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AG46ct -02f rot. (ag46ct02r-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: AG46ct -02f rot. (ag46ct02r-il)
Reynolds number: 1,000,000
Max Cl/Cd: 88.65 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ag46ct02r-il-1000000.txt
Download as CSV file: xf-ag46ct02r-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG46ct  -02f rot.                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4815   0.09148   0.09001   0.0137   1.0000   0.0083
  -8.500  -0.4815   0.08722   0.08576   0.0124   1.0000   0.0085
  -8.250  -0.4819   0.08285   0.08140   0.0111   1.0000   0.0088
  -4.250  -0.3122   0.01121   0.00643  -0.0290   1.0000   0.0071
  -4.000  -0.2857   0.01025   0.00537  -0.0286   1.0000   0.0074
  -3.750  -0.2592   0.00970   0.00477  -0.0282   1.0000   0.0082
  -3.500  -0.2326   0.00916   0.00417  -0.0277   1.0000   0.0090
  -3.250  -0.2061   0.00868   0.00364  -0.0273   1.0000   0.0096
  -3.000  -0.1796   0.00830   0.00322  -0.0269   1.0000   0.0099
  -2.750  -0.1475   0.00750   0.00232  -0.0277   0.9966   0.0114
  -2.500  -0.1090   0.00713   0.00192  -0.0299   0.9834   0.0137
  -2.250  -0.0712   0.00673   0.00146  -0.0318   0.9507   0.0219
  -2.000  -0.0464   0.00665   0.00121  -0.0306   0.8539   0.0459
  -1.750  -0.0223   0.00667   0.00107  -0.0297   0.7687   0.0925
  -1.500   0.0043   0.00649   0.00098  -0.0295   0.7356   0.1626
  -1.250   0.0315   0.00627   0.00090  -0.0294   0.7166   0.2431
  -1.000   0.0587   0.00596   0.00086  -0.0294   0.7032   0.3527
  -0.750   0.0857   0.00547   0.00082  -0.0294   0.6887   0.5141
  -0.500   0.1111   0.00480   0.00081  -0.0290   0.6720   0.7367
  -0.250   0.1330   0.00439   0.00081  -0.0273   0.6532   0.8869
   0.000   0.1664   0.00426   0.00076  -0.0281   0.6305   1.0000
   0.250   0.1941   0.00436   0.00073  -0.0279   0.6077   1.0000
   0.500   0.2218   0.00446   0.00071  -0.0278   0.5838   1.0000
   0.750   0.2496   0.00457   0.00071  -0.0276   0.5607   1.0000
   1.000   0.2773   0.00469   0.00072  -0.0275   0.5377   1.0000
   1.250   0.3051   0.00481   0.00073  -0.0274   0.5135   1.0000
   1.500   0.3329   0.00493   0.00076  -0.0273   0.4890   1.0000
   1.750   0.3606   0.00508   0.00080  -0.0272   0.4613   1.0000
   2.000   0.3883   0.00523   0.00084  -0.0271   0.4352   1.0000
   2.250   0.4159   0.00541   0.00090  -0.0270   0.4047   1.0000
   2.500   0.4435   0.00560   0.00099  -0.0269   0.3759   1.0000
   2.750   0.4709   0.00581   0.00107  -0.0269   0.3450   1.0000
   3.000   0.4984   0.00603   0.00117  -0.0268   0.3149   1.0000
   3.250   0.5259   0.00625   0.00129  -0.0267   0.2862   1.0000
   3.500   0.5532   0.00650   0.00141  -0.0266   0.2543   1.0000
   3.750   0.5806   0.00675   0.00157  -0.0266   0.2271   1.0000
   4.000   0.6078   0.00703   0.00173  -0.0265   0.1977   1.0000
   4.250   0.6350   0.00730   0.00191  -0.0264   0.1744   1.0000
   4.750   0.6894   0.00785   0.00231  -0.0262   0.1325   1.0000
   5.000   0.7165   0.00812   0.00252  -0.0261   0.1164   1.0000
   5.250   0.7436   0.00842   0.00275  -0.0260   0.1007   1.0000
   5.500   0.7706   0.00870   0.00299  -0.0259   0.0881   1.0000
   5.750   0.7975   0.00900   0.00326  -0.0258   0.0756   1.0000
   6.000   0.8244   0.00930   0.00354  -0.0257   0.0650   1.0000
   6.250   0.8512   0.00962   0.00383  -0.0256   0.0546   1.0000
   6.500   0.8778   0.00997   0.00416  -0.0254   0.0456   1.0000
   6.750   0.9041   0.01038   0.00454  -0.0252   0.0363   1.0000
   7.000   0.9305   0.01076   0.00492  -0.0251   0.0301   1.0000
   7.250   0.9568   0.01116   0.00535  -0.0249   0.0250   1.0000
   7.500   0.9822   0.01180   0.00598  -0.0246   0.0187   1.0000
   7.750   1.0085   0.01213   0.00636  -0.0244   0.0167   1.0000
   8.000   1.0340   0.01270   0.00693  -0.0241   0.0136   1.0000
   8.250   1.0588   0.01345   0.00779  -0.0237   0.0116   1.0000
   8.500   1.0843   0.01392   0.00835  -0.0234   0.0105   1.0000
   8.750   1.1093   0.01450   0.00898  -0.0232   0.0093   1.0000
   9.000   1.1315   0.01577   0.01040  -0.0225   0.0078   1.0000
   9.250   1.1555   0.01649   0.01122  -0.0221   0.0073   1.0000
   9.500   1.1799   0.01709   0.01191  -0.0218   0.0068   1.0000
   9.750   1.2034   0.01785   0.01276  -0.0214   0.0063   1.0000
  10.000   1.2265   0.01864   0.01364  -0.0210   0.0058   1.0000
  10.250   1.2484   0.01961   0.01473  -0.0205   0.0054   1.0000
  10.500   1.2650   0.02160   0.01694  -0.0195   0.0049   1.0000
  10.750   1.2770   0.02430   0.01996  -0.0183   0.0046   1.0000
  11.000   1.2972   0.02533   0.02112  -0.0177   0.0045   1.0000
  11.250   1.3152   0.02662   0.02257  -0.0170   0.0043   1.0000
  11.500   1.3311   0.02816   0.02427  -0.0163   0.0041   1.0000
  11.750   1.3448   0.02988   0.02617  -0.0154   0.0039   1.0000
  12.000   1.3575   0.03156   0.02802  -0.0146   0.0037   1.0000
  12.250   1.3683   0.03330   0.02990  -0.0138   0.0035   1.0000
  12.500   1.3780   0.03498   0.03171  -0.0131   0.0034   1.0000
  12.750   1.3794   0.03707   0.03394  -0.0119   0.0032   1.0000
  13.000   1.3763   0.03969   0.03670  -0.0117   0.0032   1.0000
  13.250   1.3660   0.04459   0.04179  -0.0150   0.0031   1.0000
  13.500   1.3542   0.05105   0.04843  -0.0204   0.0031   1.0000
  13.750   1.3317   0.06018   0.05777  -0.0275   0.0031   1.0000
  14.000   1.2968   0.07196   0.06976  -0.0354   0.0032   1.0000
  14.250   1.2468   0.08659   0.08462  -0.0438   0.0034   1.0000
  14.500   1.1967   0.10126   0.09945  -0.0515   0.0037   1.0000
  14.750   1.1499   0.11558   0.11390  -0.0587   0.0040   1.0000
  15.000   1.1119   0.12883   0.12725  -0.0652   0.0042   1.0000
  15.250   1.0734   0.14334   0.14184  -0.0724   0.0044   1.0000
  15.500   1.0144   0.16550   0.16407  -0.0831   0.0047   1.0000
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