More drag questions

I am having difficulty understanding what is being presented in the drag debug
window and how it can be used to achieve a target drag level. See the
following screenshot from a level, unaccelerated flight condition like those
normally used in airplane performance flight testing. The aircraft speed,
drag, engines, and polar clcd debug windows are open in the screenshot.

First, a very significant
difference can be seen in the drag level shown in the speed debug window vs
the total drag force shown in the drag debug window – 10,622 lbs in the speed
debug window and 60,857.6 lbs in the drag debug window. This being a stable,
level, unaccelerated flight condition with thrust of 10,633 lbs, it is obvious
that the current drag level at the time of this screenshot was 10,622 lbs, and
the drag coefficient, Cd is 0.07305. None of the drag coefficient build-ups in
the drag debug window are anywhere close to this value, so what purpose do
those build-ups serve in refining this value? A couple of other questions:
“Other drag” in the drag debug window is quite high – 0.33364 on average. It
supposedly consists mostly of “slip_stream_&prop_wash" and
&_control_surfaces.” Why would there be drag for slip stream and
prop wash for a turbojet airplane with underwing mounted engines (A320) and
high sideslip and control surface drag for a steady-state, level,
unaccelerated flight condition with no wind? What is the “wingledcd” parameter
in the “target_cd” buildup? Is this a delta cd value for winglets? The
description of the “wing_winglets_flag” in the SDK says that this is a legacy
FSX parameter not used in the modern flight model. How is this value
determined, and can it be adjusted by the developer?

I suggest you screenshot the CD vs CL curve in debug and paste it as a
background in excel. It’s the best way I found for the tuning process of the
drag against desired model

Thank you, but that it not what I am asking.