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LOCKHEED C-5A BL0 AIRFOIL (c5a-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: LOCKHEED C-5A BL0 AIRFOIL (c5a-il)
Reynolds number: 100,000
Max Cl/Cd: 32.48 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-c5a-il-100000-n5.txt
Download as CSV file: xf-c5a-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-5A BL0 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.6849   0.09019   0.08434  -0.0526   1.0000   0.0292
 -12.500  -0.7118   0.08276   0.07680  -0.0565   1.0000   0.0290
 -12.250  -0.7377   0.07666   0.07057  -0.0588   1.0000   0.0288
 -12.000  -0.7621   0.07160   0.06537  -0.0597   1.0000   0.0287
 -11.750  -0.7853   0.06735   0.06095  -0.0594   1.0000   0.0286
 -11.500  -0.8071   0.06373   0.05716  -0.0579   1.0000   0.0285
 -11.250  -0.8279   0.06066   0.05392  -0.0554   1.0000   0.0284
 -11.000  -0.8481   0.05808   0.05117  -0.0517   1.0000   0.0284
 -10.750  -0.8682   0.05595   0.04887  -0.0469   1.0000   0.0285
 -10.500  -0.8842   0.05376   0.04647  -0.0422   1.0000   0.0286
 -10.250  -0.8952   0.05143   0.04388  -0.0379   1.0000   0.0289
 -10.000  -0.9025   0.04917   0.04131  -0.0339   1.0000   0.0293
  -9.750  -0.9060   0.04697   0.03878  -0.0301   1.0000   0.0296
  -9.500  -0.9056   0.04489   0.03634  -0.0266   1.0000   0.0300
  -9.250  -0.9014   0.04289   0.03400  -0.0236   1.0000   0.0302
  -9.000  -0.8918   0.04066   0.03156  -0.0213   1.0000   0.0305
  -8.750  -0.8792   0.03861   0.02934  -0.0194   1.0000   0.0308
  -8.500  -0.8651   0.03681   0.02736  -0.0176   1.0000   0.0312
  -8.250  -0.8498   0.03520   0.02562  -0.0160   1.0000   0.0316
  -8.000  -0.8336   0.03373   0.02403  -0.0143   1.0000   0.0322
  -7.750  -0.8167   0.03238   0.02256  -0.0128   1.0000   0.0328
  -7.500  -0.7994   0.03112   0.02120  -0.0112   1.0000   0.0335
  -7.250  -0.7821   0.02997   0.01993  -0.0096   1.0000   0.0345
  -7.000  -0.7651   0.02897   0.01882  -0.0080   1.0000   0.0359
  -6.750  -0.7478   0.02810   0.01781  -0.0063   1.0000   0.0374
  -6.500  -0.7328   0.02691   0.01668  -0.0045   1.0000   0.0389
  -6.250  -0.7176   0.02596   0.01572  -0.0027   1.0000   0.0405
  -6.000  -0.7020   0.02509   0.01480  -0.0009   1.0000   0.0421
  -5.750  -0.6857   0.02429   0.01392   0.0008   1.0000   0.0441
  -5.500  -0.6690   0.02352   0.01308   0.0024   1.0000   0.0470
  -5.250  -0.6518   0.02275   0.01228   0.0038   1.0000   0.0515
  -5.000  -0.6333   0.02208   0.01156   0.0051   1.0000   0.0570
  -4.500  -0.5961   0.02036   0.01020   0.0073   1.0000   0.1040
  -4.250  -0.5784   0.01900   0.00947   0.0080   1.0000   0.2095
  -4.000  -0.5584   0.01736   0.00899   0.0080   0.9989   0.4174
  -3.750  -0.5308   0.01696   0.00928   0.0080   0.9959   0.5637
  -3.500  -0.5013   0.01716   0.00971   0.0081   0.9921   0.6408
  -3.250  -0.4707   0.01749   0.01005   0.0080   0.9878   0.6825
  -3.000  -0.4378   0.01771   0.01019   0.0071   0.9840   0.7037
  -2.750  -0.4069   0.01783   0.01021   0.0065   0.9792   0.7179
  -2.500  -0.3735   0.01803   0.01034   0.0054   0.9755   0.7331
  -2.250  -0.3453   0.01819   0.01045   0.0055   0.9704   0.7483
  -2.000  -0.3134   0.01834   0.01052   0.0047   0.9658   0.7614
  -1.750  -0.2806   0.01839   0.01049   0.0035   0.9607   0.7729
  -1.500  -0.2504   0.01847   0.01053   0.0031   0.9545   0.7809
  -1.250  -0.2138   0.01850   0.01049   0.0010   0.9503   0.7902
  -1.000  -0.1880   0.01850   0.01047   0.0014   0.9430   0.7973
  -0.750  -0.1541   0.01848   0.01040  -0.0001   0.9382   0.8057
  -0.500  -0.1245   0.01852   0.01042  -0.0005   0.9327   0.8121
  -0.250  -0.0957   0.01848   0.01036  -0.0010   0.9263   0.8207
   0.000  -0.0614   0.01850   0.01039  -0.0023   0.9220   0.8266
   0.250  -0.0357   0.01848   0.01037  -0.0021   0.9142   0.8347
   0.500  -0.0033   0.01845   0.01036  -0.0031   0.9087   0.8412
   0.750   0.0274   0.01844   0.01038  -0.0038   0.9030   0.8483
   1.000   0.0552   0.01841   0.01038  -0.0039   0.8954   0.8558
   1.250   0.0917   0.01833   0.01034  -0.0056   0.8910   0.8620
   1.500   0.1165   0.01826   0.01032  -0.0051   0.8807   0.8703
   1.750   0.1528   0.01805   0.01018  -0.0064   0.8736   0.8760
   2.000   0.1838   0.01780   0.00999  -0.0068   0.8629   0.8840
   2.250   0.2137   0.01759   0.00987  -0.0069   0.8520   0.8904
   2.500   0.2491   0.01724   0.00960  -0.0078   0.8413   0.8974
   2.750   0.2837   0.01681   0.00925  -0.0084   0.8252   0.9038
   3.000   0.3177   0.01642   0.00894  -0.0089   0.8055   0.9102
   3.250   0.3525   0.01608   0.00867  -0.0097   0.7856   0.9174
   3.500   0.3887   0.01581   0.00847  -0.0107   0.7591   0.9230
   3.750   0.4289   0.01548   0.00810  -0.0123   0.7185   0.9287
   4.000   0.4688   0.01534   0.00774  -0.0138   0.6457   0.9336
   4.250   0.5037   0.01561   0.00765  -0.0147   0.5554   0.9386
   4.500   0.5259   0.01619   0.00774  -0.0135   0.4442   0.9475
   4.750   0.5471   0.01725   0.00808  -0.0128   0.3123   0.9549
   5.000   0.5702   0.01822   0.00859  -0.0126   0.2216   0.9634
   5.250   0.5977   0.01907   0.00914  -0.0134   0.1702   0.9711
   5.500   0.6271   0.01985   0.00976  -0.0144   0.1379   0.9782
   5.750   0.6570   0.02062   0.01048  -0.0155   0.1160   0.9859
   6.000   0.6880   0.02135   0.01119  -0.0168   0.1005   0.9933
   6.250   0.7147   0.02204   0.01188  -0.0173   0.0921   1.0000
   6.500   0.7213   0.02245   0.01230  -0.0137   0.0880   1.0000
   6.750   0.7295   0.02296   0.01280  -0.0104   0.0846   1.0000
   7.000   0.7424   0.02361   0.01345  -0.0081   0.0812   1.0000
   7.250   0.7595   0.02427   0.01418  -0.0064   0.0772   1.0000
   7.500   0.7778   0.02501   0.01493  -0.0051   0.0738   1.0000
   7.750   0.7971   0.02594   0.01585  -0.0040   0.0713   1.0000
   8.000   0.8190   0.02695   0.01693  -0.0033   0.0687   1.0000
   8.250   0.8412   0.02788   0.01799  -0.0027   0.0655   1.0000
   8.500   0.8630   0.02888   0.01906  -0.0020   0.0628   1.0000
   8.750   0.8845   0.02997   0.02017  -0.0015   0.0604   1.0000
   9.000   0.9069   0.03132   0.02163  -0.0010   0.0580   1.0000
   9.250   0.9282   0.03265   0.02321  -0.0003   0.0554   1.0000
   9.500   0.9477   0.03395   0.02468   0.0006   0.0530   1.0000
   9.750   0.9659   0.03516   0.02596   0.0015   0.0508   1.0000
  10.000   0.9853   0.03704   0.02788   0.0021   0.0489   1.0000
  10.250   0.9987   0.03895   0.03022   0.0039   0.0473   1.0000
  10.500   1.0096   0.04088   0.03250   0.0059   0.0453   1.0000
  10.750   1.0190   0.04264   0.03450   0.0079   0.0435   1.0000
  11.000   1.0275   0.04435   0.03639   0.0100   0.0421   1.0000
  11.250   1.0344   0.04624   0.03843   0.0120   0.0410   1.0000
  11.500   1.0408   0.04861   0.04089   0.0139   0.0401   1.0000
  11.750   1.0298   0.05129   0.04398   0.0179   0.0394   1.0000
  12.000   1.0145   0.05434   0.04744   0.0217   0.0387   1.0000
  12.250   0.9965   0.05778   0.05123   0.0248   0.0380   1.0000
  12.500   0.9760   0.06166   0.05543   0.0270   0.0375   1.0000
  12.750   0.9526   0.06618   0.06024   0.0280   0.0372   1.0000
  13.000   0.9253   0.07172   0.06604   0.0275   0.0371   1.0000
  13.250   0.8931   0.07882   0.07338   0.0248   0.0373   1.0000
  13.500   0.8551   0.08844   0.08319   0.0190   0.0379   1.0000
  13.750   0.8112   0.10205   0.09694   0.0097   0.0387   1.0000
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