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LOCKHEED C-5A BL576 AIRFOIL (c5c-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-5A BL576 AIRFOIL (c5c-il)
Reynolds number: 100,000
Max Cl/Cd: 48.17 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c5c-il-100000.txt
Download as CSV file: xf-c5c-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-5A BL576 AIRFOIL                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5218   0.09849   0.09331  -0.0346   1.0000   0.1417
  -9.000  -0.5162   0.09583   0.09067  -0.0328   1.0000   0.1449
  -8.750  -0.5286   0.09277   0.08768  -0.0326   1.0000   0.1493
  -8.500  -0.5916   0.08929   0.08438  -0.0344   1.0000   0.1525
  -8.250  -0.6480   0.08554   0.08064  -0.0338   1.0000   0.1541
  -8.000  -0.6017   0.08247   0.07765  -0.0303   1.0000   0.1572
  -7.750  -0.6049   0.07975   0.07495  -0.0283   1.0000   0.1607
  -7.500  -0.6710   0.07606   0.07105  -0.0286   1.0000   0.1690
  -7.250  -0.6483   0.07222   0.06737  -0.0263   1.0000   0.1713
  -7.000  -0.6426   0.06947   0.06463  -0.0242   1.0000   0.1749
  -6.750  -0.6947   0.04777   0.04091  -0.0262   1.0000   0.0840
  -6.500  -0.6810   0.04424   0.03718  -0.0246   1.0000   0.0795
  -6.250  -0.6694   0.04018   0.03270  -0.0229   1.0000   0.0759
  -6.000  -0.6557   0.03564   0.02721  -0.0207   1.0000   0.0720
  -5.750  -0.6365   0.03352   0.02486  -0.0196   1.0000   0.0732
  -5.500  -0.6161   0.03179   0.02293  -0.0186   1.0000   0.0754
  -5.250  -0.5939   0.02995   0.02077  -0.0176   1.0000   0.0773
  -5.000  -0.5702   0.02819   0.01865  -0.0167   1.0000   0.0790
  -4.750  -0.5465   0.02707   0.01712  -0.0157   1.0000   0.0825
  -4.500  -0.5225   0.02540   0.01553  -0.0153   1.0000   0.0870
  -4.250  -0.4983   0.02434   0.01437  -0.0145   1.0000   0.0917
  -4.000  -0.4743   0.02332   0.01331  -0.0139   1.0000   0.0986
  -3.750  -0.4505   0.02250   0.01248  -0.0131   1.0000   0.1067
  -3.500  -0.4269   0.02155   0.01164  -0.0125   1.0000   0.1177
  -3.250  -0.4032   0.02068   0.01086  -0.0118   1.0000   0.1390
  -3.000  -0.3789   0.01906   0.00992  -0.0116   1.0000   0.2166
  -2.750  -0.3570   0.01683   0.00970  -0.0110   1.0000   0.5622
  -2.500  -0.3423   0.01665   0.01013  -0.0070   1.0000   0.7389
  -2.250  -0.3284   0.01678   0.01041  -0.0028   1.0000   0.8201
  -2.000  -0.3151   0.01706   0.01078   0.0021   1.0000   0.8928
  -1.750  -0.2533   0.01803   0.01158  -0.0025   1.0000   0.9726
  -1.500  -0.1693   0.01873   0.01195  -0.0138   1.0000   0.9964
  -1.250  -0.1574   0.01848   0.01160  -0.0125   1.0000   1.0000
  -1.000  -0.1570   0.01816   0.01120  -0.0089   1.0000   1.0000
  -0.750  -0.1504   0.01800   0.01093  -0.0063   1.0000   1.0000
  -0.500  -0.1370   0.01802   0.01083  -0.0048   1.0000   1.0000
  -0.250  -0.1198   0.01816   0.01086  -0.0038   1.0000   1.0000
   0.000  -0.1010   0.01839   0.01098  -0.0032   1.0000   1.0000
   0.250  -0.0813   0.01867   0.01118  -0.0027   1.0000   1.0000
   0.500  -0.0611   0.01901   0.01143  -0.0023   1.0000   1.0000
   0.750  -0.0407   0.01940   0.01175  -0.0020   1.0000   1.0000
   1.000  -0.0034   0.02006   0.01235  -0.0050   0.9952   1.0000
   1.250   0.0419   0.02079   0.01304  -0.0094   0.9866   1.0000
   1.500   0.0859   0.02145   0.01367  -0.0135   0.9767   1.0000
   1.750   0.1288   0.02203   0.01424  -0.0172   0.9657   1.0000
   2.000   0.1703   0.02253   0.01475  -0.0206   0.9544   1.0000
   2.250   0.2150   0.02305   0.01530  -0.0244   0.9447   1.0000
   2.500   0.2569   0.02340   0.01569  -0.0276   0.9333   1.0000
   2.750   0.3050   0.02345   0.01581  -0.0314   0.9184   1.0000
   3.000   0.3640   0.02305   0.01553  -0.0366   0.9022   1.0000
   3.250   0.4043   0.02260   0.01517  -0.0382   0.8841   1.0000
   3.500   0.4505   0.02202   0.01472  -0.0407   0.8687   1.0000
   3.750   0.4975   0.02111   0.01397  -0.0429   0.8518   1.0000
   4.000   0.5459   0.01991   0.01296  -0.0449   0.8343   1.0000
   4.250   0.6020   0.01803   0.01128  -0.0473   0.8139   1.0000
   4.500   0.6405   0.01663   0.01002  -0.0468   0.7819   1.0000
   4.750   0.6717   0.01575   0.00921  -0.0455   0.7340   1.0000
   5.000   0.7240   0.01503   0.00803  -0.0474   0.5922   1.0000
   5.250   0.7269   0.01667   0.00821  -0.0418   0.3558   1.0000
   5.500   0.7283   0.01856   0.00909  -0.0372   0.2306   1.0000
   5.750   0.7398   0.01999   0.01006  -0.0344   0.1854   1.0000
   6.000   0.7565   0.02134   0.01112  -0.0324   0.1619   1.0000
   6.250   0.7787   0.02254   0.01215  -0.0314   0.1466   1.0000
   6.500   0.8029   0.02356   0.01315  -0.0308   0.1351   1.0000
   6.750   0.8315   0.02491   0.01450  -0.0308   0.1274   1.0000
   7.000   0.8599   0.02622   0.01575  -0.0310   0.1205   1.0000
   7.250   0.8884   0.02775   0.01739  -0.0311   0.1144   1.0000
   7.500   0.9155   0.02920   0.01896  -0.0310   0.1093   1.0000
   7.750   0.9447   0.03144   0.02114  -0.0316   0.1040   1.0000
   8.000   0.9656   0.03288   0.02299  -0.0300   0.1004   1.0000
   8.250   0.9872   0.03458   0.02494  -0.0290   0.0961   1.0000
   8.500   1.0103   0.03666   0.02703  -0.0286   0.0920   1.0000
   8.750   1.0279   0.03972   0.03042  -0.0272   0.0899   1.0000
   9.000   1.0393   0.04188   0.03312  -0.0243   0.0879   1.0000
   9.250   1.0487   0.04441   0.03611  -0.0214   0.0855   1.0000
   9.500   1.0559   0.04739   0.03951  -0.0186   0.0842   1.0000
   9.750   1.0586   0.05101   0.04358  -0.0153   0.0841   1.0000
  10.000   1.0559   0.05508   0.04808  -0.0117   0.0848   1.0000
  10.250   1.0483   0.05936   0.05274  -0.0080   0.0859   1.0000
  10.500   1.0370   0.06364   0.05735  -0.0044   0.0869   1.0000
  10.750   1.0237   0.06792   0.06188  -0.0011   0.0878   1.0000
  11.000   1.0093   0.07211   0.06625   0.0020   0.0887   1.0000
  11.250   1.0028   0.07693   0.07116   0.0038   0.0897   1.0000
  11.500   0.6432   0.11230   0.10735  -0.0047   0.1913   1.0000
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