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LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il)
Reynolds number: 200,000
Max Cl/Cd: 66.65 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c5d-il-200000.txt
Download as CSV file: xf-c5d-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-5A BL758.6 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5256   0.08754   0.08378  -0.0404   1.0000   0.0698
  -9.000  -0.5415   0.08328   0.07959  -0.0415   1.0000   0.0710
  -8.750  -0.5719   0.07838   0.07475  -0.0431   1.0000   0.0713
  -8.500  -0.6063   0.07532   0.07170  -0.0404   1.0000   0.0714
  -8.250  -0.6316   0.07167   0.06801  -0.0384   1.0000   0.0724
  -8.000  -0.6892   0.06893   0.06468  -0.0344   1.0000   0.0759
  -7.750  -0.6983   0.06256   0.05826  -0.0329   1.0000   0.0770
  -7.500  -0.6896   0.05938   0.05517  -0.0315   1.0000   0.0779
  -7.250  -0.6822   0.05700   0.05281  -0.0297   1.0000   0.0789
  -7.000  -0.6760   0.05469   0.05045  -0.0279   1.0000   0.0802
  -6.750  -0.7004   0.03747   0.03108  -0.0220   1.0000   0.0442
  -6.500  -0.6862   0.03331   0.02677  -0.0210   1.0000   0.0427
  -6.250  -0.6699   0.03043   0.02354  -0.0196   1.0000   0.0418
  -6.000  -0.6503   0.02799   0.02074  -0.0184   1.0000   0.0413
  -5.750  -0.6289   0.02604   0.01846  -0.0174   1.0000   0.0412
  -5.500  -0.6065   0.02448   0.01661  -0.0165   1.0000   0.0417
  -5.250  -0.5836   0.02322   0.01512  -0.0156   1.0000   0.0425
  -5.000  -0.5605   0.02226   0.01395  -0.0148   1.0000   0.0436
  -4.750  -0.5369   0.02077   0.01238  -0.0142   1.0000   0.0455
  -4.500  -0.5143   0.02006   0.01171  -0.0136   1.0000   0.0487
  -4.250  -0.4913   0.01956   0.01114  -0.0129   1.0000   0.0526
  -4.000  -0.4650   0.01858   0.01021  -0.0130   0.9994   0.0574
  -3.750  -0.4284   0.01818   0.00976  -0.0150   0.9966   0.0646
  -3.500  -0.3915   0.01771   0.00935  -0.0173   0.9941   0.0750
  -3.250  -0.3572   0.01713   0.00885  -0.0190   0.9905   0.0874
  -3.000  -0.3207   0.01665   0.00852  -0.0212   0.9873   0.1126
  -2.750  -0.2828   0.01587   0.00819  -0.0240   0.9851   0.1931
  -2.500  -0.2514   0.01479   0.00795  -0.0258   0.9815   0.3584
  -2.250  -0.2215   0.01377   0.00818  -0.0266   0.9785   0.6469
  -2.000  -0.1873   0.01381   0.00847  -0.0274   0.9752   0.7399
  -1.750  -0.1596   0.01387   0.00864  -0.0270   0.9698   0.7897
  -1.500  -0.1295   0.01400   0.00883  -0.0269   0.9650   0.8321
  -1.250  -0.0970   0.01420   0.00908  -0.0272   0.9616   0.8678
  -1.000  -0.0774   0.01425   0.00916  -0.0249   0.9539   0.8978
  -0.750  -0.0447   0.01441   0.00932  -0.0252   0.9500   0.9229
  -0.500  -0.0132   0.01455   0.00944  -0.0255   0.9447   0.9466
  -0.250   0.0305   0.01473   0.00958  -0.0286   0.9406   0.9650
   0.000   0.0861   0.01495   0.00976  -0.0343   0.9389   0.9793
   0.250   0.1454   0.01512   0.00989  -0.0410   0.9377   0.9876
   0.500   0.2081   0.01513   0.00988  -0.0482   0.9360   0.9939
   0.750   0.2699   0.01495   0.00969  -0.0551   0.9339   0.9963
   1.000   0.3078   0.01478   0.00953  -0.0576   0.9249   1.0000
   1.250   0.3635   0.01436   0.00913  -0.0630   0.9208   1.0000
   1.500   0.4171   0.01359   0.00839  -0.0675   0.9105   1.0000
   1.750   0.4752   0.01266   0.00749  -0.0726   0.9038   1.0000
   2.000   0.5033   0.01210   0.00695  -0.0722   0.8902   1.0000
   2.250   0.5324   0.01149   0.00637  -0.0718   0.8750   1.0000
   2.500   0.5599   0.01098   0.00587  -0.0711   0.8584   1.0000
   2.750   0.5798   0.01069   0.00559  -0.0692   0.8378   1.0000
   3.000   0.6037   0.01040   0.00530  -0.0679   0.8142   1.0000
   3.250   0.6256   0.01021   0.00509  -0.0664   0.7863   1.0000
   3.500   0.6500   0.01007   0.00486  -0.0652   0.7502   1.0000
   3.750   0.6725   0.01009   0.00468  -0.0636   0.6971   1.0000
   4.000   0.6902   0.01037   0.00465  -0.0612   0.6291   1.0000
   4.250   0.7003   0.01091   0.00474  -0.0574   0.5395   1.0000
   4.500   0.7027   0.01179   0.00499  -0.0523   0.4207   1.0000
   4.750   0.7043   0.01293   0.00544  -0.0475   0.2969   1.0000
   5.000   0.7112   0.01409   0.00598  -0.0439   0.1951   1.0000
   5.250   0.7236   0.01508   0.00663  -0.0412   0.1424   1.0000
   5.500   0.7391   0.01592   0.00728  -0.0390   0.1182   1.0000
   5.750   0.7566   0.01668   0.00795  -0.0371   0.1065   1.0000
   6.250   0.7953   0.01810   0.00932  -0.0341   0.0940   1.0000
   6.500   0.8164   0.01878   0.01000  -0.0330   0.0899   1.0000
   6.750   0.8375   0.01978   0.01090  -0.0319   0.0860   1.0000
   7.000   0.8609   0.02060   0.01177  -0.0312   0.0830   1.0000
   7.250   0.8849   0.02136   0.01261  -0.0305   0.0802   1.0000
   7.500   0.9088   0.02215   0.01343  -0.0299   0.0772   1.0000
   7.750   0.9332   0.02314   0.01438  -0.0296   0.0741   1.0000
   8.000   0.9598   0.02460   0.01592  -0.0296   0.0713   1.0000
   8.250   0.9827   0.02535   0.01684  -0.0287   0.0686   1.0000
   8.500   1.0056   0.02622   0.01780  -0.0280   0.0657   1.0000
   8.750   1.0285   0.02719   0.01875  -0.0275   0.0629   1.0000
   9.000   1.0525   0.02908   0.02079  -0.0272   0.0603   1.0000
   9.250   1.0724   0.03023   0.02220  -0.0259   0.0578   1.0000
   9.500   1.0918   0.03126   0.02335  -0.0247   0.0550   1.0000
   9.750   1.1122   0.03252   0.02458  -0.0240   0.0524   1.0000
  10.000   1.1273   0.03509   0.02748  -0.0224   0.0502   1.0000
  10.250   1.1391   0.03667   0.02943  -0.0199   0.0479   1.0000
  10.500   1.1528   0.03811   0.03105  -0.0181   0.0457   1.0000
  10.750   1.1668   0.03961   0.03263  -0.0165   0.0440   1.0000
  11.000   1.1778   0.04285   0.03598  -0.0151   0.0425   1.0000
  11.250   1.1721   0.04603   0.03962  -0.0110   0.0415   1.0000
  11.500   1.1643   0.04848   0.04249  -0.0066   0.0406   1.0000
  11.750   1.1507   0.05123   0.04559  -0.0018   0.0398   1.0000
  12.000   1.1341   0.05429   0.04896   0.0026   0.0391   1.0000
  12.250   1.1144   0.05775   0.05270   0.0064   0.0387   1.0000
  12.500   1.0907   0.06184   0.05707   0.0093   0.0385   1.0000
  12.750   1.0619   0.06684   0.06234   0.0110   0.0386   1.0000
  13.000   1.0288   0.07296   0.06871   0.0109   0.0389   1.0000
  13.250   0.9930   0.08053   0.07649   0.0085   0.0396   1.0000
  13.500   0.9579   0.08945   0.08558   0.0037   0.0404   1.0000
  13.750   0.9261   0.09952   0.09575  -0.0025   0.0413   1.0000
  14.000   0.9017   0.10941   0.10567  -0.0079   0.0419   1.0000
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