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AG36 (ag36-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: AG36 (ag36-il)
Reynolds number: 50,000
Max Cl/Cd: 32.7 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ag36-il-50000.txt
Download as CSV file: xf-ag36-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG36                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4895   0.09444   0.08799   0.0018   1.0000   0.2663
  -8.500  -0.4906   0.09167   0.08531   0.0005   1.0000   0.2801
  -8.250  -0.4815   0.08789   0.08157   0.0013   1.0000   0.2953
  -8.000  -0.4654   0.08392   0.07761   0.0039   1.0000   0.3141
  -7.750  -0.4681   0.08157   0.07535   0.0029   1.0000   0.3373
  -7.500  -0.4518   0.07772   0.07151   0.0064   1.0000   0.3621
  -7.250  -0.4444   0.07457   0.06842   0.0083   1.0000   0.3888
  -7.000  -0.4371   0.07152   0.06543   0.0103   1.0000   0.4172
  -6.750  -0.4279   0.06850   0.06246   0.0130   1.0000   0.4486
  -6.000  -0.3460   0.04091   0.03273  -0.0394   1.0000   0.1416
  -5.750  -0.3203   0.03673   0.02781  -0.0401   1.0000   0.1316
  -5.500  -0.2961   0.03370   0.02428  -0.0398   1.0000   0.1317
  -5.250  -0.2707   0.03111   0.02107  -0.0394   1.0000   0.1339
  -5.000  -0.2453   0.02859   0.01818  -0.0387   1.0000   0.1358
  -4.750  -0.2208   0.02659   0.01607  -0.0379   1.0000   0.1425
  -4.500  -0.1956   0.02490   0.01416  -0.0370   1.0000   0.1550
  -4.250  -0.1695   0.02325   0.01237  -0.0361   1.0000   0.1690
  -4.000  -0.1442   0.02185   0.01102  -0.0351   1.0000   0.1986
  -3.750  -0.1172   0.02024   0.00969  -0.0344   1.0000   0.2615
  -3.500  -0.0799   0.01576   0.00810  -0.0323   1.0000   1.0000
  -3.250  -0.0584   0.01582   0.00759  -0.0314   1.0000   1.0000
  -3.000  -0.0373   0.01591   0.00728  -0.0305   1.0000   1.0000
  -2.750  -0.0163   0.01605   0.00709  -0.0298   1.0000   1.0000
  -2.500   0.0047   0.01624   0.00697  -0.0291   1.0000   1.0000
  -2.250   0.0255   0.01647   0.00697  -0.0285   1.0000   1.0000
  -2.000   0.0461   0.01676   0.00706  -0.0280   1.0000   1.0000
  -1.750   0.0663   0.01711   0.00725  -0.0276   1.0000   1.0000
  -1.500   0.0859   0.01756   0.00755  -0.0273   1.0000   1.0000
  -1.250   0.1046   0.01811   0.00797  -0.0272   1.0000   1.0000
  -1.000   0.1225   0.01878   0.00855  -0.0273   1.0000   1.0000
  -0.750   0.1396   0.01958   0.00926  -0.0276   1.0000   1.0000
  -0.500   0.1594   0.02046   0.01007  -0.0285   0.9985   1.0000
  -0.250   0.2249   0.02143   0.01094  -0.0374   0.9764   1.0000
   0.000   0.2889   0.02223   0.01170  -0.0455   0.9552   1.0000
   0.250   0.3414   0.02282   0.01232  -0.0511   0.9316   1.0000
   0.500   0.3974   0.02325   0.01279  -0.0568   0.9099   1.0000
   0.750   0.4475   0.02355   0.01319  -0.0610   0.8875   1.0000
   1.000   0.4936   0.02373   0.01345  -0.0640   0.8657   1.0000
   1.250   0.5360   0.02383   0.01365  -0.0659   0.8438   1.0000
   1.500   0.5717   0.02398   0.01392  -0.0664   0.8211   1.0000
   1.750   0.6067   0.02402   0.01405  -0.0663   0.7987   1.0000
   2.000   0.6342   0.02428   0.01439  -0.0652   0.7742   1.0000
   2.250   0.6634   0.02434   0.01452  -0.0637   0.7510   1.0000
   2.500   0.6891   0.02451   0.01480  -0.0619   0.7259   1.0000
   2.750   0.7130   0.02476   0.01513  -0.0600   0.6994   1.0000
   3.000   0.7371   0.02494   0.01538  -0.0579   0.6728   1.0000
   3.250   0.7615   0.02505   0.01554  -0.0557   0.6458   1.0000
   3.500   0.7858   0.02523   0.01578  -0.0534   0.6180   1.0000
   3.750   0.8094   0.02561   0.01618  -0.0513   0.5883   1.0000
   4.000   0.8323   0.02616   0.01674  -0.0492   0.5569   1.0000
   4.250   0.8552   0.02675   0.01732  -0.0472   0.5247   1.0000
   4.500   0.8783   0.02730   0.01787  -0.0451   0.4921   1.0000
   4.750   0.8990   0.02801   0.01870  -0.0433   0.4563   1.0000
   5.000   0.9219   0.02836   0.01898  -0.0413   0.4221   1.0000
   5.250   0.9429   0.02897   0.01961  -0.0394   0.3857   1.0000
   5.500   0.9650   0.02951   0.02002  -0.0375   0.3500   1.0000
   5.750   0.9844   0.03057   0.02108  -0.0357   0.3122   1.0000
   6.000   1.0039   0.03173   0.02209  -0.0339   0.2748   1.0000
   6.250   1.0221   0.03308   0.02326  -0.0321   0.2368   1.0000
   6.500   1.0377   0.03495   0.02514  -0.0302   0.2008   1.0000
   6.750   1.0543   0.03711   0.02721  -0.0285   0.1699   1.0000
   7.000   1.0703   0.03979   0.03001  -0.0270   0.1465   1.0000
   7.250   1.0866   0.04270   0.03308  -0.0255   0.1297   1.0000
   7.500   1.1000   0.04624   0.03697  -0.0240   0.1188   1.0000
   7.750   1.1151   0.04980   0.04064  -0.0228   0.1103   1.0000
   8.000   1.1171   0.05394   0.04546  -0.0208   0.1052   1.0000
   8.250   1.1319   0.05752   0.04907  -0.0199   0.0996   1.0000
   8.500   1.1319   0.06265   0.05458  -0.0185   0.0982   1.0000
   8.750   1.1227   0.06769   0.06009  -0.0169   0.0979   1.0000
   9.000   1.1096   0.07281   0.06557  -0.0158   0.0979   1.0000
   9.250   1.0942   0.07798   0.07099  -0.0150   0.0982   1.0000
   9.500   1.0773   0.08307   0.07624  -0.0145   0.0986   1.0000
   9.750   0.9701   0.09871   0.09220  -0.0275   0.1143   1.0000
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