V-STOL Solution

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title: "V-STOL Solution" type: doc version: 1 created: 2026-02-28 author: "Wikipedia contributors" status: active scope: public tags: ["v-stol-aircraft-corporation-aircraft", "1990s-united-states-ultralight-aircraft", "homebuilt-aircraft", "single-engined-pusher-aircraft"] description: "American ultralight STOL aircraft" topic_path: "geography/united-states" source: "https://en.wikipedia.org/wiki/V-STOL_Solution" license: "CC BY-SA 4.0" wikipedia_page_id: 0 wikipedia_revision_id: 0

::summary American ultralight STOL aircraft ::

::data[format=table title="Infobox aircraft"]

Field	Value
name	Solution
aircraft_type	Ultralight aircraft
national_origin	United States
manufacturer	V-STOL Aircraft
designer	Dick Turner
status	Production completed
introduction	1998
::

| name = Solution | logo = | logo_size = | image = | alt = | caption = | long_caption = | other_names = | aircraft_type = Ultralight aircraft | aim = | outcome = | related = | national_origin = United States | manufacturer = V-STOL Aircraft | design_group = | designer = Dick Turner | builder = | issuer = | status = Production completed | owners = | primary_user = | more_users = | service = | major_applications = | proposals = | prototypes = | number_built = | construction_number = | civil_registration = | military_serial = | radio_code = | requirement = | aircraft_carried = | flights = | total_hours = | total_distance = | construction_date = | introduction = 1998 | retired = | first_flight = | initiated = | in_service = | last_flight = | expected = | developed_from = | variants = | developed_into = | preservation = | fate = | predecessors = | successors = | concluded = The V-STOL Solution is an American ultralight aircraft that was designed by Dick Turner in 1998 and produced by V-STOL Aircraft. The aircraft was supplied as a kit for amateur construction.

Design and development

The design goal of the Solution was to produce a legal US FAR 103 Ultralight Vehicles regulations compliant single seat ultralight that could be easily converted to a two-seater with the addition of a second seat and a larger engine. FAR Part 103 specifies a maximum empty weight of 254 lb and the Solution has a standard empty weight of 246 lb. It features a cable-braced high-wing, a single-seat, open cockpit, conventional landing gear and a single engine in pusher configuration.

The aircraft is made from bolted-together aluminium tubing, with the flying surfaces covered in Dacron sailcloth. Its 33 ft span wing has a wing area of 183 sqft, which is large enough to support a second person. The second seat would be installed behind the first, in tandem, and could be optionally equipped with dual controls.

The pilot is accommodated on an open seat and has conventional three-axis controls in the form of a centre stick and rudder pedals. The standard engine provided for single seat flying was the single cylinder two-stroke Rotax 277 of 28 hp, while larger engines could be installed for two-seat operations.

V-STOL Aircraft had the design on the market for only a short period before the company went out of business. Assembly time from the kit is estimated at 50 hours.

Specifications (Solution single-seat)

|ref=Cliche and the Virtual Ultralight Museum |prime units?=imp General characteristics

|genhide=

|crew=one |capacity= |length m= |length ft= |length in= |length note= |span m= |span ft=33 |span in= |span note= |height m= |height ft= |height in= |height note= |wing area sqm= |wing area sqft=183 |wing area note= |aspect ratio= |airfoil= |empty weight kg= |empty weight lb=246 |empty weight note= |gross weight kg= |gross weight lb=498 |gross weight note= |fuel capacity= |more general= Powerplant

|eng1 number=1 |eng1 name=Rotax 277 |eng1 type=single cylinder two-stroke aircraft engine |eng1 kw= |eng1 hp=28

|prop blade number= |prop name= |prop dia m= |prop dia ft= |prop dia in= |prop note=

Performance

|perfhide=

|max speed kmh= |max speed mph= |max speed kts= |max speed note= |cruise speed kmh= |cruise speed mph=45 |cruise speed kts= |cruise speed note= |stall speed kmh= |stall speed mph=22 |stall speed kts= |stall speed note= |never exceed speed kmh= |never exceed speed mph= |never exceed speed kts= |never exceed speed note= |range km= |range miles= |range nmi= |range note= |endurance= |ceiling m= |ceiling ft= |ceiling note= |g limits= |roll rate= |glide ratio= |climb rate ms= |climb rate ftmin=500 |climb rate note= |time to altitude= |sink rate ms= |sink rate ftmin= |sink rate note= |lift to drag= |wing loading kg/m2= |wing loading lb/sqft=2.7 |wing loading note= |power/mass= |thrust/weight= |more performance= |avionics=

|see also= |related= |similar aircraft= |lists=

References

References

1. Cliche, Andre: ''Ultralight Aircraft Shopper's Guide'' 8th Edition, page E-37 Cybair Limited Publishing, 2001. {{ISBN. 0-9680628-1-4
2. Virtual Ultralight Museum. (n.d.). "Solution".

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