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Fig. 38 – External XFOIL program window & *.dat file selection window
Function Description
Polar calculation
Open XFOIL polar
Computing basic aerodynamic characteristics for an airfoil:
CL-lift, CD-drag, CM-moment, versus angle of attack and
Reynolds & Mach number. (airfoil geometry saved to *.dat
file).
Aerodynamic characteristics are computed in XFOIL external
program. Results saved to *.txt file (Fig. 41).
Load file from disk with saved aerodynamic characteristics
(Fig. 41). When *.txt file is loaded, functions below turn active:
Show Drag polar Show drag CD polar, Fig. 42.
Show Lift coefficient Show lift coefficient CL graph, Fig. 42.
Show Moment coefficient Show moment coefficient CM graph, Fig. 42.
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