Profile drag is lowered primarily by reducing cross section and streamlining.
2.
The aerofoil section was a NACA laminar flow one to have a low profile drag.
3.
The total of the skin-friction drag and the viscosity-related pressure drag is usually called the profile drag.
4.
In flight, this configuration was found to have a profile drag representative of boundary layer transition at 60 % of chord.
5.
The lift, and the profile drag, largely due to skin friction which is contributed to by the whole wing area.
6.
For this reason profile drag is more pronounced at higher speeds, forming the right side of the drag graph's U shape.
7.
The low speed region shows a fall in lift induced drag, through a minimum followed by an increase in profile drag at higher speeds.
8.
Collective pitch was an automatic function of throttle setting and profile drag of the propeller, which to maintain rpm diverted torque away from the rotor as airspeed increased.
9.
Profile drag caused by the deflected ailerons may add further to the difference, along with changes in the lift vectors as one rotates back while the other rotates forward.
10.
In the as delivered configuration, a profile drag was measured which was representative of the wing section with boundary layer transition at the leading edge ( 0 % laminar flow ).
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