wing needs CG

[RonPlanes]

Can anyone figure out where the cg should be on this wing?

[Sparky Paul]

Nope.

[Ollie]

The allowable CG range depends heavily on the tail area and moment arm relative to the wing. It is the whole configuration of the polane that determines the CG range. Here are the tail volume coefficients by Dr. Mark Drela:

"Ch = (A_hori/A_wing) * (tail_arm/avg_wing_chord)
Cv = (A_vert/A_wing) * (tail_arm/avg_wing_span )

A well-sized tail will be in the range...
Ch = 0.35 - 0.50
Cv = 0.02 - 0.035
If the Ch and/or Cv are below the minimum values, the handling will suffer."

After you have calculated the tail volume coefficients we can comment on CG location.

[Sparky Paul]

Since we generally start with the wing and find the empennage areas from that, renobulating Mark's equation to work from an initial Ch and Cv is handy...
.
Ah=Ch*(Area_wing*mac/tail_arm) Ch=0.35->0.50
Av=Cv*(Area_wing*avg_wing_span/tail_arm) Cv=0.02->0.035
.
with this in spread sheet form, the required areas for a selected coefficient pop out..
Did this for planes built and to be built.
Interesting to note the values for eBakerRacerVee1996 show the sizes it has are too large... but it is a good flier.. :)
A check run on the Senoirta showed it too wouldn't be hurt by smaller surfaces.