.02928  -0.0244   1.0000   0.0591
  -6.500  -0.6745   0.03829   0.02704  -0.0230   1.0000   0.0611
  -6.250  -0.6567   0.03674   0.02539  -0.0218   1.0000   0.0637
  -6.000  -0.6373   0.03514   0.02358  -0.0205   1.0000   0.0663
  -5.750  -0.6159   0.03354   0.02169  -0.0193   1.0000   0.0687
  -5.500  -0.5942   0.03214   0.02008  -0.0181   1.0000   0.0723
  -5.250  -0.5741   0.03103   0.01901  -0.0170   1.0000   0.0772
  -5.000  -0.5522   0.02996   0.01777  -0.0158   1.0000   0.0826
  -4.750  -0.5314   0.02892   0.01671  -0.0145   1.0000   0.0884
  -4.500  -0.5106   0.02806   0.01576  -0.0133   1.0000   0.0983
  -4.250  -0.4901   0.02716   0.01480  -0.0122   1.0000   0.1110
  -4.000  -0.4700   0.02609   0.01388  -0.0112   1.0000   0.1321
  -3.750  -0.4495   0.02483   0.01289  -0.0105   1.0000   0.1764
  -3.500  -0.4313   0.02335   0.01209  -0.0098   1.0000   0.2765
  -3.250  -0.4169   0.02188   0.01184  -0.0077   1.0000   0.4733
  -3.000  -0.4056   0.02158   0.01239  -0.0027   1.0000   0.6601
  -2.750  -0.3933   0.02178   0.01275   0.0022   1.0000   0.7577
  -2.500  -0.3761   0.02196   0.01288   0.0056   1.0000   0.8093
  -2.250  -0.3549   0.02210   0.01287   0.0077   1.0000   0.8457
  -2.000  -0.3287   0.02232   0.01293   0.0089   1.0000   0.8842
  -1.750  -0.2828   0.02284   0.01326   0.0065   1.0000   0.9315
  -1.500  -0.2077   0.02350   0.01358  -0.0024   1.0000   0.9683
  -1.250  -0.1483   0.02372   0.01356  -0.0094   1.0000   0.9884
  -1.000  -0.1151   0.02366   0.01336  -0.0119   1.0000   1.0000
  -0.750  -0.1139   0.02337   0.01299  -0.0085   1.0000   1.0000
  -0.500  -0.1113   0.02313   0.01267  -0.0052   1.0000   1.0000
  -0.250  -0.1065   0.02297   0.01243  -0.0023   1.0000   1.0000
   0.000  -0.0873   0.02303   0.01239  -0.0020   0.9971   1.0000
   0.250  -0.0538   0.02332   0.01256  -0.0043   0.9901   1.0000
   0.500  -0.0199   0.02366   0.01279  -0.0067   0.9833   1.0000
   0.750   0.0136   0.02399   0.01305  -0.0088   0.9759   1.0000
   1.000   0.0457   0.02430   0.01330  -0.0107   0.9677   1.0000
   1.250   0.0803   0.02467   0.01363  -0.0129   0.9603   1.0000
   1.500   0.1136   0.02501   0.01395  -0.0148   0.9516   1.0000
   1.750   0.1452   0.02531   0.01426  -0.0163   0.9421   1.0000
   2.000   0.1843   0.02571   0.01467  -0.0192   0.9346   1.0000
   2.250   0.2133   0.02596   0.01496  -0.0201   0.9232   1.0000
   2.500   0.2451   0.02623   0.01530  -0.0214   0.9126   1.0000
   2.750   0.2845   0.02651   0.01566  -0.0241   0.9037   1.0000
   3.000   0.3153   0.02670   0.01596  -0.0250   0.8911   1.0000
   3.250   0.3479   0.02680   0.01617  -0.0261   0.8773   1.0000
   3.500   0.3841   0.02673   0.01624  -0.0275   0.8618   1.0000
   3.750   0.4249   0.02639   0.01609  -0.0292   0.8446   1.0000
   4.000   0.4575   0.02581   0.01567  -0.0290   0.8194   1.0000
   4.250   0.4959   0.02476   0.01482  -0.0289   0.7900   1.0000
   4.500   0.5277   0.02392   0.01415  -0.0278   0.7597   1.0000
   4.750   0.5565   0.02340   0.01381  -0.0267   0.7290   1.0000
   5.000   0.5894   0.02277   0.01336  -0.0260   0.6878   1.0000
   5.250   0.6332   0.02188   0.01230  -0.0260   0.5906   1.0000
   5.500   0.6601   0.02245   0.01178  -0.0240   0.4087   1.0000
   5.750   0.6671   0.02386   0.01240  -0.0205   0.3006   1.0000
   6.000   0.6780   0.02520   0.01331  -0.0180   0.2370   1.0000
   6.250   0.6922   0.02647   0.01426  -0.0162   0.1958   1.0000
   6.500   0.7090   0.02771   0.01531  -0.0147   0.1699   1.0000
   6.750   0.7293   0.02890   0.01645  -0.0136   0.1516   1.0000
   7.000   0.7525   0.03008   0.01763  -0.0130   0.1374   1.0000
   7.250   0.7789   0.03127   0.01883  -0.0129   0.1256   1.0000
   7.500   0.8083   0.03258   0.02011  -0.0133   0.1173   1.0000
   7.750   0.8411   0.03402   0.02176  -0.0140   0.1100   1.0000
   8.000   0.8685   0.03543   0.02318  -0.0141   0.1033   1.0000
   8.250   0.8981   0.03718   0.02515  -0.0145   0.0981   1.0000
   8.500   0.9233   0.03892   0.02714  -0.0142   0.0931   1.0000
   8.750   0.9461   0.04058   0.02882  -0.0138   0.0886   1.0000
   9.000   0.9660   0.04275   0.03140  -0.0128   0.0849   1.0000
   9.250   0.9825   0.04486   0.03387  -0.0114   0.0810   1.0000
   9.500   0.9984   0.04672   0.03589  -0.0101   0.0775   1.0000
   9.750   1.0146   0.04902   0.03830  -0.0090   0.0749   1.0000
  10.000   1.0182   0.05197   0.04184  -0.0061   0.0727   1.0000
  10.250   1.0196   0.05484   0.04516  -0.0032   0.0703   1.0000
  10.500   1.0204   0.05758   0.04822  -0.0006   0.0683   1.0000
  10.750   1.0198   0.06042   0.05132   0.0020   0.0669   1.0000
  11.000   1.0165   0.06339   0.05453   0.0047   0.0659   1.0000
  11.250   1.0094   0.06633   0.05766   0.0075   0.0651   1.0000
  11.500   1.0036   0.06931   0.06078   0.0099   0.0642   1.0000
  11.750   0.9881   0.07291   0.06456   0.0124   0.0637   1.0000
  12.000   0.9635   0.07720   0.06909   0.0143   0.0636   1.0000
  12.250   0.9377   0.08210   0.07421   0.0149   0.0636   1.0000
  12.500   0.9114   0.08777   0.08004   0.0140   0.0637   1.0000
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