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LOCKHEED C-5A BL0 AIRFOIL (c5a-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-5A BL0 AIRFOIL (c5a-il)
Reynolds number: 50,000
Max Cl/Cd: 27.24 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c5a-il-50000.txt
Download as CSV file: xf-c5a-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6622   0.09001   0.08264  -0.0444   1.0000   0.1488
 -10.000  -0.6816   0.08396   0.07658  -0.0454   1.0000   0.1407
  -9.750  -0.7581   0.07866   0.07127  -0.0425   1.0000   0.1345
  -9.500  -0.7812   0.07463   0.06710  -0.0398   1.0000   0.1299
  -9.250  -0.7931   0.07059   0.06297  -0.0373   1.0000   0.1269
  -9.000  -0.8153   0.06646   0.05858  -0.0337   1.0000   0.1232
  -8.750  -0.8478   0.06299   0.05438  -0.0282   1.0000   0.1179
  -8.500  -0.8440   0.05925   0.05045  -0.0260   1.0000   0.1169
  -8.250  -0.8416   0.05583   0.04675  -0.0234   1.0000   0.1162
  -8.000  -0.8373   0.05259   0.04315  -0.0207   1.0000   0.1157
  -7.750  -0.8298   0.04948   0.03967  -0.0182   1.0000   0.1153
  -7.500  -0.8184   0.04650   0.03632  -0.0160   1.0000   0.1149
  -7.250  -0.8037   0.04368   0.03311  -0.0140   1.0000   0.1147
  -7.000  -0.7861   0.04111   0.03015  -0.0122   1.0000   0.1152
  -6.750  -0.7667   0.03888   0.02751  -0.0105   1.0000   0.1170
  -6.500  -0.7439   0.03660   0.02510  -0.0095   1.0000   0.1215
  -6.250  -0.7191   0.03478   0.02320  -0.0086   1.0000   0.1279
  -6.000  -0.6900   0.03295   0.02127  -0.0079   1.0000   0.1347
  -5.750  -0.6627   0.03146   0.01981  -0.0069   1.0000   0.1476
  -5.500  -0.6387   0.02987   0.01845  -0.0056   1.0000   0.1662
  -5.250  -0.6239   0.02799   0.01691  -0.0031   1.0000   0.1978
  -5.000  -0.6272   0.02441   0.01491   0.0012   1.0000   0.3271
  -4.750  -0.6379   0.02528   0.01757   0.0147   1.0000   0.6576
  -4.500  -0.6227   0.02790   0.02004   0.0234   1.0000   0.7196
  -4.250  -0.5074   0.03658   0.02802   0.0263   1.0000   0.8146
  -4.000  -0.4248   0.03744   0.02829   0.0191   1.0000   0.8524
  -3.750  -0.3435   0.03739   0.02775   0.0105   1.0000   0.8859
  -3.500  -0.2878   0.03655   0.02660   0.0046   1.0000   0.9062
  -3.250  -0.2453   0.03565   0.02549   0.0007   1.0000   0.9246
  -3.000  -0.2030   0.03474   0.02436  -0.0035   1.0000   0.9424
  -2.750  -0.1622   0.03381   0.02327  -0.0077   1.0000   0.9582
  -2.500  -0.1218   0.03290   0.02221  -0.0120   1.0000   0.9721
  -2.250  -0.0791   0.03200   0.02118  -0.0168   1.0000   0.9849
  -2.000  -0.0322   0.03105   0.02011  -0.0226   1.0000   0.9966
  -1.750  -0.0137   0.03048   0.01950  -0.0229   1.0000   1.0000
  -1.500  -0.0083   0.03007   0.01909  -0.0206   1.0000   1.0000
  -1.250  -0.0034   0.02969   0.01871  -0.0182   1.0000   1.0000
  -1.000   0.0009   0.02935   0.01838  -0.0157   1.0000   1.0000
  -0.750   0.0044   0.02904   0.01808  -0.0130   1.0000   1.0000
  -0.500   0.0072   0.02877   0.01782  -0.0102   1.0000   1.0000
  -0.250   0.0093   0.02852   0.01759  -0.0073   1.0000   1.0000
   0.000   0.0106   0.02830   0.01739  -0.0043   1.0000   1.0000
   0.250   0.0110   0.02810   0.01721  -0.0012   1.0000   1.0000
   0.500   0.0106   0.02792   0.01706   0.0020   1.0000   1.0000
   0.750   0.0093   0.02776   0.01692   0.0054   1.0000   1.0000
   1.000   0.0071   0.02762   0.01681   0.0088   1.0000   1.0000
   1.250   0.0041   0.02748   0.01670   0.0123   1.0000   1.0000
   1.500   0.0007   0.02735   0.01660   0.0159   1.0000   1.0000
   1.750  -0.0029   0.02725   0.01652   0.0194   1.0000   1.0000
   2.000  -0.0055   0.02718   0.01647   0.0227   1.0000   1.0000
   2.250  -0.0058   0.02718   0.01650   0.0256   1.0000   1.0000
   2.500  -0.0005   0.02736   0.01669   0.0274   1.0000   1.0000
   2.750   0.0098   0.02771   0.01706   0.0284   1.0000   1.0000
   3.000   0.0232   0.02821   0.01759   0.0288   1.0000   1.0000
   3.250   0.0383   0.02883   0.01824   0.0288   1.0000   1.0000
   3.500   0.0544   0.02955   0.01902   0.0286   1.0000   1.0000
   3.750   0.0734   0.03042   0.01996   0.0278   0.9988   1.0000
   4.000   0.1480   0.03257   0.02233   0.0168   0.9720   1.0000
   4.250   0.2150   0.03391   0.02393   0.0082   0.9404   1.0000
   4.500   0.2954   0.03433   0.02470  -0.0009   0.8980   1.0000
   4.750   0.3815   0.03368   0.02447  -0.0093   0.8599   1.0000
   5.000   0.4381   0.03267   0.02387  -0.0123   0.8242   1.0000
   5.250   0.5901   0.02506   0.01725  -0.0201   0.7332   1.0000
   5.500   0.6410   0.02353   0.01403  -0.0152   0.4049   1.0000
   5.750   0.6449   0.02579   0.01513  -0.0108   0.3009   1.0000
   6.000   0.6773   0.02798   0.01675  -0.0116   0.2433   1.0000
   6.250   0.7177   0.02988   0.01853  -0.0135   0.2158   1.0000
   6.500   0.7493   0.03160   0.02016  -0.0140   0.1991   1.0000
   6.750   0.7766   0.03340   0.02211  -0.0138   0.1883   1.0000
   7.000   0.8060   0.03566   0.02433  -0.0141   0.1808   1.0000
   7.250   0.8221   0.03743   0.02655  -0.0119   0.1748   1.0000
   7.500   0.8445   0.03958   0.02871  -0.0112   0.1678   1.0000
   7.750   0.8611   0.04218   0.03168  -0.0094   0.1649   1.0000
   8.000   0.8715   0.04466   0.03467  -0.0066   0.1622   1.0000
   8.250   0.8807   0.04725   0.03766  -0.0040   0.1586   1.0000
   8.500   0.8904   0.05011   0.04084  -0.0016   0.1560   1.0000
   8.750   0.8951   0.05349   0.04461   0.0011   0.1557   1.0000
   9.000   0.8988   0.05692   0.04836   0.0037   0.1546   1.0000
   9.500   0.8780   0.06497   0.05722   0.0103   0.1566   1.0000
   9.750   0.8561   0.06976   0.06233   0.0134   0.1601   1.0000
  10.000   0.8413   0.07461   0.06735   0.0153   0.1632   1.0000
  10.250   0.5924   0.11611   0.10878  -0.0219   0.4018   1.0000
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