While we wait for someone to walk in with their VSPAERO drag results, I must admit up front I have nothing to offer in that regard. This info is a space filler until then. Honestly, since I last rode the OpenVSP horse, I’m waiting to see through your work if it is likely worth spending a lot of time for the results VSPAero will produce.
What follows
may be of interest because:
a) It deals with aircraft drag
b) It contains actual values (wellestimates)
c) The project aircraft general configuration (the Beetlemaster) is similar to Airplane 5.
Background: The Beetlemaster idea is the product of a
long running thread here on HBA. In general, it envisions a small, centerline twin aircaft powered by modified VW Type 1 engines of approx 80HP each driving fixed pitch props. Four different concepts emerged from four members who each had slightly different goals
:

Pops: (post 310) Strutbraced, 2 place tandem seat of primarily metal construction. 1500lb MTOW, 140 sq ft wing area, 34’ span (AR= 8.24)

Autoreply: (post 309) Cantilever wing, 4 place, aerodynamically clean composite construction, ?1600 ? lb MTOW, 126 sq ft wing area, 46’ span (AR = 16.07)

Vigilant1: Cantilever wing, 2 place, composite wing, 1600 lb MTOW, 126 sq ft wing, 35’ span (AR = 9.7)

Jan Carlsson: Most similar to Pops’s design.
Drag Estimate:
Parasite drag: This estimate of my version of the Beetlemaster was performed via the method described by Raymer and Roncz for conceptual design purposes. Fuselage, tail, and wing drag is calculated by applying a skin friction factor (based on aircraft and construction type) to the wetted areas of the various structures above. After this, drag from particular additional items (landing gear, struts, a stopped prop, etc) are calculated based primarily on frontal area, and added to the previously computed skin friction drag. For my design:
 Wetted wing area (disregarding fuselage carrythrough): 238.38 sq ft
 Wetted tail area: 62.57 sq ft
 Fuselage (incl tail booms): 158.7 sq ft
Total wetted area: 459.65 sq ft.
Skin Friction Coefficient Selected: .0058 Resultant equivalent flat plate drag area of above:
2.67 sq ft
For reference: Skin friction coefficient values for typical composite design: .0050 (Roncz, Raymer)
For typical metal design: Roncz: .0060  .0065 Raymer: .0058
For typical rag and tube: .014 (Hiscocks)
Additional nonlift drag (equiv flat plate area):
 Landing gear (Raymer, tricycle, leg and wheel fairings):
.41 sqft
 Stopped propeller (Raymer, fixed pitch, 2 blade, 54” dia, AR 8):
0.9 sq ft.
 Total nonlift effective flatplate drag area
 2 engines running: 3.08 sq ft
 1 stopped propeller: 3.98 sq ft
Anticipated parasite drag values:
 70kts (climb), SL, two engines running:
51 lbs
 70 kts (climb), SL, 1 stopped prop:
66 lbs
 120 Kt cruise, 6000’ MSL, two engine running:
126 lbs
Induced drag
– 1600 lbs, wing as above, SL 70 kt climb:
53 lbs
– 1600 lbs, wing as above, 6000’ MSL, 120 kt cruise:
21 lbs
Thrust required for level flight, 1600 lbs:
SL, 70 kts, 2 engines: 104 lbs
SL, 70 kts, 1 stopped propeller: 119 lbs
120 kt cruise at 6000' MSL: 147 lbs
Anyway, for what it is worth. Comparing to VSPAERO values for a similar aircraft design would be interesting.