The initial concept for the vertical and horizontal tail surfaces was based upon the conventional tail design option for the stock Cruiser aircraft. Since I need to be LSA compliant my aircraft requires a bit more wing area (an unreasonable 108 square feet) and that drives the requirement for vertical and horizontal tail area to be somewhat larger. After crunching the numbers a somewhat larger tail design was worked out along with a ventral fin to allow for more vertical fixed surface area. In addition to the larger vertical tail size, the aft fuselage was also stretched 24" to provide more moment arm. The vertical tail uses the full stretch to increase moment arm while the horizontal tail uses only part of it. The difference in aft displacement allows for an elevator without cutouts for rudder deflection and leaves less rudder blanked in a spiral dive situation. The number crunching for the tail, as well as the wing, is being handled by my good friend George Lendich from Australia. He has taken a keen interest in learning that aspect of engineering and reducing such calculations to an Excel spreadsheet. Between myself and Bill Simpson, George is getting a very through engineering education free of the tuition payments that we had.
1) A side view of the aircraft which shows the overall appearance. location and size of the Vertical Tail. The vertical tail design is based on a moderate sweep angle and taper with a vertical trailing edge. This is a complete departure from what was used in the conventional tail Cruiser in planform and mounting as this VT is removable from the airframe rather that permanently installed. If flight testing indicates the VT size to be either excessive or marginal a revised part could be manufactured and installed.
2) A top view of the aircraft which shows the overall appearance. location and size of the Horizontal Tail. The planform of the HT is close to what had been designed for the conventional tail option on the Cruiser. In this instance the span is extended by the add-on mass